Joint Conference of

ICTACEM 2021, APCATS 2021, AJSAE 2021 and AeSI 2021

December 20 -22, 2021

TECHNICAL PROGRAM
AND
BOOK OF ABSTRACTS

Conference Organizer and host institution

Aerospace Engineering Department, Indian Institute of Technology Kharagpur, India
Conference co-sponsors and other Supporting institutions
The Aeronautical Society of India (AeSI)
Asian-Pacific Conference on Aerospace Technology and Science (APCATS)
Asian Joint Symposium on Aerospace Engineering (AJSAE)
 EDITORS:
Prof. Anup Ghosh,

Prof. Kalyan Prasad Sinhamahapatra,

Prof. Ratan Joarder,

Prof. Sikha Hota

ASSOCIATED EDITORS:
Prof. Akshay Prakash

Prof. Amardip Ghosh

Prof. Arnab Roy

Prof. Bhrigu Nath Singh

Prof. Chetankumar Sureshbhai Mistry
Prof. Dipak Kumar Maiti
Prof. Manas Kumar Laha

Prof. Manoranjan Sinha

Prof. Mira Mitra

Prof. Mohammed Rabius Sunny

Prof. Mrinal Kaushik

Prof. Naba Kumar Peyada

Prof. Prasun Jana

Prof. Sandeep Saha

Prof. Somnath Ghosh

Prof. Srinibas Karmakar

Prof. Sunil Manohar Dash

Prof. Suresh Chandra Pradhan

Prof. Susmita Bhattacharyya

2
First Impression: 2021

© Abstracts of Authors 2021

© IIT Kharagpur
© Typography Vidya Kutir Publications

No part of this publication may be reproduced or transmitted in any form by any means,
electronic or mechanical, including photocopy, recording, or any information storage and
retrieval system, without permission in writing from the copyright owners.

DISCLAIMER
Authors are solely responsible for the views, opinions, correctness, authenticity, and
permissions required for the chapter. Editors or Publisher has no responsibility on behalf
of the authors in whatsoever manners.

ISBN: 978-93-92403-23-1

3
 FOREWORD

The department of Aerospace Engineering, Indian Institute of Technology, Kharagpur (IIT Kharagpur)
is hosting International Conference on Theoretical, Applied, Computational and Experimental
Mechanics (ICTACEM) every three years since 1998. It is indeed a great pleasure that the 8th edition of
ICTACEM in 2021 is being held jointly with Asia Pacific Conference for Aerospace Technology and
Science (APCATS), Asian Joint Symposium on Aerospace Engineering (AJSAE) and the annual
symposium of Aeronautical Society of India, Kolkata Chapter and Aerospace Engineering Department,
IIT Kharagpur is privileged to host the joint conference. ICTACEM was conceived to bring together
the researchers in all disciplines of mechanics to exchange and share knowledge between people from
different parts of the world. A special focus is always given to the recent advances in Aerospace science
and technologies. The Joint Conference 2021 has taken extra care to highlight the latest aerospace
researches and developments with an emphasis on the developments in the Asian countries. With more
than a dozen plenary talks from renowned personalities and over 150 excellent contributory papers the
ICTACEM-APCATS-AJSAE-AeSI joint conference 2021 will definitely be enriching and motivating
to the participating academician and researchers and in particular to our young researchers. Let the three
days of intense scientific discussion helps our participants to come closer and hone their scientific quest.

Prof. K.P. Sinhamahapatra

Organizing Chair

4
 SECRETARIATS OF JOINT CONFERENCE OF ICTACEM,
APCATS, AJSAE AND AESI, KOLKATA
• Mr. A. S. Kiran Kumar, Patron, President, AeSI, New Delhi, Ex-Chairman, ISRO
• Prof. M. Sinha, Mentor, HoD, Department of Aerospace Engineering, IIT Kharagpur
• Gp. Capt. T. K. Ray, Mentor, Chairman, AeSI, Kolkata
• Prof. K. P. Sinhamahapatra, Conference Chair, Department of Aerospace Engineering, IIT
Kharagpur, ictacem@aero.iitkgp.ac.in
• Prof. C. D. Kong, Conference Chair, International Visiting Professor, Department of
Aerospace Engineering, IIT Kharagpur, cdgong@aero.iitkgp.ac.in
• Prof. B. N. Singh, Conference Vice-Chair, Department of Aerospace Engineering, IIT
Kharagpur, ictacem@aero.iitkgp.ac.in
• Prof. Amar Nath Mallick, EC Member, AeSI, Kolkata Chapter & Professor, Department of
Mechanical Engineering, NIT, Durgapur, amarnath.mullick@me.nitdgp.ac.in

INTERNATIONAL COMMITTEE OF JOINT CONFERENCE OF

ICTACEM, APCATS, AJSAE AND AESI, KOLKATA
• Prof. Xue-Ying Deng, Honorary Chair, Beihang University, China
• Prof. C. D. Kong, Honorary Chair, Chosun University, Korea
• Dr. C. Y. Hwang, Honorary Co-Chair,Korea Aerospace Research Institute, Korea
• Prof. S. S. Lee, Honorary Co-Chair; Gyeongsang National University, Korea
• Prof. J. H. Hwang, Honorary Co-Chair. Korea Aerospace University, Korea
• Prof. Yankui Wang, Honorary Co-Chair, Beihang University, China
• Prof. Hai Huang, Honorary Co-Chair, Beihang University, China
• Prof. Guowei Yang, Honorary Co-Chair, ARMC, CAS, China
• Prof. Nobuhiko Yamasaki, Honorary Co-Chair, Kyushu University, Japan
• Prof. Tai-Yan Kam, Honorary Co-Chair, National Chiao Tung University, Taiwan, China
• Prof. Mahir Dursun, Honorary Co-Chair, Gazi University, Turkey

INTERNATIONAL REPRESENTATIVES
• Prof. D. K. Maiti, Department of Aerospace Engineering, IIT
Kharagpur, dkmaiti@aero.iitkgp.ac.in
• Dr. C. Y. Hwang, Korea Aerospace Research Institute, cyhwang@kari.re.kr
• Prof. Shenyan Chen, Beihang University, chenshenyan@buaa.edu.cn
• Prof. Nobuhiko Yamasaki, Kyushu University, yamasaki@aero.kyushu-u.ac.jp
• Prof. J. L. Tsai, National Chiao Tung University, jialin@mail.nctu.edu.tw
• Prof. Mahir Dursun, Gazi University, mdursun@gazi.edu.tr

5
TECHNICAL PROGRAM

6
 Venue SL1 Durati
on

Inauguration Of Joint Conference -- ICTACEM 2021, APCATS 2021, AJSAE 2021 and AeSI 2021

8:40 Welcome Address By Chairman -- Prof. K. P. Sinhamahapatra 0:05

8:45 0:05
Opening Address By Secretary -- Prof. R. Joarder, Prof. Anup Ghosh
8:50 0:10
Address on behalf of APCATS & AJSAE -- Prof. C. D. Kong, Honorary Chair
20 December

9:00 0:05

09:05 Address by President AeSI -- Shri A.S. Kiran Kumar 0:10

9:15 Address By Chief Guest, Director, IIT Kharagpur -- Prof. V. K. Tewari 0:10

Address By Guest of Honour -- Prof. P. K. Dutta

0:05
Vote Of Thanks by Vice Chairman of Conference -- Prof. B. N. Singh
9:25
Plenary Session -1: Fundamental features of perturbation/fluctuation growth in high-speed compressible shear
flows
Prof. Sharath Girimaji, TAMU, USA 0:45
Session Chair: Prof. Somnath Ghosh
09:30 Ms. Swagatika Pradhan
Venue SL1 SL3
Plenary Session -3: Thermal control system
design and test for APSCO SSS-1 satellite
Plenary Session -2: Spray-Swirl Interactions: Some Insights Prof.Shenyan Chen, Beihang University,
0:45
Prof. Saptarshi Basu, IISc Bengaluru, India Beijing, China
Session Chair: Prof. S. Karmakar Session Chair: Prof. S. Bhattacharyya
10:15 Mr. Saugata Mandal Mr. Narendra Kumar
Venue SL1 SL2 SL3 SL4
Session Chair:
Session Chair: Prof. Somnath Session Chair: Prof. Prof. S.
Ghosh Session Chair: Prof. P. Jana S. Karmakar Bhattacharyya
Ms. Swagatika Pradhan Mr. Raj Kumar Mr. Saugata Mandal Ms. Reshma G
Scaling law for core length in Dynamic Modelling of a Porous Design and Numerical APSCO SSS-1
supersonic free jets Functionally Graded Rotor- Study of Variable Communication
bearing System for Different Geometry Scramjet System Design and 0:15
Temperature Distributions Inlet for Mach 5 to Implementation
11:00 Mach 7
Arun Kumar Perumal and Aneesh Batchu, Bharath Shivashree S Hao Tian, Jikai
Ethirajan Rathakrishnan Obalareddy and Prabhakar Wang and Hai
Sathujoda Huang
Parametric study of bio-inspired Free Vibration Analysis of a Unsteady Simulation Development of a
corrugated airfoil geometry in a Rotor-bearing System having of Frontal Cavity in Flight Simulator for
0:15
forward flight at Reynolds Corrosion Defect Supersonic Flows Low-End
11:15 number 80000 Computers
Yagya Dutta Dwivedi, N Bharath Obalareddy, Aneesh Jayraj Deshmukh, Amish Jindal,
Lakshmi Narasimhan, Jayendra Batchu and Prabhakar Dinesh Bajaj, Manini Mittal,
Rajanala and Kameswara Sathujoda Devabrata Sahoo and Gandharv Jaggi and
Sridhar Vepa Ashish Vashishtha Abha Gupta
11:30 Break 0:15
Session Chair:
Session Chair: Prof. Arnab Session Chair: Prof. M. R. Session Chair: Prof. Prof. S.
Roy Sunny Amardip Ghosh Bhattacharyya
Mr. Pranay Kumar Mr. Raj Kumar Mr. Saisantosh Iyer Ms. Reshma G
AERODYNAMIC STUDY ON A numerical study of integrity Study of effect of Design and
AIRFOIL WITH U-SHAPE of Z-pinned laminates rotational rate of a Analysis of Active
TUBERCLE GEOMETRY cylinder on the Phased Array
volume fraction of Antenna for 80 kg- 0:15
vapor formed during Class Micro-
nucleate boiling Satellite SAR
11:45 phenomenon of water
B Sudarshan, V Viswanath, S Arun Kumar, Sourabh Borchate Manjunath S V, Chan Mi Song,
Mukund, J V Sujan and S Suhas and C.S. Upadhyay Maharana Sarat Seung Joo Jo,

7
 Kumar and Abdul Chang Hyun Lee,
Sharief Myeong Jae Lee,
Seung Hun Lee,
Sung Chan Song
and Hyun-Ung Oh
An Improved Unsteady CFD Assessing post impact LES of a Swirl- Robust Navigation
analysis of combined pitching mechanical characteristics of Stabilized Turbulent with NavIC
and plunging airfoil using glass fiber laminates by using Kerosene Spray Software Receiver 0:15
OpenFoam beam coupons: A simplistic Flame in a Model using Vector Delay
12:00 approach Combustor Lock Loops
P Srinivasa Murthy Manoj K. Singh and R. Kitey Kaidi Wan, Yunzhe Ravindar Reddy
Huang, Zhenxun Gao, Dadapur,
Yong He and Chittimalla Srinu
Chongwen Jiang and Laxminarayana
Parayitam
Numerical Simulation of flow Performance Analysis of Experimental and Linearized control
over blunt body with Passive Circular and Lemon Bore Numerical Simulation of an axisymmetric
Control Technique Hydrodynamic Journal Bearing for Residence Time spinning top to a 0:15
Considering Surface Roughness Distribution of regular precession
12:15 and Shear Thinning Effect Deactivation Tank trajectory
M V Nitya, Vineeta Bhat, Sai Kuldeep Narwat, Vivek Kumar, Prince Kumar Jain, Anirudh
Swaroop and Snehal U M Simran Jeet Singh, Abhishek Samiran Sengupta, Chandramouli and
Kumar and Satish C Sharma Vimal Kotak, Kajal Abhijit Sarkar
Dhole, Nilesh Gohel
and Sujay
Bhattacharya
Near - Wake Flow Structures of Performance analysis of rough Theoretical & Satellite topology
a Rectangular Wing at the surface multi-recess porous experimental study on and continuous size
Onset of Stall hydro-static thrust bearing a miniature jet pump optimization based
0:15
with low area ratio on Two-level multi-
point approximation
12:30 method
Aritras Roy and Rinku Pushpendra K Kushwaha, Vimal Kotak, Samiran Shuanjun Liu, Hai
Mukherjee Vivek Kumar, Vinay Vakharia Sengupta, Anil Huang, Shenyan
and Satish C. Sharma Pathrose, Sugilal Chen and Jiayi Fu
Gopalkrishnan and
Sujay Bhattacharya
Flow modifications & capacity Al/epoxy adhesion strength by a Numerical Connectivity
augmentation due to streamwise modified butt joint test Performance Studies Preserving Multi-
deployment of longitudinal configuration of a Small Scale Spacecraft
vortex generators in a finned Horizontal Axis Wind Formation Control 0:15
tube bank Turbine Blade with for Trajectory
Humpback Whale Tracking with
12:45 Tubercles Obstacle Avoidance
Amit Arora Madhusudhanan U and Rajesh Supreeth R, S K Zhongyuan Chen,
Kitey Maharana and Shitao Wang and
Bhaskar K Wanchun Chen
13:00 LUNCH BREAK 1:00

Venue SL1
Plenary Session -4: Recent Status and Development of Korea Military Airworthiness System
Prof. Changduk Kong, Chosun University, South Korea
0:45
Session Chair: Prof. B. N. Singh
14:00 Mr. Pabitra Maji
Venue SL1 SL3
Plenary Session -6: Shock-turbulence
interaction: analysis and modelling for
Plenary Session -5 : Avionics Architecture Solutions and aerospace application
Analysis for Helicopters Prof. Krishnendu Sinha, IIT Bombay, 0:45
Prof. Mahir Dursun, Gazi Universit, Turkey India
Session Chair: Prof. D. K. Maiti Session Chair: Prof. Somnath Ghosh
14:45 Mr. Umakant Meher Mr. Agneev Roy
Venue SL1 SL2 SL3 SL4
Session Chair: Prof. Somnath Session Chair: Prof. B. N. Session Chair: Prof. Session Chair:
Ghosh Singh C. S. Mistry Prof. N. K. Peyada
Mr. Agneev Roy Mr. Umakant Meher Mr. Ajey Singh Mr. Harinarayana

8
 Shock wave effects on Chitosan Comparative study of dampers Research on Thrust Optimization
bio-polymer for drug delivery on a G+26 storey building Measurement System Design of Modified
applications subjected to lateral loading Design and Intelligent Stewart Platforms
Thrust Prediction for Isotropic Force 0:15
Method Applied to Output
Micro-electric
15:30 Propulsion
Pranav H A and B Sudarshan Ritik Saxena, Divyansh Tewari, Haibo Wang, Guobiao Zijian Liu, Weipeng
Akshit Gupta and Dr M Abdul Cai, Chencong Fu, Li, Hai Huang and
Akbar Wei Liu and Weizong Bin Ren
Wang
Effect of oblique shocks Effect of graphene nanoplatelets PIC/MCC Simulation Performance
interaction on the inlet structure on the thermomechanical of Axial Ring-Cusp Analysis of
in a hypersonic flow behaviour of smart polymer Hybrid Discharge in Autonomous Flight
nanocomposites the Micro Ion Models Based on 0:15
Thruster Ionization Reinforcement
Chamber Learning for
15:45 Military UAV
Sanjay A V and B Sudarshan Nilesh Tiwari and A. A. Shaikh Wei Liu, Weizong Hyoju Nam, Haejin
Wang, Guobiao Cai, Kwon, Keunho
Shuwen Xue, Yifei Yun, Jia Kim and
Li, Haibo Wang and Kyutae Cho
Guangqing Xia
16:00 Break 0:15
Session Chair: Prof. Arnab Session Chair: Prof. D. K. Session Chair: Prof. Session Chair:
Roy Maiti C. S. Mistry Prof. N. K. Peyada
Mr. Ramakrishnan Mr. Umakant Meher Mr. Ajey Singh Mr. Harinarayana
Experimental study on two Effects of internal length scale Three-dimensional Agile Turn
octave Indian flute acoustics parameter on damage initiation PIC-MCC Analysis of Guidance Law
and evolution using gradient Ion Thruster Grid based on Deep 0:15
enhanced damage mechanics Misalignment Reinforcement
16:15 theory Learning
Praful K and Sudarshan B Aditya Deshpande and Bhrigu Yifei Li, Weizong Xiaopeng Gong,
Nath Singh Wang, Guobiao Cai, Yizhong Fang,
Chencong Fu, Wei Wanchun Chen and
Liu and Guangqing Zhongyuan Chen
Xia
Performance assessment of five Robust flutter analysis of a Numerical Capture Region of
probe flow analyser suitable for sweptback wing using μ method investigation of Realistic True
wind tunnel calibration discharge mechanism Proportional
and plasma behavior Navigation Based 0:15
in an external on Closed-form
discharge plasma Solutions
16:30 thruster
Akhila Rupesh A Arun Kumar and Amit Shuwen Xue, Xiangxiang Li,
Kumar Onkar Yuanyuan Gao, Wei Wanchun Chen,
Liu, Yifei Li, Guobiao Zhongyuan Chen
Cai and Weizong and Yizhong Fang
Wang
A Numerical Study on the Numerical Study of Tilted Aerothermal Understanding the
Negative Lift and Point of Non- Multi-Storied RCC Buildings Predictions of High- Strapon Separation
linearity in Lift Curve of NACA on Shallow Foundations Pressure Turbine Dynamics in 0:15
0012 Airfoil at Low Reynolds Considering Soil-Structure Flows Using RANS atmospheric phase
16:45 Number Interaction Methods
Gangadhar Venkata Ramana Devjit Acharjee, Srijani Pranjal Anand and Ayush Raikwar,
Pinapatruni, Sunil Manohar Bandyopadhyay and Debasish Rajesh Ranjan Vidya Gurumurthy
Dash, Jit Sinha and Kalyan Bandyopadhyay and Devendra Ghate
Prasad Sinhamahapatra
Experimental Prediction of A homogenized crystal RANS modeling for Study of Stability
Wind Flow and Pressure plasticity model for lamellar short and long Parameters for
Distributions Around a Low- transformed β colony of separation bubbles in Multi-Rotor Aircraft
Rise Building titanium alloys flow past low- using CFD Analysis 0:15
pressure turbine and Validation with
cascades Theoretical
17:00 Calculations
Venugopal Mm, S K Maharana S. Mustafa Kazim, Kartik Shruti Rajpara and Manoj S Naik,
and Mahantayya K Hiremath Prasad and Pritam Chakraborty Rajesh Ranjan Sumedha Y D,
Anish G P Nand,
Yeshas M N
9
 Bharadwaj and
Promio Charles F
Three dimensional Transient Low Velocity Impact Mode Transition in A Review of
computational investigation of Response of Functionally- Strut Based Parallel Predictive Control
the geometric design of delta- Graded Rectangular Plates – A Fuel Injection in for Autonomous 0:15
type vortex generators deployed Finite Element Approach. Scramjet Engine Flight Systems
17:15 in finned tube arrays
Amit Arora Ritwik Mandal, Tanmoy Rajesh Kumar, Mahir Dursun
Bandyopadhyay and Amit Pruthvi Narne and
Karmakar Amardip Ghosh
17:30

Venue SL1
Plenary Session -7: Numerical investigation of shock-turbulence interaction and shock-associated noise for
supersonic jets
Prof. Zhenxun Gao, Beihang University, Beijing, China 0:45
Session Chair: Prof. K. P. Sinhamahapatra
09:00 Ms. Gargi Das
Venue SL1 SL3
Plenary Session -9: Computational
Plenary Session -8: New opportunities and challenges for future Determination of Detonation Characteristics
UAVs of Condensed Explosives
0:45
Prof. Raktim Battacharya, TAMU, USA Prof. A. Kushari, IIT Kanpur, India
Session Chair: Prof. S. Saha Session Chair: Prof. R. Joarder
9:45 Mr. Hitesh Sharma Mr. Shva Prasad
21 December

Venue SL1 SL2 SL3 SL4

Session Chair: Prof. K. P. Session Chair: Prof. M. R. Session Chair: Prof. Session Chair:
Sinhamahapatra Sunny R. Joarder Prof. Anup Ghosh
Ms. Gargi Das Mr. Iqbal Ahmed Mr. Shva Prasad Mr. Raj Kumar
Experimental study of inflight Quadratic Wachspress Shape Mixing characteristics An aircraft wing
icing conditions on coefficient Functions for Polygonal Finite of circular and structural layout and
0:15
of pressure distribution around Element Method elliptical twin jets cross-sectional size
10:30 NACA0012 aerofoil optimization design
Ms. Swetha S, Dr. Sarat Kumar Shalvi Singh and Pritam Ch Narendra Kumar Hai Huang and Jiayi
Maharana, Dr. Abdul Sharief Chakraborty and K P Fu
and Ms. Steffi Thangachan Sinhamahapatra
An Improved Homotopy Effect of carbon black content A study on Analysis and
Perturbation Method to Study on quasi-static compression Applicability in Super control of
Damped Oscillators. behaviour of filled rubber Cavitation with Aeroelastic
SLBM performance of 0:15
delaminated
composite plate
10:45 using AFC
C F Sagar Zephania and Tapas Spandan Bandyopadhyaya, Kyungwon Oh and Jayant Prakash
Sil Rajesh Kitey and C.S. Changduk Kong Varun and
Upadhyay Prashanta K.
Mahato
Influence of tab blockage on Induction Heating of AEROACOUSTIC Finite element
asymmetric under- expanded Thermoplastic using Fe3O4 STUDY ON HVLS analysis of biaxial
sonic free jet FAN BLADE WITH cuboid voided slab 0:15
SERRATIONS under one way
11:00 bending load
Lavala Srinivasa Rao, Partha Inseok Baek and Seoksoon Lee Shashank H K, Rohith N Nareshnayak and
Mondal and Sudip Das J and B Sudarshan B N Rao
11:15 Break 0:15
Session Chair: Prof. Arnab Session Chair: Prof. M. R. Session Chair: Prof. Session Chair:
Roy Sunny Akshay Praksh Prof. Anup Ghosh
Mr. Narendra Kumar Mr. Aditya Deshpande Mr.Pranay Kumar Mr. Raj Kumar
Aerodynamics Analysis of Drop Test of an Aircraft Design of Propulsion Study on Multiscale
Fighter Aircraft in Formation Landing Gear Equipped with System for Propeller- Modelling Method
Flight MR Damper less UAV for Investigation on
0:15
Damage of Wind
Turbine Composite
11:30 Blade
Jaemuk Kim and Cheolheui Banghyun Jo, Jaihyuk Hwang Rohith J, Shashank H Haseung Lee,
Han and Daesung Jang K, Akshay S Prasad, Younggyu Lee,
10
 Dheeraj R and B Changduk Kong
Sudarshan and Hyunbum Park
Transverse-only VIV of a freely Unsteady Aerodynamic Force DESIGN AND Flutter Investigation
vibrating hybrid cylinder at low Approximation for Flutter PERFORMANCE of MW Sized
Reynolds number Prediction ANALYSIS OF Hybrid Composite
AXIAL FLOW Wind Turbine Blade 0:15
WIND TURBINE
FOR HOUSEHOLD
11:45 APPLICATIONS
Himalaya Sarkar, Pavan Kumar Promio Charles F and Dr. Venkatesu Sadu, Praveen Shakya and
Yadav and Subhankar Sen Vedavathi G A Dr. Pol Redy Kukutla, Umakanta Meher
Dr. Syamsundar C
and Dr. Sivaiah P
Aerodynamic Characterisation Parametric perturbation studies ICETACM2021- Wake Dynamics of
of a Re-entry Module in on the behaviour of bistable EXPERIMENTAL a Flexible Flapping
Supersonic Flow Regime unsymmetrical laminates STUDY OF FLOW Filament at Low
BEHAVIOURS OF Reynolds Number
FLY ASH SLURRY 0:15
WITH AND
WITHOUT
CHEMICAL
12:00 ADDITIVES
Devashish Bhalla, Vidya K. S. Suraj, P. M. Anilkumar, Priyanka Nimar, Chhote Lal Shah,
Gurumurthy and Manoj T. Nair C. G. Krishnanunni and B. N. Kanwarpal Singh and Dipanjan
Rao Arvind Kumar Majumdar, Chandan
Bose and Sunetra
Sarkar
Insight into the mechanism of Finite element modelling and Mechanical and New Response
drag reduction for a spiked Monte Carlo ray tracing for the microstructural Branch for
blunt body solar parabolic trough collector characterization of Undamped 2-DOF
with torque box Incoloy 901 repair by VIV of a Diamond 0:15
DED for aerospace Oscillator
gas turbine engine
12:15 parts
Md Gulam Sarwar, Priyank Natraj H, B. Nageswara Rao Jongkee Ahn, Kumar Sourav and
Kumar and Sudip Das and K. Srinivas Reddy Dongyeop Lee, Bohee Deepak Kumar
Kim, Chiwon Kim,
Hyun-Uk Hong and
Je-Hyun Lee
Turbulence model and grid Prediction of Mechanical Numerical Study on FOV-constrained
Sensitivity analyses of T-shape Properties for 3-D woven Transient Transverse 3D impact angle
tall building using composite considering realistic Jet Effect of the Two- and impact time
0:15
Computational Fluid Dynamics features Dimensional Slot control guidance
technique Under Supersonic
12:30 Conditions
Ajay Pratap and Neelam Rani Hiyeop Kim, Pyunghwa Kim, Song Xue, Tianyixing Peng Wang,
Yongun Jun and Jungsun Park Han and Chongwen Wanchun Chen and
Jiang Zhongyuan Chen
Numerical study of a square Vibroacoustic analysis of The Spray Experimental
plan shape building with corner simply supported and clamped Characteristics Of Verification of
modification functionally graded sandwich Pintle Injector Using Stiffness behavior
plates under transient loading Homogeneous of Multilayer Metal
0:15
Mixture Model And bellows
Eulerian To
Lagrangian
12:45 Transformation
Geetam Saha, Dibya Jyoti Basu, Avnish Pandey and K V Jeongseok Kang, Istiyak Khan, Nilesh
Aritro Roy Mitra and Dipesh Nagendra Gopal Younglin Yoo, Hong- Gohel, Samiran
Majumdar Gye Sung, Minchan Sengupta and Sujay
Kwon and Junyoung Bhattacharya
Heo
13:00 LUNCH BREAK 1:00

Venue SL1
Plenary Session -10: Compressive Failure Behaviors of Composites and Composite Sandwich Structures
Prof. Jia-Lin Tsai, National Yang Ming Chiao Tung University, Hsinchu, Taiwan
0:45
Session Chair: Prof. P. Jana
14:00 Mr. Nikhil Kumar

11
Venue SL1 SL3
Plenary Session -12: Accurate measurement
of laminar burning velocity of premixed
Plenary Session -11: Development Policy of Korea’s Space fuel-air mixtures
Science & Technology Prof. Sudarshan Kumar, IIT Bombay, 0:45
Dr. Chin-Young Hwang, KARI, South Korea India
Session Chair: Prof. Amardip Ghosh Session Chair: Prof. R. Joarder
14:45 Mr. Saisantosh Iyer Dr. Syam S
Venue SL1 SL2 SL3 SL4
Session Chair:
Session Chair: Prof. S. M. Session Chair: Prof. Prof. Anup Ghosh
Dash Session Chair: Prof. P. Jana R. Joarder Mr. Kamal Kishor
Mr. Prabir Sikdar Mr. Nikhil Kumar Dr. Syam S Prajapati
A detailed analysis of improved Structure analysis and Numerical Electro-mechanical
mathematical models of optimization of SSS-1 Investigation of Impedance response
secondary velocities along microsatellite Cavity Flow Field in of delaminated
0:15
perpendicular and transverse Presence of Store glass-fibre
directions for steady uniform composite beam
15:30 turbulent flow
Titas Chattopadhyay Yipeng Zhang, Hai Huang and Bhaskar K, Rakesh Umakanta Meher,
Shenyan Chen Kumar, Punit N. Praveen Shakya and
Gwalani, Anagha Mohammed Rabius
Mandayam Sunny
Bhulokam, Gargi S.
Pantoji and Aishvarya
D. Joshi
Simulating the impact of Effect of Hygrothermal Numerical Analysis Numerical Study of
ground vortex ingestion on inlet Environment on Dynamic of Weapon Bay the Effect of Shear
performance Behavior of Folded Laminated Cavities of Different Connectors in
0:15
Composite Plate Configurations Insulated Sandwich
Panel Building
15:45 System
Dr. Rajesh Kumar and Babu Ranjan Thakur, Surendra Bhaskar K., Rakesh Devjit Acharjee,
Pramodkumar Vanam Verma, Bhrigu Nath Singh and Kumar, Arjun R. Dibya Jyoti Basu
Dipak Kumar Maiti Prasad, Akshay M. and Debasish
M., Rahul Ithal H. L. Bandyopadhyay
and Siddalingana
Gowda M. P.
16:00 Break 0:15
Session Chair:
Session Chair: Prof. S. M. Session Chair: Prof. D. K. Session Chair: Prof. Prof. B. N. Singh
Dash Maiti Amardip Ghosh Mr. Smruti
Mr. Prabir Sikdar Mr. Aditya Deshpande Dr. Syam S Ranjan Sahoo
NUMERICAL STUDY OF Failure Mechanisms of SMA LES of shock- Based on Natural
MULTIPLE-IMPINGEMENT Reinforced Composites under turbulence interaction Frequencies, Crack
JET ARRAYS ON ISO- Impact Loading in a Bell-shaped Analysis of Fixed 0:15
THERMAL HORIZONTAL Convergent Divergent Support Fibre Glass
16:15 FLAT PLATE Nozzle. Composite Beam
Dr. Pol Reddy Kukutla, Dr. Vagish Mishra, Ashish Mishra, Agneev Roy and Vaibhav
Venkatesu Sadu, Dr. Luv Verma and Anindya Roy Somnath Ghosh Suryawanshi,
Syamsundar C, Dr. Maruthi Shailesh Palekar,
Prasad Yadav G and Dr.Sekhar Prasad Patare,
Babu P Prasad Bojage and
Atul Joshi
LES of compressible round jet A comparative study of recent The Effect of Mole Probabilistic Mixed
impinging on a flat isothermal phase-field implementations for Weight Ratio of Mode Stress
plate fracture prediction in solids Reaction on the Intensity Factors of
Propagation of Single Edge
Cellular Detonations Cracked Laminated 0:15
Composite Plates
Using Stochastic
Extended Finite
16:30 Element Method
Swagatika Pradhan and Sidharth Pc and B.N Rao Chun Wang Shailesh Palekar,
Somnath Ghosh Achchhe Lal,
Prasad Patare, Atul
Joshi and Prasad
Bojage
12
 Experimental Investigation of Third-Order Shear Deformation Heat Treatment of Dynamic response
Flow characteristics for Natural Theory for the Low-Velocity AISI 1045 Specimens control of adjacent
Circulation Valve Impact Response of 3D Braided using High-Frequency structures connected
0:15
Composite Plates and Simulation by viscous damper
using inerter-based
16:45 isolation systems
Nikhil Pandey, Samiran Pabitra Maji and Bhrigu Nath Jinkyu Choi and Sudip Chowdhury
Sengupta, Vijay K. Veluri, Singh Seoksoon Lee
Manoj Tilara and Sujay
Bhattacharya
Modelling and analysis of Measuring deformation in Numerical Analyses Modeling damage
winglet morphing for aerial lightweight structures with on Free-Play evolution of
vehicles revamped DIC system: wind Nonlinear laminated
0:15
tunnel study Aeroelasticity composites under
high strain rate
17:00 loading
Nandni Sharma, Gaurav Vivek Khare and Sudhir Kamle Guowei Yang, Bipin Kumar
Chhabra and Abha Gupta Chengde Huang and Chaurasia and
Guangnan Zheng Deepak Kumar
Study of evolving regular Low-Velocity Oblique Impact Effects of Column
water-waves under steady wind Response of Pre-twisted Orientation on
forcing Sandwich Conical Shell with Building Structure- 0:15
CNTRC Facings Verified Through
17:15 Pushover Analysis
Santosh Kumar Singh Tripuresh Deb Singha, Tanmoy Suchintya Halder
Bandyopadhyay and Amit and Abhishek Hazra
Karmakar
17:30

Venue SL1
Plenary Session -13: Prof. Estimation of Aerodynamic Derivatives from Flight Data
A. K. Ghosh, IIT Kanpur, india
0:45
Session Chair: Pro. N. K. Peyada
09:00 Mr. Saumitra Barman
Venue SL1
Plenary Session 14: Dr. K. S. Parikh, ISRO SAC, Ahmedabad, India
Session Chair: Prof. S. Bhattacharyya 0:45
9:45 Ms. Reshma G
Venue SL1 SL2 SL3 SL4
Session Chair: Prof. Session Chair:
Session Chair: Prof. M. R. K. P. sinhamahpatra Prof. B. N. Singh
Session Chair: Prof. S. Saha Sunny Mr. Narendra Mr. Smruti
Mr. Hitesh Sharma Mr. Iqbal Ahmed Kumar Ranjan Sahoo
22 December

A modified sharp interface Applicability of duffing Comparison of Full- Porous Scaffold by

immersed boundary method oscillator on the dynamic field Solution Additive
analysis of bistable variable between Virtual and Manufacturing for
0:15
stiffness laminates Experimental Digital Bone Replacement
Image Correlation for in Biomedical
10:30 Model Verification. Application
Bo Yin, Guowei Yang and K. S. Akhil, P. M. Anilkumar Vipin Chandra and Apurba Das,
Zhanzhou Hao and B. N. Rao Pritam Chakraborty Arghya Mondal,
Palash Mondal,
Masud Rana, Amit
Roy Chowdhury
and Amit Karmakar
Effects of jet flow on wake of Numerical Analysis of Experimental A Study on
high-speed train Structural Design Result for Investigation of Vibration
UAV applied to Composite Siphon breaker for Characteristics of
Structure considering on Self- Small Pipe breaks Cantilever Conical
0:15
Healing Method Shell Made of FG
Sandwich Material
with Porosity and
10:45 Thermal Effect
Guo Dilong, Liu Wen and Yang Hyunbum Park and Yonggyu Samiran Sengupta, Apurba Das,
Guowei Lee Vijay K. Veluri and Subhendu Pal,
Sujay Bhattacharya

13
 Korak Sarkar and
Amit Karmakar
A robust fifth-order WENO-Z Effects of vertical inclinations Design and analysis Application of finite
type scheme with improved of square prism on the of thermal control element direct
accuracy at second-order performance of piezoelectric system for SSS-1 integration method 0:15
critical point energy harvester: An satellite in flutter analysis
11:00 experimental study
Yiqing Shen, Shiyao Li and Ke Rakesha Chandra Dash, Dipak Shenyan Chen, Jie Huang, Guannan
Zhang Kumar Maiti and Bhrigu Nath Xingwang Yan and Zheng, Guowei
Singh Shuchong Wang Yang, Chengde
Huang and Yingjie
Yu
First-ply failure
load prediction of
pre-twisted
0:15
delaminated
composite conical
11:15 Break shells
Suman Karmakar,
Session Chair: Prof. Tripuresh Deb
Session Chair: Prof. Akshay S. Saha Singha, Tanmoy
Praksh Session Chair: Prof. P. Jana Ms. Swagatika Bandyopadhyay and
Mr. Sambhu Kumar Mr. Kamal Kishor Prajapati Pradhan Amit Karmakar
Study of influence of vortices Stochastic finite element A quasi-longitudinal
on trailing airfoil modelling of the graded cellular study of the effect of
arches hemodynamical
parameters on the 0:15
biomechanics of
rupture in Abdominal
11:30 Aortic Aneurysms
Bhaskar K, Mithil K, Pushkar Mohammad Amir, Mohammad Samarth S Bhatt,
Chaudhary, Sacheet S Talha, Sang-Woo Kim and Amritanshu Dixit,
Amblekar and Sachin Maruti Changduk Kong Ahmad Shaikh, Tejas
Shet Canchi and
Rangavittal Hk
Numerical analyses of re-entry Design and development of a Equilibration of Van
module - Apex cover separation piezoelectric XY micro- der Waals liquid drop
aerodynamics at low subsonic displacement scanning stage with vapour in 0:15
Mach number for various smoothed particle
11:45 angles of attack hydrodynamics
B Venkatshivaram Jadav, Babu Xiaoyan Zhang, Weipeng Li, P. C. Harisankar, C.
C and Vidya G Jie Liu and Shuo Yang F. Sagar Zephania and
Tapas Sil
Ensemble Machine Learning Damage Analysis of Multi- Design and
Methods for Unsteady layered Composite Structures verification of
Aerodynamics Modeling using electrical power
0:15
Flight Test Data subsystem for a
student small satellite
12:00 “SSS-1”
Ajit Kumar and Ajoy Kanti Kartikeswar Dwibedy and Anup Liu Bohan, Yu
Ghosh Ghosh Xudong and Huang
Hai
CFD Investigation of Sensor/actuator position Wall effect on the
Geometrical Truncation effect optimization for large size Drucker Prager model
of Typical Winged Re-entry structure using multi-objective parameters for pebble 0:15
Vehicle on Pressure Coefficient optimization beds in nuclear fusion
12:15 at FADS ports reactor
Kunal Garg, Jathaveda M, G Jianhongyu Li, Hai Huang and Deepak K Pawar,
Vidya, Babu C, Dr Patil M M Shenyan Chen Maulik Panchal,
and Dr Ashok V Paritosh Chaudhuri,
Ratna Kumar
Annabatuala and
Narasimhan
Swaminathan
Risk assessment of cerebral Static and free vibration Modeling and design
aneurysms using FSI analysis of functionally graded of hybrid reluctance
shells using non-polynomial actuator for fast 0:15
quasi 3D shear deformation steering mirror
12:30 theory

14
 Shine S R, Shantanu Saha, Sambhaji Lore, Aditya Weipan Zhang,
Harshavardhan E and Jayanand Deshpande and Bhrigu Nath Weipeng Li and Bin
Sudhir B Singh Ren
Stably electrospraying An analytical approach to sense Numerical simulation
Concentrated aqueous solution the presence of damage through of wind-driven rain on
with outer ionic liquid electro-mechanical impedance gabled roof buildings 0:15
(EMI) response for a step-lap
12:45 joint
Yufeng Cheng, Jinrui Zhang, Umakanta Meher and Chenhao Xu,
Guobiao Cai and Weizong Mohammed Rabius Sunny Chongwen Jiang,
Wang Siyuan Pi, Shuyao Hu
and Zhenxun Gao
13:00 LUNCH BREAK 1:00

Venue SL1
14:00 Joint Meeting Of Organisers 1:00

15:00 Closing Session of ICTACEM2021 1:00

16:00

Corresponding links for the technical sessions are embedded in the name of the sessions; namely SL1, SL2, SL3 and SL4.

15
BOOK OF ABSTRACTS

16
INVITED TALKS

17
Compressive Failure Behaviors of Composites and Composite Sandwich
Structures

Jia-Lin Tsai
Department of Mechanical Engineering, National Yang Ming Chiao Tung University, Hsinchu, Taiwan,
300

The compressive strength of unidirectional fiber composites is normally lower than the tensile strength.
In this talk, the compressive failure behaviors of unidirectional composites are characterized based on
the microbuckling model with the consideration of initial fiber misalignment. In addition, the
compressive failure tests of fiber composites are performed in terms of different testing techniques.
From the experimental data, it is indicated that the stress concentration occurring in the clamping area
can significantly lower the compressive strength of fiber composites. A design of testing method is
proposed to reduce the stress concentration resulting in the higher experimental data.
Composite sandwich structures are composed of highly stiff composite face sheets and a low density
foam core. The foam core is sandwiched between two face sheets, and the entire laminate is bonded
together by using an adhesive to form a sandwich structure. During the manufacturing process or
engineering application, a debond defect between the face sheet and foam core might be generated,
substantially deteriorating the performance of the sandwich structure. The second part of the talk will
focus on the failure behaviors of debond sandwich structures subjected to compressive loading.
Experiments and numerical simulations are conducted to understand the effects of the face sheet
thickness and debond length on the compressive strength and failure mechanisms of the composite
sandwich structures. It is revealed that, when the dominant failure mode is global buckling, failure
occurs at the intermediate portion of the foam core and strength could be characterized using the
maximum principal strain criterion. However, when the failure mode is local buckling, failure is initiated
at the debond tip, and strength could be predicted using the damage zone method.

18
 New opportunities and challenges for future UAVs

Raktim Bhattacharya
Professor, Director, Intelligent Systems Research Laboratory
Aerospace Engineering, Electrical & Computer Engineering, Texas A&M University
Email: isrlab.github.io

Abstract:
Unmanned aerial vehicles are seeing an explosive growth in several domains, mostly in the commercial
sector. Applications include real-estate, journalism, wild life conservation, precision agriculture,
delivery, internet access, infrastructure assessment, etc. Each application has key requirements, which
must be met in the design of these vehicles. A key design challenge is ensuring design flexibility,
extensibility, and reconfigurability – while guaranteeing low cost, resource efficiency, reliability, and
robustness. In this talk, some of the challenges in the air vehicle design for these applications will be
presented, including aerodynamics, structures and flight control.

19
 Spray-Swirl Interactions: Some Insights

Saptarshi Basu
Professor, Mechanical Engineering Department, IISc Bangalore

Coupling of spray with the coherent structures of a highly turbulent flow has been a long-standing
problem especially in the context of liquid fuel delivery systems in gas turbine combustors. The atomizer
in a gas turbine combustor usually has one or more (radial/axial entry) air swirlers with a fuel nozzle
being mounted centrally along the longitudinal axis of swirler. It is well known that swirling flows are
highly three dimensional in nature and often induce multiple aerodynamically unstable modes whose
frequencies are several orders of magnitude. The basic understanding of flow dynamics in gas turbine
swirl cup is critical to achieving clean and efficient combustion in modern-day gas turbine
combustors. In this work, we analyze the evolution of the hydrodynamic topology and consequent
spray-flow interactions in a coaxial swirl injector assembly.
The key results of the present work are discussed in four parts. In the first part, the global evolution and
temporal dynamics of various vortex breakdown modes are discussed. Experiments are carried out for
three sets of co annular flow Reynolds number. Furthermore, for each condition, swirl number is varied
independently from. Three distinct forms of vortex breakdown namely, pre-vortex breakdown (PVB),
central toroidal recirculation zone (CTRZ; axisymmetric toroidal bubble type breakdown) and sudden
conical breakdown are explored in greater details. Energy ranked, and frequency resolved / ranked
robust structure identification methods – POD, DMD respectively is implemented over instantaneous
time resolved PIV data sets to extract the dynamics of coherent structures associated with each vortex
breakdown modes. The dominant structures obtained from POD analysis suggest the dominance of KH
instability (axial + azimuthal; accounts ~ 80 % of total TKE) for both PVB and CTRZ while the
remaining energy is contributed by shedding modes. On the other hand, shedding modes contribute to
the majority of the TKE in conical breakdown. The frequency signatures quantified from POD temporal
modes and DMD analysis reveals the occurrence of multiple dominant frequencies in the range of ~ 10
– 400 Hz with conical breakdown. This phenomenon may be a manifestation of high energy contribution
by shedding eddies in the shear layer. Contrarily, with PVB and CTRZ, the dominant frequencies are
observed in the range of ~ 20 – 40 Hz only. In addition, the current work explores the hysteresis (path
dependence) phenomena of conical breakdown as functions of Reynolds and Rossby numbers. It has
been observed that the conical mode is not reversible and highly dependent on the initial conditions.
In the second part, we have reported how the liquid sheet behaves in such swirling flows. The air flow
rate across the swirler is progressively varied to probe the two-phase flow interaction dynamics across
weak, transition and strong momentum coupling regimes. The liquid sheet breakup and gas – liquid
phase interaction dynamics suggests strong one way coupling at higher MR values. The POD analysis
implemented over the shadow images clearly delineates the superimposing of gas phase instabilities
with liquid sheet. The breakup length scale and liquid sheet oscillations are meticulously analyzed in
time domain to reveal the breakup dynamics of liquid sheet. Furthermore, the large-scale coherent
20
structures of swirl flow exhibit different sheet breakup phenomena in spatial domain. For instance,
flapping breakup is induced by counter rotating vortices in the flow field induced by vortex breakdown
phenomenon. The breakup regime map is also constructed based to illustrate the various forms of
breakup mechanism as a function of MR values. Finally, the ligament formation mechanism and its
diameter, size of first-generation droplets are measured with phase Doppler interferometry (PDI). The
measured sizes scale reasonably with KH waves.
In the third part, the fundamental mechanisms of vortex-droplet interactions leading to flow distortion,
droplet dispersion and breakup in a complex swirling gas flow field are discussed. In particular, how the
location of droplet injection determines the degree of inhomogeneous dispersion and breakup modes
have been elucidated in detail. The droplets are injected as monodispersed streams at various spatial
locations like the vortex breakdown bubble and shear layers (inner and outer) exhibited by the swirling
flow. Time-resolved particle image velocimetry (3500 frames/s) and high-speedshadowgraphy
measurements are employed to delineate the two-phase interaction dynamics. These measurements have
been used to evaluate the fluctuations in instantaneous circulation strength caused by the flow field
eddies and resultant angular dispersion in the droplet trajectories . The droplet-flow interactions show
two-way coupling at low momentum ratios (MR) and strong one way coupling at high momentum ratios.
The gas phase flow field is globally altered at low air flow rates (low MR) due to the impact of droplets
with the vortex core. The flow perturbation is found to be minimal and mainly local at high air flow
rates (high MR). Spectral coherence analysis is carried out to understand the correlation between eddy
circulation strength and droplet dispersion . Droplet dispersion shows strong coherence with the flow
at certain frequency bands. Subsequently, proper orthogonal decomposition (POD) is implemented to
elucidate the governing instability mechanism and frequency signatures associated with turbulent
coherent structures. POD results suggest the dominance of KH instability mode (axial and azimuthal
shear). The frequency range pertaining to high coherence between dispersion and circulation shows
good agreement with KH instability quantified from POD analysis. The droplets injected at inner (ISL)
and outer shear layer (OSL) show different interaction dynamics. For instance, droplet dispersion at
OSL exhibits secondary frequency (shedding mode) coupling in addition to KH mode, whereas, ISL
injection couples only at a single narrow frequency band (i.e. KH mode).

21
 Fundamental features of perturbation growth in high-speed
compressible shear flows

Sharath S. Girimaji1 & Bajrang Sharma2

1
Aerospace Engineering Department, 2Ocean Engineering Department Texas A&M University

Abstract: High-speed shear flows are of much interest in a variety of engineering applications. The
stability, transition and turbulence characteristics of these compressible shear flows exhibit some
profound differences from those in incompressible flows. These differences arise from flow-
thermodynamic interactions enabled by the change in the nature of pressure. Ultimately this change
leads to the emergence of dilatational velocity fluctuations in high speed flows. In this talk, I will discuss
the effect of dilatational fluctuations and internal-kinetic energy interactions on the development of
perturbations in simple shear flows and canonical wall-bounded flows. The study clearly shows that the
fundamental dilatational mechanisms are qualitatively identical in a range of shear flows. The findings
are expected to aid in developing physics-based closure models and identify the appropriate features for
data-driven turbulence models.

22
 Status and Development of Korea Military Airworthiness

Changduk Kong
Chosun University, 309 Pilmundaero, Dong-gu, Gwangju, 61452, Republic of Korea

1. INTRODUCTION & OBJECTIVES

Each country has enacted Airworthiness Certification based on the ICAO regulations established in
1944. (ICAO Annex 8 “Airworthiness of Aircraft”) According to US civil regulation of 14 CFR
Aeronautics and Space-Part 3, ‘airworthy’ means the aircraft conforms its type design and is in a
condition for safe operation, while according to MILHDBK-516B Airworthiness Certification Criteria,
‘airworthiness’ means the property of particular system configuration to safely attain, sustain, and
terminate flight in accordance with the approved usage and limits.. The civil aviation airworthiness
authorities of each country are as follows; US has FAA(Federal Aviation Administration), Europe has
EASA(European Aviation Safety Agency), and Korea has Airworthiness Division of MOLIT(Ministry
of Land, Infrastructure and Transportation). While military airworthiness authorities are as follows; US
has Air Force, Army and Navy, EU has European Defense Agency, and Korea has Airworthiness
Planning Division of DAPA. Civil Airworthiness Standards of each country are KAS(Korea
Airworthiness Standard) of MOLIT, CS(Certification Code of Specification) of EASA and FAR(or
CFR) Part of FAA for airworthiness process, aircraft, engine, propeller, noise, fuel and exhaust gas.
Because KAS and CS have been made based on FAR (or CFR), they are almost same as FAR. There
are several types of certification such as TC(Type Certification), PC(Production Certification),
AC(Airworthiness Certification), STC(Supplement TC), TSOA(Technical Standard Order Approval),
and PMA (Parts Manufacturer Approval). In case of military airworthiness standards, Korea and US
follow DoD MIL-HDBK_516C, and EU follows civil airworthiness standards, CS of EASA. This study
is to make common application between Korea military airworthiness system and international military
airworthiness system as well as to improve Korea military airworthiness system.
2. MILITARY AIRWORTHINESS SYSTEMS
Recently, more and more countries around the world require the airworthiness certification to ensure
flight safety of military aircraft. Airworthiness certification regulation and process of military aircrafts
differ from country to country. For instance, US is carrying out politics and regulations on airworthiness
certification activities by Air Force, Army and Navy, and European Defense Agency is using the
modified civil airworthiness process. In Korea, DAPA (Defense Acquisition Program Administration)
is performing airworthiness certification as a military airworthiness authority by law. Korea military
airworthiness system is composed of Act, Criteria, Organization and Process. The “Act on military
aircraft flight safety certification (Act No.11690)” was legislated in 2009 for Korean military, police
and other custom aircrafts including exporting A/Cs. The Korea military airworthiness authority is APD
(Airworthiness Planning Division) of DAPB (Defense Industry Promotion Bureau), and Standard
Airworthiness Certification Criteria was legislated based on US DoD MIL-HDBK_516B Change 1
“Airworthiness Certificate Criteria”, later updated by MILHDBK_516C. Process Regulation on military
airworthiness certification is stated at DAPA regulation No. 342 -4th revision. Since the licensed
23
production of military aircrafts such as F-5, MD-500, F-16, UH-60, F-15K, etc. and development of
military aircrafts such as KT-1, T-50, KUH, KC-100, LAH and F-21, Korea aerospace industries
including KAI, Hanwha Aerospace and KAL have got military aircraft development capability. These
developed military aircrafts received type certificates and airworthiness certificates by Korea military
airworthiness system and civil airworthiness system.

3. CONCLUSION

Recently, since the military airworthiness has been required in global military aircraft market, Korea
enforced the “Act on Military Aircraft Flight Safety Certification (Act No.11690)’. Therefore the
military airworthiness has taken charge of an important role not only for domestic delivery and sale of
developed military aircrafts but also for export and purchase of military aircrafts. If continuous study
on European and US advanced airworthiness systems and development of the effective military
airworthiness system by application and improvement, it is expected the Korea military aircraft industry
will be promoted more rapidly and effectively.

REFERENCES
1. C. Kong, Keynote Lecture “A Proposal for Korea Military Airworthiness Certification System Development,” 2016
International Military Airworthiness certification Conference, Seoul Plaza, DAPA, May 30, 2016.
2. H. Youn et al, “Practice of Airworthiness Certification”, pp. 21~68, Joendang, 2014.
3. DoD MIL-HDBK_516B -4h revision, -516C.
4. ICAO Annex 8 “Airworthiness of Aircraft”
5. Act on military aircraft flight safety certification (Act No.11690), 2009

24
 Development Policy of Korea’s Space Science & Technology

Dr. Chi-Young Hwang

Korea Aerospace Research Institute, South Korea

Abstract. Korea has began to participate in the space sector in the late 1980s. Initially, it began with the
scientific interest and aspiration of researchers, but with the establishment of the Korea Aerospace
Research Institute in 1989, and the establishment of a basic mid- to long-term space development plan
in 1996, the government-level development began. Along with the progress of space development, legal
and institutional systems were established. The Space Development Promotion Act was enacted in 2005
to establish the National Space Commission headed by the Minister of Science and Technology. Korea's
space development has been developed around the demand of civil public sectors such as scientific
experiments, earth observation, weather forecasting, environmental and ocean monitoring, and it is
gradually expanding to astronaut projects, lunar probes, and national security. KSLV-2 was launched in
2021 following the KSLV-1 launch in 2013 as the national demand for increased domestic satellite
launch. Along with the progress of space development programs, the investment of space development
of national resources is increasing and the chairman of the National Space Commission upgraded to the
prime minister this year. Currently, Korea is establishing the 4th Basic Plan for Space Development
Promotion with the goal of 2022. In this presentation, I would like to introduce the main contents of the
Korean space development system, the ongoing projects, and the basic plan for the promotion of national
space development.

25
 Thermal control system design and test for APSCO SSS-1 satellite

Chen Shenyan
Associate Professor, School of Astronautics, Beihang University, Beijing, China

Asia-Pacific Space Cooperation Organization (APSCO) Student Small Satellite (SSS) project is aimed
to train the students and faculties from Member States (MSs) of APSCO to study space technology and
satellite engineering through practical design of satellites until its launch. SSS-1 is the main satellite
with 36kg. According to the orbital environment, the external heat flow of SSS-1 was calculated by
considering the direct sunlight, the earth reflection and the earth infrared radiation. The thermal control
strategy was proposed by combining the passive and active thermal control techniques. The finite
element model for thermal analysis was established according to the primal design. The extreme cold
and hot conditions were applied as the typical load cases. The thermal analysis results showed that the
temperature of most payloads satisfy the design requirements whether in the transient or steady state. In
order to verify the thermal control effect of SSS-1, the ground vacuum thermal balance test of the
satellite was carried out, and the satellite temperature distribution under various conditions was obtained.
The test results showed that the temperature of most payloads can meet the design requirements, while
the on-board power area is higher than expected. Finally, the test results are compared with the analysis
results, and the thermal property parameters of the FE model were adjusted. And the thermal control
design was updated according to the test and analysis results. The SSS-1 has been launched by CZ-2D
rocket at Oct.14, 2021. The TT&C data showed that the temperature is kept at a proper region.

26
 Computational Determination of Detonation Characteristics of Condensed
Explosives

Abhijit Kushari
Professor, Aerospace Engineering Department, IIT Kanpur

Abstract. Defence research labs at present are working in the area of pressable polymer bonded
explosives (PBX) compositions which have applications is strategic systems. In order to meet the
requirement of strengthen blast waves for deep earth penetrator, concrete piercing warhead are being
developed. The ingredients in these PBX compositions need to be tailored in such a way that the
detonation products from these compositions react with air as well. This can be ensured by the addition
of metal powders in the compounds. However, the addition of metal powder in these compositions make
them non-ideal explosives for which the characteristics of the detonation waves are not available in
literature. It is not possible to ascertain the impact and short-select the desired composition by repeated
experimentation. Furthermore, the standard tools like NASA-CEA or ANSYS etc. do not have the
desired properties for such explosives in their databases. Therefore, a theoretical model is developed in
order to understand the thermochemical properties, CJ characteristics and equation of state for these
metal infused explosives. The methods used for the development of this general-purpose computational
method is discussed in the present talk and the results are compared with the literature data.

27
 Numerical investigation of shock-turbulence interaction and shock-
associated noise for supersonic jets

Zhenxun Gao
National Laboratory for Computational Fluid Dynamics, School of Aeronautic Science &
Engineering, Beihang University, Beijing, China, 100191

Supersonic jet noise is a key component of the aerodynamic noise on aerospace vehicles. This paper
focuses on the shock-associated noise for supersonic jets, and the numerical investigation is carried out
to study the shock-turbulence interaction and the associated noise. Firstly, Direct Numerical Simulation
(DNS) is applied to perform simulations for the turbulent mixing layer and shock/turbulent mixing layer.
The results are compared to analyze the influence of shock/turbulent mixing layer interaction (STMLI)
on the turbulence characteristics. Meanwhile, two mechanisms for generating shock-associated noise
are identified by applying the shock-leakage theory and the turbulence scale analysis. Secondly, Large
Eddy Simulation (LES) is used to simulate the axisymmetric non-ideally expanded supersonic jet, and
the FW-H equation is applied to calculate the far-field noise. Based on the simulation data, the shock
leakage presented earlier is discussed.

28
Accurate measurement of laminar burning velocity of premixed fuel-air
mixtures

Sudarshan Kumar
Department of Aerospace Engineering, Indian Institute of Technology Bombay Powai Mumbai
400076 India

Abstract. In this talk, the importance of accurate measurement of laminar burning velocity of premixed
fuel-air mixtures and its application for validating various detailed reaction models will be discussed.
The development and application of externally heated diverging channel method will be presented for
laminar burning velocity measurements at high pressure and high temperature conditions to understand
and evaluate the combined effect of pressure and temperature on the propagation of premixed fuel-air
flames. The experimental measurements of methane-air mixtures for different equivalence ratios are
reported for a pressure range (1-5 atm), and elevated temperatures of 350 – 650 K. Predictions from
three widely used detailed kinetic models (GRI-Mech 3.0, Aramco 2, FFCM-1) are employed to
compare with present measurements. The variation of pressure exponent, β, follows a bell-shaped curve
with maximum value for slightly rich mixtures (ϕ = 1.1) and a peculiar non-linear behaviour for very
rich mixtures (ϕ ≥ 1.3). Based on the detailed analysis of experimental results, the temperature exponent
(α) is proposed as a function of pressure, and pressure exponent (β) as a function of temperature at
various equivalence ratios. A modified power law correlation considering the  and β variations is
proposed as: 

Analysis of the flame structure at high-pressure conditions indicates that the reaction layer thickness is
reduced with an increase in pressure. A decrease in mixture thermal diffusivity with pressure contributes
to a reduction in laminar burning velocity at elevated pressures.

29
 Estimation of Aerodynamic Derivative from Flight Data

Prof. A.K. Ghosh

Department of Aerospace Engineering, I.I.T. Kanpur

Abstract. The estimation of aerodynamic derivative through flight data is of paramount importance in
characterizing aerodynamic model for performance, stability and control analysis. The application of
conventional and un-conventional method has been presented. The challenge of generating flight data
using scaled model is also addressed and shared.

30
 Shock-turbulence interaction: analysis and modelling for aerospace
application

Krishnendu Sinha
Professor, Aerospace Engineering Department, IIT Bombay

Abstract. Shock waves and turbulence together make an interesting area of

research. Shock waves can result in extremely high pressure and
temperature in hypersonic flows. This translates to high aerodynamic and
thermal loads on an aircraft. A shock wave can also enhance the mixing
in turbulent flows, which is beneficial in combustion applications. The
interaction of shock waves and turbulence in high-speed flows is thus a
problem of fundamental interest, as well as practical importance.
The canonical problem of homogeneous isotropic turbulence passing
through a normal shock wave is possibly the simplest and the most
fundamental problem. It brings out many key aspects of shock-turbulence
interaction, and is studied using direct numerical simulation and linear
interaction analysis. Of particular interest are the amplification of
turbulent kinetic energy and turbulent heat flux at a shock wave.
Physical insights obtained from DNS and theoretical analysis are used to
develop advanced turbulence models for CFD simulation. Application to
shock-boundary layer interaction flows show marked improvement in
predicting flow separation and peak surface heat transfer rates. The new
turbulence models have also been applied to real-life configurations in
aerospace vehicles.

31
CONTRIBUTED PAPERS

32
 Effects of internal length scale parameter on damage initiation and
evolution using gradient enhanced damage mechanics theory

Aditya Deshpande1, Bhrigu Nath Singh2

1
Research Scholar, Department of Aerospace Engineering, Indian Institute of Technology Kharagpur,
INDIA,
2
Professor, Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, INDIA
Email: adityadeshpande17@gmail.com

Abstract. Continuum based smeared crack and damage modelling methods have been proven
advantageous in solving various damage problems. Due to evident strain localization and loss of well-
posedness of the problem near failure loads, local continuum damage mechanics formulation shows
high mesh sensitivity. To rectify these issues, gradient enhanced damage theory, incorporating internal
length scale into the formulation as a method of regularization, is adopted. Present research work
discusses the relative effects of internal length scale on the damage initiation and evolution response of
the material. Gradient enhanced damage mechanics formulation is solved using non-linear finite element
method. Effects of internal length scale on total dissipated damage energy and damage localization
regions are presented. It is observed that, increasing length scale parameter tends to make the damage
response of material less brittle as the damage localizes in larger region.

33
 Mechanical and microstructural characterization of Incoloy 901 repair
by DED for aerospace gas turbine engine parts

Jongkee Ahn1, Dongyeop Lee2, Bohee Kim3, Chiwon Kim4, Hyun-Uk Hong5
and Je-Hyun Lee6
1,2,3
Hanwah Aerospace, Aerospace R&D Center, Seongnam-si, South Korea
4,5,6
Changwon National University, Department of Materials Convergence and System Engineering,
Changwon-si, South Korea
Email: jongkee.ahn@hanwha.com
Abstract. The additive manufacturing (AM) techniques is suitable for aerospace industry because of
higher performance and flexible manufacturing. AM technique is used for producing new parts or
repairing used parts. In this study, the performance of direct electron deposition (DED) repair part of
Incoloy 901 applied to aerospace gas turbine engine parts have been examined. The Incoloy 901 coupons
were prepared by DED, and the mechanical properties such as tensile and fatigue behavior were
characterized. The measured properties were compared with that of the tungsten inert gas (TIG) welded
coupons. Furthermore, the microstructure analyses were also conducted by Scanning Electron
Microscopy (SEM) and Transmission Electron Microscopy (TEM). The DED coupons showed a higher
mechanical properties compared to TIG coupons. The metallurgical properties such as volume fraction
of γ’ and area of heat affected zone were also analyzed. The results indicated that the microstructural
properties could have contributed to the difference in mechanical properties between DED and TIG
process.

34
Numerical Analysis of Weapon Bay Cavities of Different Configurations

Bhaskar K1, Rakesh Kumar2, Arjun R. Prasad3, Akshay M. M.4, Rahul Ithal H. L.5,
Siddalingana Gowda M. P.6
1,3,4,5,6
Aerospace Engineering, R V College of Engineering, Bengaluru, Karnataka,India
2
Aeronautical Development Establishment, DRDO, Bengaluru, Karnataka, India

Abstract. Weapon bays play a crucial role in providing better aerodynamic performance and stealth of
an aircraft. This can be analysed effectively by thorough understanding of the flow field within the
cavity. The present study aims at analysing the effect of leading-edge profile on the cavity flow. A basic
understanding of the effect of leading surface indicates that a straight leading surface leads to a stronger
primary vortex, whereas a wavy leading surface profile can mitigate the effect due to complex
interactions within the cavity. An attempt to quantify this effect is made by considering two variants of
saw-toothed profile, provided at both leading and trailing edges. Two wavelengths for the saw-tooth,
which is a function of width of the cavity, are considered, where the cavities have a length-to-depth ratio
of 5 and a width-to-depth ratio of 1. They are subjected to a free stream velocity of 70m/s with variation
in yaw angle from 0 - 6 degrees. Numerical approach is made to characterize the static pressure field
through high fidelity simulations using ANSYS® Fluent. The results obtained for both the cavities are
then compared with plain rectangular cavity to understand the effect of saw-tooth profiles on the flow
field.

35
 Aeroacoustic Study on Hvls Fan Blade with Serrations

Shashank H K1, Rohith J2 and B Sudarshan3

1,2,3
Department of Mechanical Engineering, B.M.S. College of Engineering, Bangalore, India-560019

Abstract. Owls are able to fly noiselessly due to their wing feathers by alleviating the noise generated
by the air flow effectively. The presence of serrations and fringes on its feathers plays a prime role in
reducing the noise and also in improving the aerodynamic performance. However, implying such design
is not abundant in the application arena applied to high-volume low-speed (HVLS) fan blades which
generate a significant amount of noise due to the impeller rotation of. The current study is aimed at
creating an array of serrations on the leading edge and trailing edge of the airfoil (NACA7415) similar
to that of the owl’s wing feather. The Aero-acoustic features are simulated using the ANSYS Fluent
software and the effect is studied with reference to the baseline airfoil geometry. The preliminary results
indicate that the serrations are effective in reducing the noise and improving overall aerodynamic
performance.

36
 Structure analysis and optimization of SSS-1 microsatellite

Yipeng Zhang1, Hai Huang2, Shenyan Chen3

1,2,3
Beihang University, School of Astronautics, Key Laboratory of Spacecraft Design Optimization
and Dynamic Simulation,102200 Beijing, China
Email: : zhangyipeng@buaa.edu.cn

Abstract. Abstract. SSS-1 is a 30kg micro-satellite mainly developed by Beihang University. In the
present work, the structure of the SSS-1 microsatellite was analyzed and optimized. According to the
overall requirements, the SSS-1 satellite adopts a frame-box-plate initial structure design scheme. To
study the mechanical properties of the structure and judge the feasibility of the initial design, a finite
element model of the SSS-1 satellite is established based on the geometry and mass characteristics of
the on-board payloads. Static and dynamic analysis are carried out. The calculation results show that the
second layer of the satellite has a local mode, and the first order frequency is low. Topology optimization
and size optimization were implemented. Combining with the optimization results and the practical
situation, the first and second layers of the satellite frame were reinforced. The structural analysis results
show that the first-order frequency of the improved design is increased from 34.622Hz to 86.45Hz.
Meanwhile, the weight of the entire satellite is reduced 1.13kg. And all the design requirements are still
satisfied.

37
 Characteristics Of Pintle Injector Using Homogeneous Mixture Model
and Eulerian to Lagrangian Transformation

Jeongseok Kang1, Younglin Yoo2, Hong-Gye Sung3, Minchan Kwon4

and Junyoung Heo5
1,2
Korea Aerospace University, Department of Aerospace Engineering, 76, Hanggongdaehak-ro,
Korea 3Korea Aerospace University, School of Aerospace and Mechanical Engineering/Smart Air
Mobility Engineering, 76, Hanggongdaehak-ro, Korea
4,5
Agency for Defense Development, The 1st R&D Institute, Yuseong, Korea

Abstract. Numerical analysis is conducted to investigate the spray characteristics of a hydrogen

peroxide/kerosene liquid pintle thruster. Three different rectangular shape injectors which are follow-
directionally long, square, and flow-vertically long injectors, are considered. A homogeneous mixture
model is applied to precisely compute the first breakup of liquid fuel column and then the Eulerian-To-
Lagrangian transformation method simulates the second break up and tracks the droplet after the
secondary breakup for computational efficiency.

38
 Free Vibration Analysis of a Rotor-bearing System having Corrosion
Defect

Bharath Obalareddy1, Aneesh Batchu2 and Prabhakar Sathujoda3

1,2,3
Department of Mechanical and Aerospace Engineering, Bennett University, Greater Noida, India
Email: prabhakar.sathojoda@bennett.edu.in

Abstract. The corrosion, a common surface phenomenon, occurs due to harsh environmental conditions
of the material resulting in the loss of material surface and change in the vibration behaviour and
structural integrity of the material. In the present work, a Timoshenko beam theory based finite element
formulation has been developed for the Jeffcott rotor-bearing system having corrosion defect to obtain
the natural and whirl frequencies of the system. The length, depth and position of the corrosion defect
have been varied to investigate the effect of corrosion defect on natural and whirl frequencies of the
rotor-bearing system. It has been concluded from the analysis that the effect of reduction in stiffness due
to corrosion defect is low near the bearings and high near the disk compared to the loss of mass. Hence,
as the length and depth of corrosion defect increases, the natural and whirl frequencies increase due to
the corrosion defect near the bearings and decrease as the position of the corrosion defect moves away
from the bearings towards disk.

39
 Numerical Analyses on Free-Play Nonlinear Aeroelasticity

Guowei Yang1, Chengde Huang2, and Guangnan Zheng3

1
LMFS, Institute of Mechanics, CAS, 100190, Beijing, China
2,3
School of Engineering Sciences, University of Chinese Academy of Sciences, Beijing, China
Email: gwyang@imech.ac.cn

Abstract. This paper proposes a framework of computational fluid dynamics/computational structural

dynamics (CFD/CSD) coupling approach that can deal with the three dimensional aeroelastic problems
with both the free-play nonlinearity and the aerodynamic nonlinearity. The fictitious mass method is
used to construct the reduced structural equations of motion and the switching point is detected using
the bisection method. The adaptive time step obtained by the bisection method is returned to the CFD
solver so that both the structural and the fluid equations are integrated using the same time step. An all-
movable wing with free-play at the root is considered for numerical studies. Results demonstrate the
CFD/CSD coupling method can predict the stable limit cycle oscillation (LCO) effectively. The initial
condition shows that the LCO behavior is subcritical and the hysteresis response can be predicted in
time domain effectively by the presented method. The viscous effect is shown to increase the LCO
boundary and shift the LCO amplitude to a larger velocity in transonic regime.

40
 Enhancement of Heat Transfer Cooling a Central Processing Unit
(CPU) System with Nanofluids

Brinda N1, Prem Raj2, Amod Yadav3, Getce Marcina A4 and Somashekar V5
1,2,3,4,5
Undergraduate Students, Department of Aeronautical Engineering, Acharya Institute of
Technology, Bengaluru Karnataka - 560107, India

Abstract. Theoretical studies were performed to investigate the effect of nanofluids, which are different
types of coolant fluids, being used in a CPU cooling system on heat transfer and fluid flow. The
Reynolds number study encompasses a range of 5000 to 15,000. Twenty different types of base fluids
with Al2O3 nanoparticle having a diameter of 20nm and concentration factor 4% have been used.
Nusselt number increased as the Reynolds number increased in the presence of different base fluids as
a coolant fluid. As the Reynolds number increased, skin friction increased with regard to the fluid used
as a coolant. The SiO2 nanofluid has the highest Nusselt number value and skin friction coefficient. It
was observed that the selected base liquid has the lowest Nusselt number and skin friction coefficient.
The local Nusselt number considerably increased with increasing Reynolds number and local skin
friction coefficient considerably increased with increasing Reynolds number.

41
Optimization Design of Modified Stewart Platforms for Isotropic Force
Output

Zijian Liu1, Weipeng Li2, Hai Huang3, Bin Ren4

1,2,3
School of Astronautics, BEIHANG University, Beijing 100191, PR China
4
China Academy of Space Technology, Xian 710100, PR, China
Email: liweipeng@buaa.edu.cn

Abstract. The output capabilities of the Stewart platforms rely on their configuration to a large extent.
Compared with standard Stewart Platforms, modified Stewart platforms (MSPs) will be achieved a more
balanced force output capability. The concept of isotropic force output of Stewart platforms is studied
to get a uniform force output, and configuration optimization design of the MSP is carried out to realize
the isotropic force output. Firstly, the configuration of the MSP is described and the parameters range
of the MSP's configuration is deduced according to the definition of isotropic force output. Then, the
optimization model of the MSP's configuration is established. The objective function that demonstrates
the difference between the force output in different axes is presented. Four independent parameters of
the MSP's configuration are taken as design variables. The Generalized Pattern Search method (GPSm)
is applied in the optimization and an optimized MSP that achieves isotropic force output was obtained.
Finally, the dynamic model of the optimized MSP was established, and dynamic simulation shows the
maximum force output in different axes is uniform, which verifies the optimization result of the MSP.

42
 Mixing characteristics of circular and elliptical twin jets

Ch Narendra Kumar1 and K P Sinhamahapatra2

1,2
Department of Aerospace Engineering, IIT, Kharagpur, West Bengal-721302, India, and
Email: chnarendrakumar06@gmail.com, kalyanps@iitkgp.ac.in

Abstract. In this paper, the effects of orientation and spacing to distance (S/D) on mixing properties of
twin circular and elliptical jets are investigated numerically. Here, D is the exit diameter of the circular
nozzle that is kept constant, and S is the spacing distance provided between the twin jets. The elliptical
twin free jet is studied in two orientations, either oriented along the major axis plane (Twin major) or
oriented along the minor plane (Twin minor). The numerical simulations of twin jets are carried using
the Reynold Averaged Navier Stokes (RANS) method of Shear Stress Transport (SST) K-ω turbulence
model. The results show that near the nozzle exit, the twin jets are isolated to each other and act as a
free jet, leading to a potential core length independent of spacing distance and similar to that of a free
single round jet. The results also show that jet mixing is superior for twin minor elliptical configuration
as compared to twin circle and twin major jets. In the radial direction as the jet progresses downstream
the twin major and twin minor jets experience a shape transformation due to asymmetry in their
geometrical shapes.

43
 The Effect of Mole Weight Ratio of Reaction on the Propagation of
Cellular Detonations

Chun Wang
State Key Laboratory of High-temperature Gasdynamics, CAS, No.15 Beisihuanxi Road, Beijing
100190, P.R. China

Abstract. The effect of mole weight ratio of chemical reaction on the propagation of cellular detonation
is concerned. The results of numerical investigation show that there is an important dependence of
detonation cell size on the mole weight ratio of chemical reaction. Low mole weight ratio means that
the gaseous reactant is dissociated to relatively smaller molecule product after chemical reaction, the
cell size of detonation increases with the decrease of mole weight ratio, which can be widely observed
in hydrocarbon fuel detonation. High mole weight ratio means that the gaseous reactant is recombined
to relatively larger molecule product after chemical reaction., the cell size of detonation decreases with
the increase of mole weight ratio.

44
Application of finite element direct integration method in flutter analysis

Jie Huang1, Guannan Zheng2, Guowei Yang3, Chengde Huang4, and Yingjie Yu5
1,2,3,4,5
Key Laboratory for Mechanics in Fluid Solid Coupling Systems, Institute of Mechanics, Chinese

Abstract. Flutter is a dynamic instability phenomenon caused by the interaction of aerodynamic force,
elastic force and inertia force. Common analysis methods include K method, PK method, CFD/CSD
coupling based on modal superposition method(M-S-M), etc. But these methods are not applicable when
dealing with flutter problems (aerothermal, fuel consumption, etc.) in which structural vibration
characteristics change with time. To solve those problems, this paper introduces the finite element direct
integration method(D-I-M) into CFD/CSD coupling method. Compared with the M-S-M, all vibration
characteristics of structure will be retained in D-I-M.

45
Assessing post impact mechanical characteristics of glass fiber laminates
by using beam coupons: A simplistic approach

Manoj K. Singh1 and R. Kitey2

1,2
Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur, 208016,
India
Email: manojmsk@iitk.ac.in

Abstract. Compression after impact (CAI) test is often used to assess the residual strength of laminates,
which are subjected to low velocity impact. While the test requires a complicated setup, it does not cover
all load regime. Although not standardized yet, flexural after impact (FAI) test offers a simpler
procedure, and has a potential to emerge as an alternative to CAI. In this investigation the beam
specimens, machined from glass fiber reinforced polymer (GFRP) composites are subjected to impact
energy up to 20J. The impacted specimens are subjected to symmetric four-point-bend tests to assess
their post impact flexural properties. The extent of damage and dissipation energy are observed to
increase with increase in incident energy. While the flexural strength decreases with increasing impact
energy, the flexural modulus is decreased only beyond a threshold incident energy. The residual flexural
characteristics are in good correlation with the impact induced damage in the laminates.

46
Influence of tab blockage on asymmetric under- expanded sonic free jet

Lavala Srinivasa Rao1, Partha Mondal2 and Sudip Das3

1,2,3
Department of Space Engineering and Rocketry, Mesra, Ranchi-835215, India
Email: srinuaero116@gmail.com

Abstract. Free jet facility to test various imperfectly/perfectly expanded sonic and supersonic jets have
been established at Birla Institute of Technology Mesra, Ranchi. In the present investigation an
underexpanded sonic jet with tabs having cylindrical cross sections have been adopted. The tab
placements were made circumferentially 1200 apart thus making an asymmetric arrangement in terms
of a plane bisecting the jet horizontally. The tab geometry has been selected as cylindrical in cross
section for its fundamental wake characteristics. The sonic free jet diameter is 15 mm and tab diameter
has been taken as 2mm. Three of these cylindrical tabs have been inserted and oriented circumferentially
to have blockages of 3, 7, and 11% compared to the free jet exit. To have these blockages the tabs were
either retracted away or inserted more towards the centre of the jet. All the tests were made with nozzle
pressure ratio of 4, defined as ratio between settling chamber pressure to ambient pressure which makes
the nozzle operate with underexpanded mode having ratio of exit pressure to ambient pressure as 2.11.

47
 Flutter Investigation of MW Sized Hybrid Composite Wind Turbine
Blade

Praveen Shakya1 and Umakanta Meher2

1
Malla Reddy College of Engineering and Technology, Department of Aeronautical Engineering,
Hyderabad, India
2
Indian Institute of Technology Kharagpur, Department of Aerospace Engineering, Kharagpur, India,
Email: umakanta.meher11@gmail.com

Abstract. Wind turbine blades of MW sized are generally made up of glass fibre or carbon fibre
reinforced composite materials. These large blades are slender and flexible in structure which may lead
to complex aeroelastic behaviour. In this work, a parametric study is conducted to determine the flutter
instability of hybrid glass/fibre composite SNL 61.5 wind turbine blade. Flutter speed is determined
using eigenvalue approach. Theodorsen’s theory is used for aerodynamic model. Results obtained for
different ratio of glass and carbon fibre hybrid composite are compared with original blade.

48
 Scaling law for core length in supersonic free jets

Arun Kumar Perumal1 and Ethirajan Rathakrishnan2

1,2
Department of Aerospace Engineering, IIT Kanpur, Kanpur, India
Email: akp@iitk.ac.in, erath@iitk.ac.in

Abstract. The present work is motivated by the shortcoming to predict the length of supersonic core of
free jet Lc*, especially the elliptic and circular jet exhausting into an ambient medium. Thus, we present
here the experiments demonstrating the scaling law for supersonic core length in circular and elliptic
free jets. Experimental conditions cover a wide range of nozzle design Mach number Md from 1.0 - 2.0,
nozzle expansion ratio pe/pa from 0.51 - 3.17, aspect ratio of nozzle AR from 1 - 6 (where AR = 1 and
> 1 correspond to circular and elliptic jets, respectively). In the present investigation, an empirical
scaling analysis is performed for Lc* in order to find a scaling factor ζ.

49
 Flow modifications & capacity augmentation due to streamwise
deployment of longitudinal vortex generators in a finned tube bank

Amit Arora1 and PMV Subbarao2

1
Department of Mechanical Engineering, MNIT Jaipur, Jaipur-302017, Rajasthan, India
2
Department of Mechanical Engineering, IIT Delhi, New Delhi-110016, India
Email: amit.mech@mnit.ac.in

Abstract. Intentional generation of three-dimensional longitudinal vortices is an effective way of

promoting bulk mixing in the otherwise streamlined fluid flows. “Toe-out” type vortex generators are
considered for the flow modifications, and the ensuing thermal augmentation in a plain finned tube bank.
As the degree of augmentation is governed by the location of the vortex generators, three dimensional
numerical investigation is conducted to analyse the effect of their streamwise translation. For that
purpose two different cross-stream positions are chosen where vortex generators are deployed, and their
streamwise position is varied in discrete steps. The study of velocity vectors makes it evident that the
vortex generators produce secondary flow structures over a significant region in their downstream which
promotes bulk mixing over a large fin area. Such flow modifications resulted in noticeable increase in
the heat exchange capacity on account of higher heat transfer coefficients. The flow visualization study
of the streamwise translation shows that the structure and the geometric extent of the vortices do not
change much despite the position of the vortex generators.

50
 A modified sharp interface immersed boundary method

Bo Yin1, Guowei Yang2 and Zhanzhou Hao3

1,2
Institute of Mechanics Chinese Academy of Sciences, China
3
University of Chinese Academy of Sciences, China
Email: yinbo@imech.ac.cn

Abstract. The sharp interface immersed boundary (IB) method based on the ghost cell has high
interface clarity at the boundary, compared with the diffused IB method. The physical quantity on the
ghost cell can be calculated via interpolation to realize the influence of the immersed boundary on the
flow field. However, the linear interpolation at the boundary reaches first-order accuracy at most. With
the increase of grid density, the computational efficiency decreases greatly as well. In this study, after
analyzing the causes of computational efficiency decrease, a modified sharp interface immersed
boundary method is proposed. This method constructs a compound bilinear interpolation function and
introduces a correction factor to improve the efficiency. This paper investigates the calculation results
and time-cost of flow around a cylinder under different grid densities and Reynolds numbers. The effect
of constant correction factor on the accuracy and efficiency is analyzed. It shows that when the
correction factor is negative, the calculation efficiency of the algorithm can be greatly improved. The
influence of the factor increases as the grid density increases, so that selected value of the correction
factor is dependent on the grid size.

51
 Aerodynamic Study on Airfoil With U-Shape Tubercle Geometry

B Sudarshan1, V Viswanath2, S Mukund3, J V Sujan4, and S Suhas5

1,2,3,4,5
Department of Mechanical Engineering, B.M.S. College of Engineering, Bangalore, India-
560019

Abstract. Flow separation is a vital problem for the fluid flow over an airfoil and results in performance
losses. Leading edge tubercles placed on turbine blades increases generation of energy and were found
to be effective in generation of power by a marine tidal turbine and low flow speeds. Bio-inspired
sinusoidal leading-edge protuberances are effective in flow control at higher angles of attack. The lacuna
of literature in enhancing the lift performance by augmenting the vortices formation is observed. In the
current study, the array of U-shape tubercles is investigated numerically and compared with sinusoidal
tubercles and plain leading-edge configurations for NACA0020 at a Reynolds number of 200,000. The
transient CFD simulation is performed ANSYS Fluent. The preliminary results demonstrated that the
airfoil with sinusoidal tubercles is very effective in increasing the lift coefficient.

52
Boundary Layer Transition on Large Scale Models in JF-12 Hypersonic
Shock Tunnel

Guilai Han1, Meikuan Liu2 and Zonglin Jiang3

Abstract. Hypersonic boundary layer transition on large scale models were experimentally investigated
in JF-12 hypersonic shock tunnel, including a flat plate with 3.2m in length and 1.2m, and a cone with
3.0m in length and half angle of 7 degrees. The effect of Mach number, unit Reynolds number of the
incoming flow, and stagnation temperature were discussed in this paper, by measuring the wall heat
flux, the location of transition zone, and the pressure fluctuation.

53
 Shock wave effects on Chitosan bio-polymer for drug delivery
applications

Pranav H A1 and B Sudarshan2

1,2
Department of Mechanical Engineering, B.M.S. College of Engineering, Bangalore, India-560019
Email: pranavha.mth19@bmsce.ac.in, bsudarshan.mech@bmsce.ac.in

Abstract. Biopolymers are natural polymers extracted from the cell wall of living organisms. Chitosan
material is used to study its properties when subjected to shock wave loading. We modified the present
manually operated shock tube to the semi-automatic where it produces a strong shockwave of order
Mach 4, the useful test time was found to be 100µs.The pressure sensors at end of shock tube will sense
exact pressure of de polymerized material under shockwave impact. The samples will be subjected to
repeated loading, after using SEM the properties will be investigated.

54
Effect of carbon black content on quasi-static compression behaviour of
filled rubber

Spandan Bandyopadhyaya1, Rajesh Kitey2, and C.S. Upadhyay3

1,2,3
Department of Aerospace Engineering, IIT Kanpur, Kanpur, India
Email: spandan@iitk.ac.in

Abstract. Rigid particle-filled rubbers have several engineering applications. While the rubber matrix
is an excellent shock absorber, the rigid fillers enhance the stiffness of the composite. Various
mathematical models have been proposed to predict the stress vs. strain curves of filled rubbers,
however, none of them could uniquely define the mechanical behaviour because of a complex
deformation characteristic of the composites, especially under cyclic loading. In this investigation,
vulcanized natural rubber, reinforced with carbon black fillers at different proportions, is subjected to
monotonic and cyclic loading under quasi-static compression. Permanent deformation along with strain
softening during successive loading-unloading cycles indicates the presence of Mullins effect, which
increases with increasing filler content in the matrix. The experimental data exhibit that the elastic
modulus and energy dissipation increase nearly exponentially as the filler content is increased, whereas
the corresponding values appear to saturate with the loading cycle. While unique stress-strain curves are
seen during initial cycles, successive loading-unloading conditions the material towards attaining
superimposed curves.

55
 Study of influence of vortices on trailing airfoil

Bhaskar K1, Mithil K2, Pushkar Chaudhary3, Sacheet S Amblekar4

and Sachin Maruti Shet5
1,2,3,4,5
Aerospace Engineering, RV College of Engineering®, Mysore Road, Bengaluru, India

Abstract. Study of vortex induced vibrations forms an important area of research as the performance of
most of the hydro and aerodynamic systems is influenced by them. The efforts in understanding the
mechanism of vortices started in late 18th century with the commendable efforts of Strouhal (1878) and
Von-Karman (1912). The most important dimensionless number which is used for obtaining the
frequency of vortex shedding is the Strouhal Number (St). The vortices generated by the aircraft leads
to wake turbulence, due to which smaller aircrafts flying in the vicinity experience a net downwash,
which in turn lead to disasters. Though considerable research has been carried out in the field of vortex
generation, study of effect of wake turbulence on the lift and drag coefficients of the aircraft in the
turbulence region have not been studied. Therefore, the present study aims to study the performance
parameters of airfoil in the turbulent region due to interaction with the vortices, by placing the airfoils
in series. The vortices are generated by changing the angle of attack of the leading airfoil. The airfoils
are placed at different relative distances as a function of chord lengths in order to analyse the effect of
distance between the airfoils on the vortex interaction. The numerical simulations of the experiment
have been conducted for various cases and the performance parameters like coefficient of lift, coefficient
of drag, coefficient of moment and aerodynamic efficiency have been plotted for each case.

56
 Parametric study of bio-inspired corrugated airfoil geometry in a
forward flight at Reynolds number 80000

Yagya Dutta Dwivedi1, N Lakshmi Narasimhan2, Jayendra Rajanala3

and Kameswara Sridhar Vepa4
1,2,3
Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Dundigal,
Hyderabad, Telangana, India, 500043
4
Department of Mechanical Engineering, GITAM (deemed to be University), Hyderabad, Telangana,
India, 502329
Email: lakshminarasimhan2000@gmail.com

Abstract. In this study, the effects of variations in the geometrical parameters on the aerodynamic
performance and stability of a bio-inspired airfoil were assessed using the computational method at a
Reynolds number of 80000. The investigation aims to recognize the influence of corrugations on
aerodynamic forces and moments and compare the variations with a non-corrugated profile having
similar geometry. Three different airfoils were chosen, the first is a corrugated airfoil inspired from the
mid-section of a dragonfly wing, the second is a different form of the first airfoil which was then
modified to match the maximum thickness of the first airfoil, and the third is a non-corrugated airfoil
obtained by joining the peaks of the second airfoil. These three models were fabricated using an additive
manufacturing process to undertake the experimental work in a low-speed wind tunnel to find
aerodynamic characteristics. ANSYS FLUENT solver was used to solve the steady, laminar,
incompressible, two-dimensional, RANS equations. The computational tests were performed for -4 to
+20 degrees angle of attack at Re~80000. The results revealed that the non-corrugated airfoil showed
comparatively better aerodynamic efficiency (up to 50% higher) whereas the corrugated airfoils
generated smaller moment thereby decreasing the instability caused by the wing.

57
 Design of a propellant grain with embedded metal wires

Hyunseob Lee1, Jongyun Oh2, Heesung Yang3, Sunyoung Lee4, Kiyeon Jeong5
and Taeock Khil6
1,2,3,4,5
Rocket Propulsion Laboratory, Mechanical R&D Center, LIG Nex1 Co., Ltd, Korea
Email: hyunseob.lee@lignex1

Abstract. Embedding metal wires into propellant grain can enhance the burning rate by creating cone-
shaped burning surfaces that amplify burning surface area. Applying a propellant grain with metal wires
enables to provide a variety of performance design. In this study, the performance design of a small
rocket motor using a propellant grain with embedded metal wires were conducted. Performance
characteristics were analysed according to the location and number of metal wires. The results from
internal ballistics design and experiment were compared.

58
 Finite element modelling and Monte Carlo ray tracing for the solar
parabolic trough collector with torque box

Natraj H1, B. Nageswara Rao2, and K. Srinivas Reddy3

1,3
Heat Transfer and Thermal Power Laboratory, Department of Mechanical Engineering, Indian
Institute of Technology Madras, Chennai 600 036, India
2
Structural Engineering Division, Department of Civil Engineering, Indian Institute of Technology
Madras, Chennai 600 036, India
Email: ksreddy@iitm.ac.in

Abstract. Parabolic trough collectors are the widely used concentrating solar technology. To be
competitive among solar power technologies, structural optimization of the PTC components is
essential. In this paper, a methodology is proposed to analyse the effect of self-weight and the wind
loads on the optical efficiency of the collector caused due to structural displacements at the trough
surface. Configuration of the parabolic trough collector having torque box similar to the design of LS-
3 and Euro trough design is considered. Finite element analysis for the trough surface along with optical
ray tracing reveals that the slope errors caused due to the wind loads have a substantial effect on the
optical efficiency of the collector. A decrease of 36% in slope error is observed for a change of pitch
angle from 0° to 90°. Under wind loads, the slope errors are as high as 4.074 mrad, causing a loss of
optical efficiency of 9%. The slope errors for the wind loads of 15m/s and at 0° pitch angles reach the
limit of shape quality of the mirror panels for the optimal performance. Hence the study highlights the
need for optimization of the design of solar collectors for wind loads to improve the performance

59
Research on Thrust Measurement System Design and Intelligent Thrust
Prediction Method Applied to Micro-electric Propulsion

Haibo Wang1, Guobiao Cai2, Chencong Fu3, Wei Liu4 and Weizong Wang5
1,2,3,4,5
Beihang University, School of Astronautics,102206 Beijing, China

Abstract. To evaluate the performance of electric thrusters, we have designed and developed a micro-
thrust measurement system，which is based on the torsion pendulum. Additionally, we designed a
gravity adjustment and calibration mechanism. We also designed the drag-free gas and electricity bridge
device to eliminate the drag force of the propellant supply pipeline and power supply cable of the electric
thruster, which could affect the linearity and accuracy of the measurement results. The electrostatic
comb pair is used to generate a standard weak force, and the thrust calibration and online measurement
methods are studied. Finally, through isolating vibration, setting of damping system, filtering, and
adding positive and negative bias forces for calibration, the measurement accuracy is improved as much
as possible. The thrust range of the measurement system is 0-20mN, the resolution is less than 5μN, and
the measurement error is less than 0.1%. To analyze the relationship between the power supply voltage,
current, propellant flow，and the thrust of the electric thruster, we measured the thrust of a miniature
ion thruster. Based on the measurement data under various working conditions, we try to build and train
the PBF neural network model to predict the thrust of the miniature ion thruster.

60
 Static and free vibration analysis of functionally graded shells using
non-polynomial quasi 3D shear deformation theory

Sambhaji Lore1, Aditya Deshpande2 and Bhrigu Nath Singh3

1,2,3
Department of Aerospace Engineering, IIT Kharagpur, 721302, India
Email: sambhajilore@gmail.com

Abstract. This paper deals with the bending and free vibration analysis of functionally graded
cylindrical, spherical and hyperboloid shallow shell panels using tangential non polynomial quasi 3D
shear deformation theory with eight degrees of freedoms (DOFs). The present theory assumes parabolic
variation of out-of-plane stresses and satisfies traction-free boundary conditions on the top and bottom
surfaces and does not require a shear correction factor. Power law is used to take into account the
variation of properties of shell panels across the thickness. The accuracy and efficacy of the present
theory and finite element model is validated with the results available in literature. For the analysis,
various types of shell panels with different material properties, gradation, thickness ratios, aspect ratios,
curvature ratios and boundary conditions are considered. The effects of these different geometric and
material properties on transverse displacement and natural frequencies are examined in detail.

61
 Connectivity Preserving Multi-Spacecraft Formation Control for
Trajectory Tracking with Obstacle Avoidance

Zhongyuan Chen1, Shitao Wang2, and Wanchun Chen3

1,3
School of Astronautics, Beihang University, Beijing 100191, China.
2
The 31002 troops, PLA, Beijing 100194, China
Email: wanchun_chen@buaa.edu.cn

Abstract. In order to make the multi-spacecraft formation flying safer, this paper designs a connectivity
preserving multi-spacecraft formation tracking control algorithm with the ability of inter-collision
avoidance and obstacle dodging. By combing the concept of consensus, a distributed control law for
multi-spacecraft formation configuration and maintenance is designed. Then the proposed formation
control law is expanded to trajectory tracking while achieving the safety requirements, including inter-
collision avoidance, obstacle dodging, and connectivity preservation. Both formation control schemes
are proved convergent by applying Barbalat’s Lemma. The effectiveness of proposed control schemes
is demonstrated through extensive simulations in the environment with multiple obstacles.

62
 A numerical study of integrity of Z-pinned laminates

Arun Kumar1, Sourabh Borchate2 and C.S. Upadhyay3

1,2,3
Laboratory for Advanced Aerospace Materials and Structures (LAAMS), Department of Aerospace
Engineering, Indian Institute of Technology, Kanpur, Uttar Pradesh, 208016, India.
Email: borchate@iitk.ac.in

Abstract. Many industries like aviation, automobile, rocketry, and missiles require structural materials
with high specific strength, stiffness, and fatigue life. This has led to dramatic growth in the use of
fibrous composite structures. However, in composite structures, joining two or more parts is not simple,
like welding, clamping, or riveting of metallic parts. Metal fasteners can be used for joining parts, but
drilling holes induce fatigue damages, structural failures and increased cost of drilling holes with high
dimensional accuracy. Many methods like stitching, weaving, braiding, tufting, Z-pinning, etc., have
been developed to fulfill this requirement. Z-pinning is a new technology that is better than metal
fasteners as it results in uniform load distribution around the joints, less moisture ingress, improvements
of delamination toughness, and prevention from fast (unstable) fractures. In this study, the effect of
fillers’ stiffness, Z-pin diameter, Z-pin density on stress distribution in plate, and load share of pins have
been analyzed numerically. A square plate with 6% volume fraction of pins, made of different materials,
has been considered. FEA analysis of stress distribution for three cases of loadings (tensile, shear, and
transverse) is carried out. Subsequently, the filler diameter has been reduced, and filler density has been
increased at a constant Z-pin volume fraction to understand its effect on load re-distribution
mechanisms. An analogy of springs in series and parallel has been considered for a basic understanding
of load shares of pin and ply.

63
Performance analysis of rough surface multi-recess porous hydro-static
thrust bearing

Pushpendra K Kushwaha1, Vivek Kumar2, Vinay Vakharia3, Satish C. Sharma4

1,3
Mechanical Engineering Department, School of Technology, PDEU Gandhinagar, India
2
Department of Mechanical Engineering, NSUT Delhi, India
4
Mechanical Engineering Department, IIT Roorkee, India

Abstract. This article presents numerical simulations of porous hydro-static thrust bearing considering
surface roughness effect and shear thinning behavior of lubricant. Rabinowitsch fluid model is used to
describe the shear-thinning of lubricant. An average film thickness model (Patir and cheng) has been
used and surface roughness is described along with transverse, isotropic, and longitudinal orientation on
the runner and thrust pad surface. The generalized form of the non-Newtonian Reynolds equation has
been solved using the finite element approach. The effect of permeability of porous layer, flow
coefficient of lubricant, and roughness orientation is analyzed on film pressure, load-supporting
capacity, lubricant flow rate, stiffness, and damping parameters. It has been found that the use of porous
layer and shear thinning of lubricant adversely affects the abovementioned performance indices.
However, the presence of surface roughness tends to improve the load supporting capacity, stiffness,
and damping parameters of bearing.

64
 Transverse-only VIV of a freely vibrating hybrid cylinder at low
Reynolds number

Himalaya Sarkar1, Pavan Kumar Yadav2 and Subhankar Sen3

1,2,3
Department of Mechanical Engineering, IIT(ISM) Dhanbad, Dhanbad, 826004, India

Abstract. Vortex-induced vibration (VIV) of a rigid hybrid cylinder (i.e., amalgamated geometry of
front of a half diamond cylinder and rare end of a circular cylinder) of finite length subject to uniform
steady flow is investigated numerically. The vibrations of the cylinder are confined only in the transverse
direction. Simulations are conducted for a constant mass ratio, m∗ of 10, at a constant Reynolds number
of 100 over a reduced speed, U∗ range of 1 to 10. In the present work, observations focus on the
response, aerodynamic coefficients and flow features.

65
 A quasi-longitudinal study of the effect of hemodynamical parameters
on the biomechanics of rupture in Abdominal Aortic Aneurysms

Samarth S Bhatt1, Amritanshu Dixit2, Ahmad Shaikh3 and Tejas Canchi4

1,2,3
Department of Mechanical Engineering, B.M.S. College of Engineering, Bangalore 560019, India
4
School of Mathematics and Statistics, University of Sydney, NSW 2006, Australia
Email: samarth.me17@bmsce.ac.in

Abstract. Maximum transverse diameter, routinely used as a clinical metric in Abdominal Aortic
Aneurysm (AAA) management has been insufficient to accurately stratify rupture risk. In this study, a
biomechanics-based approach is employed aiming to establish a relationship between maximum
transverse diameter and hemodynamic parameters that are indicative of disease progression. A
numerical methodology is used on six idealised, axisymmetric AAA models of increasing maximum
transverse diameter representing disease progression. Additionally, a comparative hemodynamic
analysis of the effect of four different inlet velocity profiles is performed. The results indicate a flow
field with similar vortical structures forming in the aneurysmal sac, changing in intensity with increase
in maximum transverse diameter. This is represented through elevated time-averaged wall shear stresses
(TAWSS) in the distal neck region of the aorta in the largest aneurysm (3.16 Pa). However, the elevation
of TAWSS in smaller aneurysms is observed to be sharper than those in large aneurysms indicating an
elevated rupture risk for smaller aneurysms even below the clinical metric of 55 mm. The plug inlet
velocity profile showed the highest (8.81 Pa) TAWSS indicating jet-like flows in the aneurysmal sac.
Current clinical management of AAAs will greatly benefit by bringing in additional insights through
biomechanical analysis.

66
 Effect of oblique shocks interaction on the inlet structure in a
hypersonic flow

Sanjay A V1 and B Sudarshan2

1,2
Department of Mechanical Engineering, B.M.S College of Engineering, Bengaluru-560019,
Karnataka, India
Email: sanjayav.mth19@bmsce.ac.in, bsudarshan.mech@bmsce.ac.in

Abstract. Scramjet inlets is a vital component whose design has a significant impact on the engine's
overall performance. The shock interaction in the inlet region influences the structure with pressure and
temperature variations. In the present study, shock interaction effect on the structure in an scramjet
engine kind of inlet is investigated. The inlet region with shock interaction condition is imitated with
the like family oblique shocks using the opposite wedges. The hypersonic flow of free stream Mach
number 5.5 to 7.5 is generated using the shock tunnel setup and the pressure variations are analyzed
using fast-reacting pressure transducers. Shock interaction location is positioned in the inlet region by
varying offset distance and wedge angles. The experimental testing model is designed and in parallel
CFD simulation works are in progress.

67
 A Numerical Study on the Negative Lift and Point of Non-linearity in
Lift Curve of NACA 0012 Airfoil at Low Reynolds Number

Gangadhar Venkata Ramana Pinapatruni1, Sunil Manohar Dash2, Jit Sinha3

and Kalyan Prasad Sinhamahapatra4
1,2,3,4
Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur,
West Bengal - 721302, India
Email: smdash@aero.iitkgp.ac.in

Abstract. In the present numerical study, incompressible flow around a NACA0012 airfoil is
investigated to understand the negative lift and point of non-linearity as seen in its lift curve. Numerical
simulations are performed using a finite volume-based CFD solver at a Reynolds number of 4.0×104.
We found a higher-pressure gradient and a greater static pressure magnitude region on the upper airfoil
surface, which creates a net negative circulation around the airfoil, resulting in a negative lift at a small
positive angle of attacks. However, as the angle of attack increases, the pressure on the lower airfoil
surface becomes more significant than the pressure on the upper surface along the entire chord, leading
to recovery from the negative lift and eventually producing a positive lift. It is further noticed that at
enhanced flow turbulence intensities, the pressure difference between the airfoil surfaces is suppressed,
reducing the negative lift value. In addition, we observed a point of non-linearity on the lift curve at a
moderate angle of attacks for which flow features around the airfoil are thoroughly analysed.

68
 Performance Analysis of Autonomous Flight Models Based on
Reinforcement Learning for Military UAV

Hyoju Nam1, Haejin Kwon2, Keunho Yun3, Jia Kim4 and Kyutae Cho5
1,3,4,5
Intelligence & Software Center, LIG Nex1, Seongnam-si, Gyeonggi-do, Republic of Korea
2
Computer science and Engineering, POSTECT, Pohang-si, Gyeongsangbuk-do, Republic of Korea

Abstract. In order for UAVs (Unmanned Aerial Vehicles) to perform their mission successfully without
the control of human pilots, they must recognize the surrounding environment and fly autonomously
while controlling the movement of airframe. The existing control methods for UAVs have been
developed based on mathematical models. However, the mathematical models cannot control contently
if the surrounding environment changes suddenly because the mathematical model has uncertainty. To
solve this limitation, we conducted study on autonomous reconnaissance flight of the military UAVs
based on deep reinforcement learning in which the UAVs can detect and avoid obstacles and fly to the
destination successfully. In this paper, we propose the diverse 3D simulation environments such as cities
and mountains generated using Unity for reinforcement learning, and the reward structure also.
Moreover, the UAVs were trained under various hyper-parameter conditions using PPO and SAC,
representative reinforcement learning algorithms. From the experimental results, we compared and
analyzed the performance of PPO and SAC from the multiple perspectives. In conclusion, we confirm
that using PPO in simple environments and SAC in more complex environments is more efficient in
terms of mission success rate.

69
 Aerodynamic Characterisation of a Re-entry Module in Supersonic
Flow Regime

Devashish Bhalla1, Vidya Gurumurthy2 and Manoj T. Nair3

1,3
Department of Aerospace Engineering, Indian Institute of Space Science and Technology,
Thiruvananthapuram, Kerala, India,
2
Division Head, Aero Combustion Modelling Division, Aeronautics Entity, VSRC, ISRO,
Thiruvananthapuram, Kerala, India and
Email : bhalladev36@gmail.com, g_vidya@vssc.gov.in, manojtnair@iist.ac.in

Abstract. The estimation of aerodynamic characteristics is necessary for designing a re-entry vehicle.
This is an essential input to study the static and dynamic stability of the configuration and also to provide
inputs for structural, thermal and trajectory design/ analysis. Studies related to the flow field simulation
based on CFD and the aerodynamic characteristics of a typical re-entry body, crew module, in
supersonic flow regimes, are presented in this paper, along with the detailed analysis. CFD++, a
commercial RANS solver with 2-equation realizable κ-ε turbulence model, is used for the 3D
simulations, along with Pointwise, for structured grid generation. The effect of Mach number (ranging
from 1.2 to 4) and angle of attack (ranging from 0◦ to -15◦) on CP, CL, CD, CL/CD and Cmcg, is
thoroughly studied, after validation of the results at M=4.

70
 Numerical Study of Tilted Multi-Storied RCC Buildings on Shallow
Foundations Considering Soil-Structure Interaction

Devjit Acharjee1, Srijani Bandyopadhyay2, and Debasish Bandyopadhyay3

1,3
Department of Construction Engineering, Jadavpur University, Kolkata 700106, India
2
Department of Civil Engineering, Meghnad Saha Institute of Technology, Kolkata, India
Email: devjitacharjee1996@gmail.com

Abstract. Tilt and settlement of mid-rise RCC buildings with shallow foundation in alluvial soil of
greater Kolkata has become a common problem. It greatly affects the overall structural stability of these
buildings and demands accurate investigation. Tilt & settlement monitoring to assess the verticality and
non-destructive tests to assess strength & quality of concrete are practiced in real life situation, which
cannot infer the overall building stability. Numerical modelling with fixed supports may address the
stability issue to some extent but the soil-structure interaction seems to contribute to a great extent on
the stability of the tilted building. Earthquakes have also shown that structures on softer soil are more
vulnerable. Thus, stability analysis of various RCC buildings with different structural configuration with
various tilt considering soil-structure interaction seems to be significantly important. Numerical study
of building models on finite element platform considering different soil types, nature and extent of tilts,
building configurations etc. have been made. It is found that the soil type, soil-structure interaction,
building configuration have significant role on the stability of these tilted buildings. The present study
may be explored for real life application of safety evaluation and retrofit of existing multi-storied tilted
RCC buildings.

71
 Numerical simulation of wind-driven rain on gabled roof buildings

Chenhao Xu1, Chongwen Jiang2, Siyuan Pi3, Shuyao Hu4 and Zhenxun Gao5
1,2,3,4,5
National Lab for Computational Fluid Dynamics, School of Aeronautic Science & Engineering,
Beihang University, Beijing 100191, People’s Republic of China
Email: cwjiang@buaa.edu.cn

Abstract. Methods based on the Lagrangian particle tracking (LPT) model are commonly employed in
the wind-driven rain numerical simulation. However, classical LPT methods require large number of
raindrops to obtain accurate WDR intensity distribution on the facade. One of LPT methods named
Finite Panel Method (FPM) proposed recently could reduce the require of the number of raindrops by
panel division and WDR intensity reconstruction. Nevertheless, the trajectories ended on the corner of
the panels are needed to be correctly acquired to ensure the accuracy. In this study, an efficient way to
calculate the required trajectories that the terminates are given beforehand is established, and the WDR
intensity on a gabled roof building is investigated by the present methods along with the FPM. Results
indicate that the number of raindrops required in the present methods could be reduced by 1 to 2 orders
compared with the shooting method, and the discrepancy of the maximum WDR intensity between the
classical LPT method and the present method is 7.9% in the vertical windward façade and 0.7% in the
gabled roof. It can be seen that the present method could accurately calculate the WDR intensity and
need lower effort to compute the raindrop trajectories.

72
 Research on Modeling Method of Complex Load Transmission

Liying Tang1 and Zhongmin Deng2

1,2
School of Astronautics, Beihang University, China
Email: dengzhongmin@buaa.edu.cn

Abstract. In this paper, the rocket body is regarded as a Euler-Bernoulli beam with variable cross-
section and variable elastic modulus. a research on load modeling methods is carried out for a given
complex force transmission model and is applied to developing related engineering analysis software.
First of all, for a given load transfer model, a research on modeling method of statically indeterminate
force transfer based on the McCauley singular function method is carried out, and a statically
indeterminate force transfer load analysis engineering method is established. Secondly, on the basis of
the first step, a statically indeterminate force transfer engineering analysis software is developed. Then
the robustness and operability of the software are tested to ensure that the software has the ability to
analyze engineering problems. Finally, the developed software is used to perform load transfer analysis
on the given engineering model. The force transmission error between the developed software and large-
scale commercial software is compared and analyzed, and the influence of uncertain factors in the model
on the complex force transmission of the load is studied. This software has certain theoretical opinions
and practical value for the load engineering analysis during the preliminary design of the rocket.

73
 Numerical Simulation of flow over blunt body with Passive Control
Technique

M V Nitya1, Vineeta Bhat2, Sai Swaroop3 and Snehal U M4

1,2,3,4
Department of Aerospace Engineering, B.M.S. College of Engineering, Basavanagudi,
Bangalore, India
Email: nityaanjali25@gmail.com

Abstract. The aerodynamic design of hypersonic vehicles requires the accounting of complexities such
as high-temperature effects, thin shock layer, and viscous interactions. These effects become more
formidable with increasing altitudes and higher flight speeds. Hypersonic vehicles must be thereby able
to withstand severe aerodynamic surface heating, as well as the mechanical loads acting on them and
their reduction, plays an indispensable role in the design. The techniques being developed are broadly
classified as active and passive flow control techniques. The former includes the use of a jet spike at the
nose cone of the blunt-body, while the latter uses spikes and cavities or a combination of both. The use
of a spike at the tip of the blunt-body happens to be the simplest and efficient technique in comparison
to other passive methods. This study focuses on the method of reducing wave drag using aerospikes.
The hemispherical structure is chosen as a basic model because it offers a good heat distribution.
Through this work, the effect of aerospike, with different spike heads – pointed, flat, and hemispherical
– has been investigated. It is observed that the presence of a spike generates a weaker tip shock, leading
to the formation of a separation zone on the spike stem due to the adverse pressure gradient in the
boundary layer region. Also, the formation of a shear layer separating the main flow and recirculation
zone along with the reattachment shock on the main body, aids in reducing the drag.

74
 LES of a Swirl-Stabilized Turbulent Kerosene Spray Flame in a Model
Combustor

Kaidi Wan1, Yunzhe Huang2, Zhenxun Gao3, Yong He4 and Chongwen Jiang5
1,2,3,5
Aircraft and Propulsion Laboratory, Ningbo Institute of Technology, Beihang University,
Ningbo,315832, China,National Laboratory for Computational Fluid Dynamics, School of Aeronautic
Science and Engineering, Beihang University, Beijing, 100191, China
4
State Key Laboratory of Clean Energy Utilization, Zhejiang University, Hangzhou 310027, China

Abstract. Kerosene is widely employed as aviation fuel of aeroengines. The combustion of kerosene
spray is quite complex, which involves atomization of the fuel jet, breakup of spray droplets, and
turbulent mixing between kerosene vapor and air. Large-eddy simulation (LES) is a useful high-fidelity
numerical technique to study the complex multiphase turbulent combustion phenomena in kerosene
flames. In the present study, flamelet generated manifold (FGM) chemistry tabulation approach is
coupled with artificial thickened flame (ATF) model to describe the burning of kerosene under the LES
framework. The FGM-ATF-LES approach take the complex chemical kinetic effects of kerosene
combustion into account with a minor computational cost. A swirl-stabilized turbulent kerosene spray
flame in a model combustor is investigated with the proposed FGM-ATF-LES approach and the overall
partially premixed flame characteristics are well predicted by the LES simulation.

75
 LES of compressible round jet impinging on a flat isothermal plate

Swagatika Pradhan1 and Somnath Ghosh2

1,2
Department of Aerospace Engineering, IIT, Kharagpur, West Bengal-721302, India,)
Email: swagatika244@gmail.com

Abstract. Large eddy simulations(LES) of highly subsonic round jet impinging on a circular flat plate
is carried out using high order compact finite difference scheme. An explicit filtering using approximate
deconvolution method is applied. The Mach number of the jet is taken as 0.9 and Reynolds number is
50000 based on the jet diameter and center line velocity of the jet. The distance between the jet inlet and
flat plate is taken as eight times jet radius. Isothermal, no slip wall boundary condition is used for flat
plate. The complex flow phenomena of the impinging jet are studied. The mean flow variables obtained
show similar behavior as reported earlier in the literature. From the instantaneous pressure field, it is
observed that acoustic waves from the impingement region is travelling in the upstream direction
towards the inlet inside the jet as well as outside the jet.

76
 Robust flutter analysis of a sweptback wing using μ method

A Arun Kumar1 and Amit Kumar Onkar2

1,2
Structural Technological Division, CSIR-National Aerospace Laboratories, Bangalore 560017,
India
Email: aeroamit@nal.res.in

Abstract. The present work deals with robust flutter analysis of a sweptback wing in the presence of
structural and aerodynamic uncertainties. The methodology adopted is based on the concepts of linear
fractional transformation and structured singular value (µ) method. Here, the uncertain aeroelastic
system is constructed by introducing uncertainties in the modal stiffness matrix and unsteady pressure
coefficients. Then, using linear fractional transformation, the uncertain aeroelastic system is transformed
into a feedback loop consisting of nominal aeroelastic model and block-structured uncertainties. Finally,
structured singular value (µ) analysis is conducted to find robust stability of the wing under the given
set of uncertainties at various flow conditions. The robust flutter boundary obtained from the present
approach is also compared with experimental data.

77
 Risk assessment of cerebral aneurysms using FSI

Shantanu Saha1, Harshavardhan E2, Jayanand Sudhir B3 and Shine S R4

1,2,4
Indian Institute of Space Science and Technology, Trivandrum, 695547
3
Sree Chitra Tirunal Institute for Medical Sciences and Technology, Trivandrum, 695011
Email: shine@iist.ac.in, srshine@gmail.com

Abstract. The transient cerebral hemodynamics in weakened arterial sections is modeled using FSI to
evaluate the risk of initiation of an aneurysm. Following the validation of the model, a qualitative
analysis is done by simulating a sinusoidal pulse in the Circle of Willis. The results show that critical
hemodynamic parameters at different locations are affected disproportionately due to wall weakening.
The stresses are observed to be concentrated near the bifurcations. Though constrained by the idealistic
assumptions in the geometry and boundary conditions, the study is able to capture the hemodynamic
variations at critical regions.

78
Icetacm2021-Experimental Study of Flow Behaviours of Fly Ash Slurry
with And Without Chemical Additives

Priyanka Nimar1, Kanwarpal Singh2 and Arvind Kumar3

1
UIET MDU, Rohtak, India
2
GNIOT, India
3
YMCAUST, Faridabad, India

Abstract. In a thermal power plant, both fly ash and bottom ash cause a lot of damage to the
environment. Keeping the environment in mind fly ash and BA (bottom ash) are transported through
pipelines as slurry which is also economical than other transportation method. The aim is to investigate
experimentally fly ash flow characteristics with and without chemical additions to coal ash
concentrations ranging from 30 to 50% by mass. Cetyl Trimethyl Ammonium Bromide (CTAB) which
is a cationic surface active agent and Sodium Salicylate (NaSaL) anionic surface active agent are used
in equal proportions ranging from .01to 1% of total coal ash slurry. It is demonstrated that when the
solid concentration is 30-50 percent by mass, all samples act non-Newtonian and match the Herschel-
Bulkley model with shear thickening characteristics. It is noticed that the degression rate is slow over
200 s-1 shear rate for all chemical compounds tested. The experimental results reveal that as the
percentage of chemical additives increases at the same shear rate, the degression in shear stress
decreases. It is also discovered that shear stress is reduced when only CTAB is used. BA at 30% by
mass with CTAB & NaSaL (1:1) doses demonstrates various tendencies. As the dosages of additive
increase (0.5% & 1%) the shear stress increases with increase in shear rate. Viscosity drops rapidly at
low shear rates up to 150 s-1, after which the degression rate slows.

79
 Study on Multiscale Modelling Method for Investigation on Damage of
Wind Turbine Composite Blade

Haseung Lee1, Younggyu Lee2, Changduk Kong3 and Hyunbum Park4

1,2,4
School of Mechanical Convergence System Engineering, Kunsan National University, Rep. of
Korea 3Department of Aerospace Engineering, Chosun University, Rep. of Korea
Email: swordship@kunsan.ac.kr

Abstract. In this work, 1 MW class horizontal axis wind turbine blade configuration is properly sized
and analyzed using the newly proposed aerodynamic design procedure and the in-house code developed
by authors, and its design results are verified through comparison with experimental results of the
previously developed wind turbine blade. The wind turbine structural design is carried out using the
Glass/Epoxy composite materials and the simplified deign methods by the netting rule and the rule of
mixture. The structural safety of the designed blade structure is investigated through the various load
case studies. Finally, multiscale modeming method for investigation on various damage of designed
blade was performed.

80
 Design and Numerical Study of Variable Geometry Scramjet Inlet for
Mach 5 to Mach 7

Shivashree S
Aerospace department, Jain (Deemed-to-be University), Bangalore, Karnataka-562112, India
Email: shivashrees2017@gmail.com

Abstract. A two-dimensional generic variable geometry scramjet inlet is devised to operate within a
range of Mach number 5 to 7. For optimum performance of the scramjet inlet, the shock on lip condition
is desirable. This paper focuses on achieving this condition through the displacement of the cowl
backward at off-design Mach numbers. To validate the results, the numerical simulation platform of
Fluent/MATLAB has been used. Specific performance parameters, i.e., pressure recovery factor,
compression ratio, kinetic energy efficiency, and capture area, are analyzed using Reynolds average
Navier stokes equation (RANS) and standard K- turbulence model. For discretizing the convective
terms, QUICK (quadratic upwind interpolation for convective kinematics) is used. Examining the
results, it is found that there is a marked improvement in the performance at off-design conditions when
the variable design is implemented to the scramjet inlet compared to the fixed geometry.

81
 Ensemble Machine Learning Methods for Unsteady Aerodynamics
Modeling using Flight Test Data

Ajit Kumar1 and Ajoy Kanti Ghosh2

1
Department of Mechanical and Aerospace and Mechanical Engineering, IITRAM, Ahmedabad,
Gujarat 380026
2
Department of Aerospace Engineering, IIT Kanpur, Uttar Pradesh 208016, INDIA

Abstract. Aerodynamic modeling from the flight data involves a process of identifying the aerodynamic
model from the observed input and output data. It has an important contribution in the field of aerospace
control and guidance design, performance characterization, aerodynamic database design, fault
detection and diagnosis etc. In last few decades, several methods are reported in the literature to estimate
these models. Apart from the conventional methods such as: equation error method, output error method,
filter error method, data-driven based methods also have grabbed the attention. These methods use the
principle of artificial intelligence and machine learning. In this work, two ensemble machine learning
based methods namely Bagging and Boosting are proposed to model the unsteady aerodynamics of the
aircraft from flight test data. Bagging creates a predictive model by combining multiple decision trees
which are trained on different input-output datasets using the bootstrap. Boosting creates a predictive
model where trees are grown sequentially based on previously grown trees and each decision tree fit on
a modified version of the data. The efficacy of these two data-driven methods is examined and validated
by estimating the force and moment coefficients of the standard research aircraft. Estimated results of
the proposed methods are statistically analyzed and observed as vastly correlated with measured data
and having significantly less root mean squared error (RMSE). Also, these estimated aerodynamic force
and moment coefficients are compared with the estimated coefficient model from conventionally and
most popularly used maximum likelihood estimation (MLE). Estimated results found to be on par with
the MLE predicted aerodynamic models. Moreover, Bagging and Boosting based methods do not
require to solve the equation of motion, and this advantage can be seen for generalized applications of
nonlinear modeling such as load estimation, aeroelasticity, and fault diagnosis, detection and
identification.

82
 Robust Navigation with NavIC Software Receiver using Vector Delay
Lock Loops

Ravindar Reddy Dadapur1, Chittimalla Srinu2 and Laxminarayana Parayitam3

1,2,3
Research and Training Unit for Navigational Electronics (NERTU), Osmania University (OU),
Hyderabad, India,Department of ECE, JNTUH College of Engineering Hyderabad, Hyderabad, India
Email: srinu.chittimalla@osmania.ac.in, laxminarayana@osmania.ac.in

Abstract. INTRODUCTION AND OBJECTIVES In harsh and challenging environments like urban
canyons, the NavIC receiver experiences a sudden blockage of one or more satellites at any given time.
In this scenario the positioning accuracy with the traditional scalar tracking loops of NavIC receiver gets
severely degraded. The traditional GNSS receiver tracking architectures are vulnerable and not able to
provide desired positional accuracy in these conditions. The Non-Line of Sight (NLOS) signals from
the reflections of buildings or objects degrades the code and carrier frequency measurements, which
results in the loss of lock of the code and carrier of the tracking loops. Consequently, the pseudo range
and Doppler measurements are degraded. So, advanced methods like vector tracking architectures have
been adopted recently to overcome the effects of temporary blockage of satellites or outages and
interference especially in urban environments for autonomous navigation applications. The traditional
scalar tracking loops in a GNSS receiver works independently for each channel. They don’t take the
advantage of available information like position, velocity and its errors for estimating the frequency and
phase of the code and carrier. There is no exchange of information among the tracking channels, which
can be derived from the user position. In a traditional GNSS receiver, the navigation solution is
calculated using pseudorange and pseudorange rate observations i.e. code phases and carrier frequency
observations, estimated only from the tracking loops. This inherently available information/advantage
is exploited by the vector tracking loops, where aiding from the strong tracking channels to weak
channels takes place. The performance of vector tracking loops is better than traditional tracking loops.
In the Vector tracking loops, code phases and carrier frequency observations are calculated by projecting
the relative position and velocity between the receiver and corresponding satellite in LOS direction. The
aim of this paper is to implement and integrate vector tracking loops with Extended Kalman Filter (EKF)
specifically VDLL (vector delay lock loop) into NavICSR, where NavICSR is a post-processing based
time-synchronous software receiver implemented in MATLAB for the Indian Regional Navigation
Satellite System (IRNSS/NavIC) at Research and Training Unit for navigational Electronics (NERTU)
of Osmania University [1]. Initially it is developed from the open source GPS project of Dennis M Akos.
At present, the proposed algorithms [2-5] for Vector Tracking Loops are verified with the IF data
collected from RF front end. However, we are also expecting to get a GNSS simulator including NavIC
signals, which will generate IF data for the given dynamics of the receiver. So, performance of NavIC
Software Receiver (NavICSR) with vector tracking architectures will be compared with the traditional
scalar tracking architectures and the results will be presented in this paper. The scalar and vector tracking
loop architectures are implemented in this study. The experiment will be carried out with the IF data
collected from an RF front end connected to antenna and software receiver or simulated IF data collected

83
in a file for static and dynamic conditions. This study enhances the NavICSR capability to deliver the
PVT or navigation solution for dynamic IF data. This paves the way for NavIC research community to
do further research and development using NavICSR in different challenging or signal degraded
environments.

84
 Development of drone-mounted mechanism for multiple fruit
harvesting

Bohyun Hwang1, Kiyoung Joo2, and Byungkyu Kim3

1
Department of Aerospace and mechanical engineering, Korea Aerospace University, Korea
2
Department of Smart Drone Convergence, Korea Aerospace University, Korea
3
Department of Aerospace and mechanical engineering, Korea Aerospace University, Korea,
Department of Smart Drone Convergence, Korea Aerospace University, Korea.

Abstract. The drones had been developed mainly for military purposes. Recently, the applications are
expanding to various fields such as construction, geographic mapping, shipping, delivery, and
agriculture. In particular, the use of drones in agriculture is rapidly expanding every year. In this article,
we propose a drone-mounted mechanism for fruit harvesting to relieve labor shortage and improve
safety of the farmer in the expanding smart agriculture market. The proposed mechanism is deployed
with a telescopic method to approach the fruit and then harvest the fruit. By using only one motor, power
consumption is minimized and more payload for harvested fruits is allocated. In addition, since
telescopic method is realized by employing the rack and pinion gears, rigidity is secured. Therefore,
multiple fruits can be harvested by pruning and grasping based on one time activation of the mechanism.

85
 Wake Dynamics of a Flexible Flapping Filament at Low Reynolds
Number

Chhote Lal Shah1, Dipanjan Majumdar2, Chandan Bose3, and Sunetra Sarkar4
1,2
Department of Aerospace Engineering, Indian Institute of Technology Madras, Chennai-600036,
Tamil Nadu, India.
3
Institute for Energy System, School of Engineering, University of Edinburgh, Edinburgh EH9 3BF,
United Kingdom
4
Complex System and Dynamics Group, Indian Institute of Technology Madras, Chennai-600036,
Tamil Nadu, India.
Email. 1al.chhote.shah@gmail.com

Abstract. This study investigates the dynamical behaviour of the flapping filament subjected to a
uniform inlet velocity at a low Reynolds number, considering the heaving amplitude as a bifurcation
parameter. A discrete forcing immersed boundary method (IBM)-based inhouse fluid-structure
interaction (FSI) solver is used for the present simulations. The flapping response transitions from
periodic to aperiodic state as the bifurcation parameter is gradually increased. An interesting flow-field
transition is observed in the corresponding trailing wake. At lower heaving amplitude, the flow field is
periodic with a von-Kármán wake. As the heaving amplitude is increased, the von-Kármán wake
transforms into a symmetric bifurcated wake, preceding a robust aperiodic state observed at a higher
heaving amplitude.

86
Experimental study of inflight icing conditions on coefficient of pressure
distribution around NACA0012 aerofoil

Dr. Swetha S1, Dr. Sarat Kumar Maharana2, Dr. Abdul Sharief3
and Ms. Steffi Thangachan4
1,2,4
Department of Aeronautical Engineering, Acharya Institute of Technology, Bangalore-560107
3
Professor & Dean, School of Engineering, School of Engineering, Presidency University, Bangalore
560064

Abstract. Since the beginning of civil aviation, ice accretion on aircraft has been a great matter of
concern for flight operation and has posed a serious safety issue to its overall performance. The
foundation of such weather-related and, sometimes, unpredictable occurrences lie with the changes in
properties of air. The outcomes of earlier research activities in the field of ice accretion study have
inspired scientists to go deeper into the phenomenon and unfold the mystery of ice accretion. A good
amount of data collection, interpretation and visualization is necessary to derive the cause of ice
accretion and the way to lessen it. Hence computational and experimental methods need to get
complemented by the outcomes of other techniques. An attempt to study ice accretion for a clean and a
rough NACA0012 aerofoil has been made. The complexity of the ice accretion situation over an airfoil
needs to be thoroughly investigated as far as aerodynamic performance issue is concerned in the
operation of aircraft. The impact of inflight icing conditions on the pressure coefficient variation around
an aerofoil is significant. The pressure coefficient is one of the important aerodynamic characteristics
that predicts the performance of the aerofoil. The icing conditions have been generated artificially
around the aerofoil and experiments have been conducted for different conditions to note the impact of
icing on the value of pressure coefficients. The experiments have been conducted using subsonic wind
tunnel. Two grades of sand-papers (P120 and P220) have been used to emulate the roughness of ice.
The arrangement for icing condition has been simplified to suit the need of the study. Numerical
simulations have been done to verify the aerodynamic characteristics such as coefficients of lift and
drag. Since ice accretion simulation needs to go through the fundamental steps such as the simulation
of external flow, water droplet simulation and finally ice accretion, the FENSAP-ICE (Finite Element
Navier-Stokes Analysis Package for Inflight icing) has been implementation to carry out all these
simulations. The basic governing equations for the above-mentioned steps have been solved by the
individual solver components like FENSAP (a finite element Navier-Stokes) for external flow,
DROP3D for droplet solution and ICE3D for ice accretion.

87
 Modelling and analysis of winglet morphing for aerial vehicles

Nandni Sharma1, Gaurav Chhabra2, and Abha Gupta3

1,2
Aerospace Department Punjab Engineering College (Deemed to be University), Chandigarh, India
3
Aerospace Department Punjab Engineering College (Deemed to be University), Chandigarh, India
Email: nandni99sharma@gmail.com

Abstract. This paper presents a study of the design of a wing-mounted with a morphing winglet, along
with its aerodynamic and structural analysis. The concept of span-wise morphing of winglets is proposed
as it is an effective technology for enhancing aerodynamic efficiency and has the potential to replace
conventional control surfaces. Further, the main advantages of variable span morphing winglets are the
drag reduction that leads to an increase in range and endurance of the flight. The design includes a
honeycomb core placed in between the skin of the winglet where span-wise morphing occurs to increase
the structural integrity. Two actuators are used which are fixed at the rib of the winglet to carry out the
span-wise morphing of the winglet. For aerodynamic analysis, ANSYS Fluent solver is used to
investigate a flow field in a three-dimensional wing structure and to obtain lift/drag variations. Static
structural analysis has been performed on ANSYS Mechanical solver to obtain the deformation, stress,
and strain variation. It was observed that a 25% extension in span leads to a 4% increase in overall L/D.
This shows that morphing in winglets can be a profound way to increase the aerodynamic efficiency of
aerial vehicles.

88
 Effects of jet flow on wake of high-speed train

Guo Dilong1, Liu Wen2 and Yang Guowei3

1
Key Laboratory for Mechanics in Fluid Solid Coupling Systems, Chinese Academy Of Sciences,
100190. Beijing, China
Email: jack9517@126.com

Abstract. The wake region of high-speed trains usually consists of shear layers, shedding vortices,
separation and reattachment regions, and a pair of large anti-symmetric rotating flow vortices, The rapid
formation and shedding of vortexes not only increase the pressure resistance of the head-to-tail vehicles,
but the periodical variation of vortex pair also affects the lift force and side force of rear vehicle
seriously, which affects the stability of train operation and the comfort of passengers, as well as the
passengers on the platform and workers along the railway line. In this paper, numerical analysis method
is adopted to study the jet flow, starting from the wake vortex generation source, the jet flow is controlled
by setting jet groove, and its mechanism and effectiveness are studied, Through comparative analysis,
the effects of jet flow rate, jet direction on wake are obtained. Some results are shown as follows. 1. Jet
control has an obvious influence on the aerodynamic lift force of the tail car, which changes from
positive lift force of the tail car to negative lift force. The strength of the wake field is obviously
weakened, which improves the safety and stability of train operation. 2. By comparing the effects of
different jet flow rates, it is found that the negative lift of the rear vehicle increases with the increase of
jet flow rate, and the wake vortex structure decreases with the increase of jet flow rate. The jet flow has
a slight influence on the aerodynamic resistance of the train. When the jet Angle is 0, the low jet flow
can reduce the drag, while the high jet flow can increase the drag. Therefore, the jet should be set up
according to the actual situation. 3. By comparing the effects of different jet angles, it is found that the
negative lift of the trailing vehicle increases first and then decreases with the increase of the jet Angle,
the drag of the trailing vehicle increases with the increase of the jet Angle, and the trailing vortex
structure increases rapidly with the increase of the jet Angle. Therefore, 0° Angle should be the best
state for jet control.

89
 Experimental Prediction of Wind Flow and Pressure Distributions
Around a Low-Rise Building

Venugopal M M1, S K Maharana2, and Mahantayya K Hiremath3

1,2,3
Department of Aeronautical Engineering, Acharya Institute of Technology, Bangalore-560107

Abstract. The wind flow over low-rise buildings lying in close vicinity in urban areas generates flow
interference effects. The wind-related issues are more complex to comprehend when there is a cluster
of buildings and wind flow over each of these buildings gets affected due to the presence of another.
One of the primary reasons for any physical phenomenon around an earth-fixed bluff body such as a
building is the pressure and its distribution. To understand the significance of wind flow phenomena, it
is necessary to study the pressure distribution around a building model. Experiments have been
conducted in a subsonic wind tunnel to verify the numerically obtained pressure coefficients(Cp) over
a single low-rise building with and without an opening shown in fig.1. Three different wind speeds such
as 10 m/s, 15 m/s, and 20 m/s have been considered during the experimental study. For the numerical
computation of Cp, the wind speed of 20 m/s was taken. The comparison between the experimental and
numerical values of Cp has quite satisfactory. The effect of an opening through the walls at the bottom
of the building and a cluster of prismatic buildings has also been considered for the study. The Cp
distribution around a single building inside a cluster was also noted and compared with the Cp values
for an isolated building.

90
 LES of shock-turbulence interaction in a Bell-shaped Convergent
Divergent Nozzle.

Agneev Roy1 and Somnath Ghosh2

1,2
Department of Aerospace Engineering, IIT, Kharagpur, West Bengal-721302, India
Email: agneevroy951@gmail.com, sghosh@aero.iitkgp.ac.in

Abstract. High-order accurate large-eddy simulation has been carried out for a compressible flow
through a convergent-divergent nozzle with bell-shaped divergent portion. An explicit filtering using
approximate deconvolution method is applied. The nozzle has isothermal walls and circular cross-
section. The incoming flow is a turbulent, subsonic fully developed pipe flow at M=0.4 and friction
Reynolds number 216. An adaptive filter is also used to stabilize the shocks. There is a smooth transition
from subsonic flow to supersonic flow in the convergent section, reaching M=1 at the throat. However,
with the exit to inlet pressure ratio of 0.6 a shock train develops in the bell-shaped divergent section of
the CD nozzle.

91
 A study on Applicability in Super Cavitation with SLBM

Kyungwon Oh1 and Changduk Kong2

1
Complex System and Dynamics Group, Indian Institute of Technology Madras, Chennai-600036,
Tamil Nadu, India
2
Dept. of Aerospace Engineering, Chosun University, S.Korea
Email: kwoh@howon.ac.kr

Abstract. This study is about technical analysis in launching SLBM of North Korea. We expect that
North Korea develop ICBM and SLBM by improving the technique called R-27. Also it is expected that
they attempt to achievement in covertness and ambush by completing technique of cold launching.
Recently, SLBM of North Korea rised 40 ~ 50 m on surface after launching in an underwater when they
showed the scene of firing SLBM. We expect that they actively use not general technique but super
cavitation technique. Also, they might improve the launching technique by doing SLBM launching test.
This type is about that whole rocket is separated two parts and ignited with high velocity and we might
think that 1st rocket is used in solid propellant to maneuver in high velocity in an underwater. After
then, they might use liquid propellant for the long-range ballistic missile.

92
 A Review of Predictive Control for Autonomous Flight Systems

Mahir Dursun
Gazi University, Ankara, 06500, Turkey
Email: mdursun@gazi.edu.tr
Abstract. In autonomous flight systems, the ability to make forecasts and cope with uncertain
predictions is very important subject. There are some forecasts methods to compute real-time optimal
control decisions. The objective is to find a control policy that minimizes a predicted time while
satisfying operating constraintsand handled by optimizing over multiple uncertain forecasts. In this case,
performance index and operating constraints take the form of functions defined over a probability space,
and the resulting technique is called stochastic control technich. This research has focused on predictive
control design methods that systematically handle uncertain forecasts in autonomous and
semiautonomous systems flight over the past 10 years. In this article, we present an overview of the
approach we use, its main advantages, and its challenges for autonomous flight systems. As a result it
has been presented most recent results on predictive autonomous flight control systems. It has been
show how to use efficiently formulate stochastic flight control problems and improve performance in
repetitive tasks.

93
 Comparison of Full-field Solution between Virtual and Experimental
Digital Image Correlation for Model Verification.

Vipin Chandra1 and Pritam Chakraborty2

1,2
Indian Institute of Technology, Kanpur, Uttar Pradesh 208016
Email: chandrav@iitk.ac.in

Abstract. Traditionally, an iterative procedure is used for the calibration of material model parameters
using global response of experiments that develop homogeneous strain/stress fields. The calibrated
model is then used in those applications where the response are heterogeneous in nature depending on
the nature loading and /or structural geometry. Generally, experimental data is affiliated with its inherent
noise, whereas simulation data is much clean. Hence, some discrepancies occur while comparing the
simulation data with experimental data locally. In the present work, a novel proposed procedure of
virtual speckling is developed and verified for von Mises elasto-plastic model on 6000 series aluminium
alloy under uniaxial tension test. Virtual speckled images of random grey intensity are first produced
based on simulation elements and their successive deformation fields, then the local strain field, as well
as global behaviour obtained using Digital Image Correlation (DIC) post-processing algorithm. Finally,
finite element method simulation response and virtual speckled DIC response are compared with
uniaxial tensile test response, which is generated using the same DIC post-processing algorithm to check
the effectiveness of the proposed procedure of virtual speckling.

94
 Effect of viscosity gradient on sperm cell motion in micro-devices

Kathit Shah1, Sumit Kumar2, Sanjay Mane3, Arnab Banerjee4 and Siddhartha Tripathi5
1,2,3,5
Department of Mechanical Engineering, Birla Institute of Technology and Science-Pilani, K K
Birla Goa Campus, Zuarinagar, Sancoale, Goa-403726, India
4
Department of Biological Sciences, Birla Institute of Technology and Science-Pilani, K K Birla Goa
Campus, Zuarinagar, Sancoale, Goa-403726, India
Email: siddharthat@goa.bits-pilani.ac.in

Abstract. Infertility is growing at rapid pace and affecting 8-10 % of couples worldwide. Males are
found to be solely responsible for approximately 20-30 % of infertility cases due to abnormal sperm
parameters. For successful fertilization, the important sperm parameters are progressive motility, sperm
concentration, and morphology. The success rate of assisted reproductive technologies (ART) depends
on the selection of high-quality sperms. Microfluidic devices or lab-on-a-chip (LOC) deviceInfertility
is growing at rapid pace and affecting 8-10 % of couples worldwide. Males are found to be solely
responsible for approximately 20-30 % of infertility cases due to abnormal sperm parameters. For
successful fertilization, the important sperm parameters are progressive motility, sperm concentration,
and morphology. The success rate of assisted reproductive technologies (ART) depends on the selection
of high-quality sperms. Microfluidic devices or lab-on-a-chip (LOC) devices based on ART provides
an excellent opportunity to study and separate high-quality sperms as they closely resemble the natural
selection mechanism involved in the fertilization process. Herein, we experimentally examine and
analyse the motion of sperm cells within microchannels subjected to different viscous environments.
This work presents various results on swimming behaviour of sperm cells with viscosity gradients by
examining their flagellar movement in confined microchannel geometries. The swimming speed of
sperms in different viscous environments is characterized by various kinematic parameters like average
velocity, straight line velocity, and curvilinear velocity. The results of varying viscosity, the influence
on average velocity of sperm cells has also been presented. This study can further be used to sort high-
quality sperm cells based on their swimming behaviour.s based on ART provides an excellent
opportunity to study and separate high-quality sperms as they closely resemble the natural selection
mechanism involved in the fertilization process. Herein, we experimentally examine and analyse the
motion of sperm cells within microchannels subjected to different viscous environments. This work
presents various results on swimming behaviour of sperm cells with viscosity gradients by examining
their flagellar movement in confined microchannel geometries. The swimming speed of sperms in
different viscous environments is characterized by various kinematic parameters like average velocity,
straight line velocity, and curvilinear velocity. The results of varying viscosity, the influence on average
velocity of sperm cells has also been presented. This study can further be used to sort high-quality sperm
cells based on their swimming behaviour.

95
 Measuring deformation in lightweight structures with revamped DIC
system: wind tunnel study

Vivek Khare1* and Sudhir Kamle2

1*,2
Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Uttar Pradesh,
India
Email: vivekkh@iitk.ac.in

Abstract. Introduction Aerodynamic characteristics of lightweight structures are associated with their
structural deformations and viceversa. These deformations play a vital role for maneuverability and
agility in structures like inflatable space antennas, gossamer structures and flapping wing MAVs.
Deformations in ultralight weight structures are due to flexibility attributes and involve multiple shape
changes. Flexibility induced deformations improve aerodynamic performance and assist the structure to
maintain dynamic stability in a wobbly wind environment. Scale-down aerospace structures are
experimentally examined in wind tunnel to address the deformation characteristics. Challenge is to
estimate these deformations which are inadequate to measure with conventional motion sensors or strain
gauges. Digital image correlation based non-contact measurement techniques have been established but
are effective for in-house experiments with small field of view. DIC setup would require precise
calibration every time and can lead to measurement uncertainty. Out of plane structural deformations
also include wind induced shape change such as camber development and trailing edge deformations
along with flexural and torsional deformations. Wind tunnel experiments require far field imaging
system with high depth of field and resolution to capture these deformations. Field of view should also
be considered when the test structure is large and deformations are to be measured at multiple locations.
Methods The aim of this study is to propose a stereovision based revamped DIC system and to evaluate
its effectiveness with far field wind tunnel experiments. The DIC system is equipped with a dedicated
mounting mechanism with two angle fixtures. First is the azimuth rotation disc for targeting along the
length of the wind tunnel test section. The pitch rotation disc is introduced to focus along the height of
the test structure. DIC system is calibrated for camera parameters, pixel resolution and magnification
factor under variable focal length [F]. Based on calibration data, an expression shown in Equation [1] is
derived for magnification factor which can be used to obtain actual structural deformation shown in
Equation [2]. The calibrated setup was installed from outside of transparent test section walls of the
wind tunnel. Precisely aligned stereovision system captures the deformation images during experiments.
Image correlation is performed first with calibration parameters to obtain deformation fields.
m=(20.254/F)*(X-0.081) (1) XPi=ui*m (2) Azimuth and pitch angle rotation are further used to
determine spatial location of any point in the test structure using correlation theory based on Euler angle
transformation. The theory is also used to verify the structural deformation obtained from existing DIC
method. Displacements are first obtained in pixel coordinates (expressed as ui in Equation [2]) using the
transformation matrices obtained for each camera. The coordinates are transformed into actual
displacements (XPi) using the pixel resolution obtained from calibration. Results from existing DIC
system are compared with those obtained from the correlation theory. The suitability of revamped DIC

96
system is investigated from the wind tunnel experiments on lightweight structures. A large inflated
parachute model is tested for its maximum inflated diameter at variable wind speeds. The DIC system
effectively predicted frontal diameter after full deployment. The results are verified by the measurement
of known length of cross diagonals at parachute centre. Another study is based on an ultralight weight
small flapping wing model for which the wing displacement fields are determined during flapping. The
DIC system with appropriate azimuth and pitch rotations, effectively predicted the flapping wing
displacements. The wing displacement fields are used to obtain sectional chord deformations along the
wing span. These deformations obtained from DIC system can be further used to obtain the aerodynamic
forces and moments produced in lightweight structures during wind tunnel experiments. The proposed
DIC system can estimate structural deformations for both lightweight and large scale rigid structures
without frequent calibration.

97
 FOV-constrained 3D impact angle and impact time control guidance

Peng Wang1, Wanchun Chen2 and Zhongyuan Chen3

1,2,3
School of Astronautics, Beihang University, Beijing 100191, China
Email: zhongyuan_chen@buaa.edu.cn

Abstract. For a stationary target, it is necessary for multiple missiles to attack at the same time from
different directions to enhance the damage effectiveness. In this paper, a three-dimensional field-of-
view-constrained guidance strategy is proposed for simultaneously attacking a stationary target, which
can achieve desired impact angle

98
 Parametric perturbation studies on the behaviour of bistable
unsymmetrical laminates

K. S. Suraj1, P. M. Anilkumar2, C. G. Krishnanunni3, and B. N. Rao4

1,2,3,4
Structural Engineering Division, Department of Civil Engineering, IIT Madras, Chennai 600036
Email: ce18d755@smail.iitm.ac.in

Abstract. Multistable composite laminates are ideal candidates for morphing applications due to their
ability to switch between multiple stable states with proper actuation mechanisms. Even though
extensive works have been reported on the analysis and design of the cured shape of unsymmetrical
laminates for morphing application, the effect of small parametric perturbations (in design variables) on
the bistable behaviour is not profoundly assessed in the literature. Based on the numerical model
developed for the analysis of bistable structures, the influences of material properties on the
deformation, and stability behaviour of cross-ply laminates are determined using a set of systematic
parametric studies. The study thus provides a preliminary insight into the propagation of uncertainty
through the system, where the effect of small parametric changes on the bistable behaviour has been
investigated. In this work, design charts exploiting the change in characteristic parameters by altering
the design variables are prepared from the numerical analysis using a commercially available finite
element package, ABAQUS.

99
Insight into the mechanism of drag reduction for a spiked blunt body

Md Gulam Sarwar1, Priyank Kumar2 and Sudip Das3

1,2,3
Department of Space Engineering and Rocketry, BIT Mesra, Ranchi - 835215, India
Email: sarwar251219@gmail.com

Abstract. Blunt body shapes are preferred for nose shape of high-speed aerospace application like
reentry capsule, ballistic missile, planetary probes, etc. with large volumetric efficiency and low heat
distribution on the surface of the body. But these shapes at high-speed flow generate a strong detached
bow shock wave ahead of the body and results in high-pressure regions between body and shock. This
corresponds to a high-pressure drag which requires high fuel consumption. There are many methods by
which drag can be reduced but among them, the spike method is simple and effective for reducing drag
and alleviating heating problems. When a blunt body uses a spike, it reduces drag and heating by the
transformation of a strong bow shock wave into weaker conical shock waves. The spike establishes a
recirculation region ahead of the blunt body helping to reduce its aerodynamic drag and heating which
can subsequently increase the range of flight and reduce fuel consumption.

100
Understanding the Strapon Separation Dynamics and Aerodynamics in
Atmospheric Phase

Ayush Raikwar1, Vidya Gurumurthy2, and Devendra Ghate3

1
B. Tech student, Department of Aerospace Engineering, Indian Institute of Space science and
Technology (IIST), Thiruvananthapuram, Kerala, India
2
Division Head, Aero Combustion Modelling Division, ADSG, Aeronautics Entity, Vikram Sarabhai
Space Centre (VSSC), ISRO, Thiruvananthapuram, Kerala,india
3
Assistant Professor, Department of Aerospace Engineering, Indian Institute of Space science and
Technology (IIST), Thiruvananthapuram, Kerala, India
Email: raikwar.ayush0@gmail.com, g_vidya@vssc.gov.in and devendra.ghate@iisc.ac.in

Abstract. During the flight of a multistage launch vehicle, use of jettisoning systems has been made to
carry away the spent stages once their active lives are over. For a launch vehicle with parallel staging
(strap-on) boosters, these jettisoning systems ensure collision-free separation. For majority of launch
vehicles, these systems are configured by specific springs’ arrangement. The paper aims at deducing the
necessity of a separation system for strap-on separation. The separation motion, with variation in
dynamic pressure, system configurations was studied for two strap-on separation. Separation dynamics
studies (with/without aeroeffects) for single spring force system and two spring force system applied at
different locations were realised along with their influence in the system. The system configuration for
single spring system was discussed and the advantages of having two spring separation system were
presented. The optimum configuration of two spring force system for the considered two strap-on
Launch vehicle was found out along with discussion on various other spring locations configurations.
3D CFD simulations were conducted using ANSYS FLUENT on a similar simplified two strap-on
launch vehicle at a typical separation event to understand the interference aerodynamics of the
separation system and study the effect of various parameters involved in the strap-on separation
aerodynamics.

101
 Probabilistic Mixed Mode Stress Intensity Factors of Single Edge
Cracked Laminated Composite Plates Using Stochastic Extended Finite
Element Method

Shailesh Palekar1, Achchhe Lal2, Prasad Patare3 Atul Joshi4 and Prasad Bojage5
1,3,4,5
Associate Professor, Department of Mechanical Engineering, SRES’s Sanjivani College of
Engineering, Kopargaon-423601, India
2
Assistant Professor, Department of Mechanical Engineering, SVNIT, Surat-7, India.
Email: plekarsahileshmech@sanjivani.org.in, plekarsahileshmech@sanjivani.org.in

Abstract. The second order statistics of mixed (first and second) mode stress intensity factors (MMSIF)
of single edge cracked orthotropic composite plates subjected to uni-axially applied tensile, shear and
combined loading by using stochastic extended finite element method (SXFEM) is presented in this
paper. A stochastic method based on the second order perturbation technique (SOPT) and direct Monte
Carlo simulation (MCS) combined with the interaction integral (M-integral) in the framework of XFEM
is used in the present analysis for computation of mean and coefficient of variance (COV) of MMSIFs.
The randomness is considered in the system properties such as material properties, which are modelled
as random input parameters.

102
 A robust fifth-order WENO-Z type scheme with improved accuracy at
second-order critical point

Yiqing Shen1, Shiyao Li2 and Ke Zhang3

1,2,3
LHD, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
Email: yqshen@imech.ac.cn

Abstract. By introducing a global smoothness indicator, Borges et al. (J. Comp. Phys., 2008) proposed
a weighting method for constructing a class of weighted essentially non-oscillatory schemes (WENO-Z
schemes). The fifth-order WENO-Z scheme can enhance the order of convergence at the first-order
critical point and has less dissipation at shocks. However, at the second-order critical point, the
convergence order of the original fifth-order WENO-Z scheme is only second order. Many efforts have
been devoted to improve the accuracy of the WENO-Z schemes at high-order critical points. However,
some of them don’t meet the physical requirement of dimension consistency and hence result in less
robustness. This paper presents a novel weighting method for constructing WENO-Z type scheme. An
adaptive function of local smoothness indicators of candidate sub-stencils is designed to replace the
constant 1 used to calculate the un-normalized weights of the original WENO-Z scheme. The function
can adaptively approach to a small value if the global stencil contains a discontinuity and approach to a
large value if the global stencil is sufficiently smooth. The square of the approximation of the fourth-
order derivative, which is the highest-order derivative can be approximated on a five-point stencil, is
suggested as the global smoothness indicator. Numerical results show that the new WENO-Z type
scheme can achieve fifth-order accuracy at first-order critical points and fourth-order accuracy at
second-order critical points. The new scheme has low numerical dissipation and is robust for solving
problems with shocks. This research work was supported by the National Natural Science Foundation
of China under Grants 11872067, 91852203, and 11902326.

103
 Three dimensional computational investigation of the geometric design
of delta-type vortex generators deployed in finned tube arrays

Amit Arora1 and PMV Subbarao2

1
Department of Mechanical Engineering, MNIT Jaipur, Jaipur-302017, Rajasthan, India,
2
Department of Mechanical Engineering, IIT Delhi, New Delhi-110016, India
Email: amit.mech@mnit.ac.in

Abstract. Incorporating vortex generators in the finned tube arrays is an effective way of modifying the
flow field, thereby improving the heat transfer coefficients. But the positioning of vortex generators in
the aforementioned systems is not sacrosanct due to various constraints. Since there is a strong
correlation between the geometric design of the vortex generators and the resulting flow modifications,
the loss in performance due to locational shift may be compensated by varying the geometric design.
This numerical investigation discusses the effect of geometric changes of delta-type generators on the
flow modifications, and the resulting thermal augmentations. The vortex generators are erected at a
preferred location, and four different aspect ratios (viz. 1.5, 1.0, 0.75, and 0.5) are considered for a
detailed study. The changes in the flow structures are analyzed by studying the velocity vectors as well
as contours, which manifest in the form of higher Nusselt numbers. The span averaged local Nusselt
number is found to undergo a maximum augmentation of 133.9% whereas the maximum increase in the
average Nusselt number equals 125.1%.

104
 Failure Mechanisms of SMA Reinforced Composites under Impact
Loading

Vagish Mishra1, Ashish Mishra2, Luv Verma3 and Anindya Roy4

1
Dept. of Aerospace Engineering, Indian Institute of Technology (IIT) Madras, Chennai, Tamil Nadu,
600036, India
2
Dept. of Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun,
Uttarakhand, 248007, India
3
Dept. of Applied Mechanics, Indian Institute of Technology (IIT) Madras, Chennai, Tamil Nadu,
600036, India
4
Dept. of Engineering structures, Bio based structures and materials group, Delft University of
Technology, Mekelweg 5,2628 CD Delft, Netherlands
Email: vagishdm@gmail.com

Abstract. In the past few years, pseudo-elastic shape memory alloy (PE-SMA) has surfaced as one of
the potential secondary materials that can be embedded in composites to dissipate a higher amount of
energy in comparison to plain composites. Therefore, the aim of this paper is to illustrate the damage
modes in GFRP composites embedded with pseudo-elastic shape memory alloy (SMA) under two
different types of loading, quasi-static indentation and high-velocity ballistic impact. In both the cases,
impact loading was applied until complete material failure.

105
 Numerical Analysis of Structural Design Result for UAV applied to
Composite Structure considering on Self-Healing Method

Hyunbum Park1 and Yonggyu Lee2

1,2
School of Mechanical Convergence System Engineering, Kunsan National University, Rep. of Korea
Email: swordship@kunsun.ac.kr

Abstract. In this work, structural design and numerical analysis for air intake of aircraft engine applied
to composite materials. The investigation on structural design load and aerodynamic configuration of
target structure was carried out. The distributed pressure load and acceleration condition was applied to
structural design. In order to investigate the structural design result, finite element analysis was
performed. The stress, deformation and buckling analysis for structural safety evaluation was carried
out. Finally, it was confirmed that the air intake through structural design result is safety.

106
 A homogenized crystal plasticity model for lamellar transformed β
colony of titanium alloys

S. Mustafa Kazim1, Kartik Prasad2, and Pritam Chakraborty3

1,3
Department of Aerospace Engineering, Indian Institute of Technology Kanpur, India,
2
Defence Metallurgical Research Laboratory, DRDO, Hyderabad, India
Email: mustafa@iitk.ac.in

Abstract. Titanium alloys are widely used in aero-engines because of their high specific properties,
excellent corrosion resistance and strength retention at moderate to high temperatures. The thermo-
mechanical route followed in design of these alloys results in a microstructure consisting of primary α
grains having a Hexagonally Closed Packed (HCP) crystal structure and transformed β colonies having
a lamellar microstructure with alternating laths of HCP and Body Centered Cubic (BCC) phases.
CPFEM (Crystal Plasticity Finite Elements Method) simulations are widely used to obtain the
macroscopic properties of polycrystals as well as design of microstructure. However, CPFEM
simulations for α + β Ti-alloys becomes computationally intractable as the length scales of the lamellar
microstructures within the transformed β colony are considerably smaller than that of the primary α
grains. To mitigate this problem homogenization of the lamellar colonies is necessary and has been
proposed in this work. The homogenized model ensures traction balance and strain compatibility at the
lath interface. The semi-coherent nature of the lath interface and the interaction between the two phases
is also included in the analysis for an accurate prediction. The results show a better prediction of the
homogenized response for the transformed β colony than the existing models.

107
A comparative study of recent phase-field implementations for fracture
prediction in solids

Sidharth Pc1 and B.N Rao2

1,2
Department of Structural Engineering, Indian Institute of Technology Madras, Chennai 600036,
India
Email: bnrao@iitm.ac.in

Abstract. The computational modeling of failure mechanisms in solids due to fracture based on sharp
crack discontinuities is found to suffer in situations involving complex crack topologies. This can be
overcome by diffusive crack modeling based on the introduction of a crack phase field. Phase-field
modeling of fracture is able to effectively model crack propagation with ease compared to numerical
methods based on a discrete crack model, especially for complex crack patterns. Despite the versatility
in modeling complex crack topologies, phase-field fracture models are usually implemented in in-house
codes, greatly restricting their potential applications. Thus, it is of vital importance to implement the
model in widely used commercial software packages like ABAQUS. In the present study, two of the
recent implementations of the phase-field model are evaluated. The focus of the discussion is on the
robustness of these models and on their performance compared with respect to several modeling choices
such as length scale parameter and the finite element mesh.

108
 Stably electrospraying Concentrated aqueous solution with outer ionic
liquid

Yufeng Cheng1, Jinrui Zhang2, Guobiao Cai3, and Weizong Wang4

1,2,3,4
Advanced Space Propulsion and Energy Laboratory (ASPEL), School of Astronautics, Beihang
University, Beijing 100191, People’s Republic of China
Email: wangweizong@buaa.edu.cn

Abstract. Concentrated aqueous solution has been proven difficult to be electrosprayed due to its low
viscosity, high volatility and large surface tension, while ionic liquids have been widely used in
electrospray. In this paper, we successfully electrospray concentrated sodium chloride aqueous(NaCl)
solution thorough coating it with a thin layer of ionic liquid using coaxial capillary. In this approach, we
not only extend the range of the flowrate and the applied voltage where cone-jet mode of NaCl solution
occurs, but also increase the spray current of the ionic liquid. The thin layer of ionic liquid largely
changed the surface characteristic and weaken the strong electric field inside the liquid surface, which
avoids the discharge of the NaCl solution and facilitate the formation of the compound liquid cone.
During the experiment, five possible modes, dripping mode, interceptive mode, intermittent mode,
compound cone-jet mode and electro-discharge mode are observed as applied voltages increases. The
spray current increased more rapidly with the flowrate of NaCl sulotion than that of ionic liquid. Besides,
the underlying mechanism of how the compound liquid cone remain stable has been discussed and
analysed thoroughly.

109
 Based on Natural Frequencies, Crack Analysis of Fixed Support Fibre
Glass Composite Beam

Vaibhav Suryawanshi1, Shailesh Palekar2, Prasad Patare3, Prasad Bojage4

and Atul Joshi5
1,2,3,4,5
Department of Mechanical Engineering, Sanjivani College of Engineering, Kopargaon,
Maharashtra-423603, India

Abstract. A Fibre reinforced composites (FRCs) are a type of composite material that consists of a
plastic matrix reinforced by tiny thin fibres with high tensile strength and flexural modulus. Fibre
reinforced polymer (FRP) or glass reinforced plastic are other names for it (GRP). FRCs are widely
utilised in aircraft and space applications, marine, automotive, and construction sectors. The E-Glass
epoxy resin composite beam was chosen for this study because of its high strength, rigidity, low cost,
and ease of availability. The main goal of this research is to find out if a crack exists in a fibre glass
composite beam. The crack analysis is required in order to assess the fracture prior to failure, which has
an impact on the dynamic properties of the structure, such as natural frequencies and modes of vibration.
To examine the free vibration response of composite beams, a numerical research utilising finite element
is carried out in this paper. FFT analysis and FEA validation are required to comprehend the
phenomenon of crack generation and its approximate placement.

110
Drag and flow analysis for a car model with different vortex generators

Nirmith K P1, Chandrashekhara K L2, Yogish H G3, B Shrikant4 and B. Sudarshan5

1,2,3,4,5
Department of Mechanical Engineering, B.M.S.College of Engineering, Bengaluru – 560019,
Karnataka, India

Abstract. The fluid structure interaction on the rear side of the automobile vehicle induced flow
separation leading to accentuate the drag force. The automobiles which are propelling from the velocity
of 20 m/s experiences the drag force. Hence, most of the automobiles inevitably encounter the problem
of flow separation and higher fuel consumption to encounter the drag force. To reduce the pressure
change, induced by the flow separation, across the vehicle the vortex generators (VG) are used and well
reported in the literature. There is a lacuna of material on optimization and physical mechanism of vortex
generator geometries leading to effective reduction of induced drag. In the present study, using vane
type, wedge type and hemispherical type of VGs, the flow mechanism, distinctive flow features and
related operating mechanism affecting the drag parameters will be analysed computationally using CFD
and validated experimentally using a wind tunnel facility. The preliminary CFD study is presented here.

111
Experimental Investigation of Siphon breaker for Small Pipe breaks

Samiran Sengupta1, Vijay K Veluri2 and Sujay Bhattacharya3

1,2
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai
3
Reactor Projects Group, Bhabha Atomic Research Centre, Mumbai
Email: : samiran1sengupta@gmail.com

Abstract. Siphoning application are quite useful to cause liquid to flow uphill against gravity without
being pumped for emptying or transferring liquid from one tank to another. However, in some
applications siphoning should be avoided. A typical application is found in Pool type nuclear research
reactors where the reactor pool water should not get drained through siphoning in case of a break in the
reactor system piping. Else the minimum reactor core submergence in the reactor pool required for
cooling/ shielding of the core may not be ensured. The reactor core can no longer be cooled through
natural circulation using the pool water which act as a large heat sink even during reactor shut down
condition for decay heat removal. Therefore, siphon breakers are important to keep the reactor safe
during LOCA scenario. Size of siphon breaker depends on the system piping size, elevation difference
between reactor pool water level and break location, size of break, system resistance etc. Experiments
were carried out to understand characteristics of siphon breaker for small size pipe breaks relevant to
research reactors. A computer program has been developed to predict the undershooting height based
on different empirical models of air-water flow through piping. The effect of the various break sizes on
the undershooting height is presented in this paper.

112
 Prediction and Prognosis of structural degradation by ML and DL
algorithms

Mahantayya K Hiremath1, S K Maharana2 and Venugopal M M3

1,2,3
Department of Aeronautical Engineering, Acharya institute of Technology, Bengaluru,
Email: mahantayya@acharya.ac.in

Abstract. . Aircraft is the flying machine consisting of many structural components and assemblies. It’s
important to know the structural health as it’s related to the airworthiness of an aircraft. So to determine
the health status we have many tools which mechanically give us the life cycle prediction of the
structure. The research is proposed to find the structural deterioration by the Ml and Dl algorithms. The
research work is to Analyzing the structure with asuitable instrument to find the deterioration or damages
and building data, storing data and training the system for the analysis. Structuring data and training the
system with asuitable model. Using DL and ML algorithm, predicting health status. The scope of the
research could be used in the following fields. • It could be new innovation in the structural health
assessment by Dl and ML • It could reduce the millions of rupees on regular inspection, checks and
repairs. Hence reduces the maintenance cost. • Could be a substitution for FEA and alternate for physical
instrumentation on board. • Could be used to predict future of the structural life of an aircraft.

113
 Numerical investigation of discharge mechanism and plasma behavior
in an external discharge plasma thruster

Shuwen Xue1, Yuanyuan Gao Wei Liu2, Yifei Li3, Guobiao Cai4 and Weizong Wang5
1,2,3,4,5
School of Astronautics, Beihang University, Beijing, 100191, China
Email wangweizong@buaa.edu.cn

Abstract. External discharge plasma thrusters (XPTs) have been proved as efficient as conventional
Hall thrusters. In that discharge channels are eliminated in XPTs, the ionization process occurs outside
the thruster. Accordingly, they have the advantages of low wall erosion rate and long lifetime. Therefore,
XPTs can meet the high precision orbit maneuver requirement of cube-satellites and micro-nano satellite
networking systems. In this paper, a two-dimensional axisymmetric particle-in-cell/ Monte Carlo
Collision (PIC/MCC) model for the discharge region is developed for an XPT, which adopt the real
configuration of the literature reported XPT. The transient discharge process and the influence of
operating conditions on the discharge process in the ionization chamber are presented for the first time.
The influence of electron anomalous Bohm collision on the discharge process is studied to better
understand the electron transport mechanism and the discharge process. Thruster performance indicators
such as thrust, discharge current, the second electron emission rate, and mass utilization efficiencies are
calculated. The calculation results are compared with literature experimental data under similar
conditions and good agreements are reached. The simulations interpret the single-peak property
obtained from experiment. These results lay a foundation for further optimization of low-power Hall
thruster design in the future.

114
 Performance Analysis of Circular and Lemon Bore Hydrodynamic
Journal Bearing Considering Surface Roughness and Shear Thinning
Effect

Kuldeep Narwat1, Vivek Kumar2, Simran Jeet Singh3, Abhishek Kumar4

and Satish C Sharma5
1,4
Mechanical Engineering Department, School of Technology, PDEU Gandhinagar, India
2,3
Mechanical Engineering Department, NSUT Delhi, India
5
Mechanical Engineering Department, IIT Roorkeei, India

Abstract. This article presents numerical simulations of rough surface circular and lemon bore journal
bearing operating with non-Newtonian shear thinning lubricant, in turbulent regime. Numerical
simulations of bearing have been performed by finite element solution of modified Reynolds equation
for non-Newtonian lubricant. Rabinowitsch fluid model is used to define the shear-thinning nature of
lubricant. Surface roughness has been modelled using the average film thickness model proposed by
Patir and chang. The effects of orientation of surface roughness, turbulent flow (Reynolds number) and
fluid flow coefficient are investigated on film pressure, minimum film thickness, frictional torque,
stiffness and damping coefficients of bearing. It has been found that lemon bore bearing outperforms
circular bearing in terms of above-mentioned performance indices. Turbulent flow condition is a notice
to provide a higher value of minimum film thickness, stiffness and damping coefficients but at the
expense of higher frictional torque. Roughness on the bearing surface tends to offer a high value of film
thickness but also enhances frictional torque. It has been found that the transverse orientation of surface
roughness is favourable for a higher value of stiffness coefficients, whereas the longitudinal orientation
of surface roughness is favourable for better damping capabilities in the journal bearing system.

115
 Transient Low Velocity Impact Response of Functionally-Graded
Rectangular Plates – A Finite Element Approach.

Ritwik Mandal1, Tanmoy Bandyopadhyay2, and Amit Karmakar3

1
Mechanical Engineering Department, Heritage Institute of Technology, Kolkata-700107, India
2,3
Mechanical Engineering Department, Jadavpur University, Kolkata-700032, India
Email: ritwiknitdgp@gmail.com

Abstract. This work presents the low-velocity impact response of functionally graded rectangular plates
using finite element methods. Functionally-graded materials are advanced materials in which the
material properties vary continuously along the thickness. Analyses are performed for an impact event
that occurs between a spherical projectile and a cantilever functionally-graded plate for different FGM
plates of varying constituents. First order shear deformation theory (FSDT) is implemented to derive
the governing equations of motion. The modified Hertzian contact law is employed to calculate the
contact force resulting from plastic indentation. The FGM properties are derived based on the
established power-law accounting for the graded characterization of the material properties across the
thickness direction. The time dependent equations are solved by the Newmark’s time integration
scheme. An eight noded iso-parametric shell element is employed to derive the stiffness matrices of the
FGM plate. The transient response of FGM plates are obtained for different FGM constituents
(Al/Al2O3, Al/ZrO2, SUS3O4/Si3N4, Ti-6Al-4V/Al2O3 and Ti–6Al–4V/Aluminium oxide) by
varying parameters like power law index keeping plate-thickness ratio constant.

116
An aircraft wing structural layout and cross-sectional size optimization
design

Hai Huang1 and Jiayi Fu2

1,2
School of Astronautics, Beihang University, Beijing 100191, China

Abstract. This work presents an aircraft wing structural optimization design, in which both the layout
of wing rib and the cross-sectional sizes of components were considered as design variables. The wing
structure consists of composite shells and beams, which can be taken as a typical complex structural
system with a certain scale. This study could be understood as an engineering application of our former
proposed method. Numerical results showed that the final design could obviously reduce the weight of
the wing structure, which looks quite reasonable. The efficiency of the optimization is satisfied, and the
required number of structural analysis even comparable with pure size optimization, which
demonstrated the practical applicability of the method.

117
 Damage Analysis of Multi-layered Composite Structures

Kartikeswar Dwibedy1 and Anup Ghosh2

1,2
Aerospace Engineering Department, IIT Kharagpur, India

Abstract. This work proposes a mathematical model for analysis of damage in multi-layered composite
structures in different service conditions. At first the growth of damage in the form of delamination and
matrix crack can be predicted numerically. This study also includes propagation of damage with or
without matrix crack under application of static uniformly distributed load on mathematical model of
16 layered square plate and spherical shell. It is an incorporation of two methods, Virtual crack closure
technique and extended layerwise method for this simulation. The extended layerwise method is used
for simulation of damage like delamination and matrix crack in multi-layered composite structures while
Virtual crack closure technique is used for determination of strain energy release rates in different
service conditions. An algorithm is also proposed for propagation of arbitrary and changing shape type
damages.

118
 Vibroacoustic analysis of simply supported and clamped functionally
graded sandwich plates under transient loading

Avnish Pandey1 and K V Nagendra Gopal2

1,2
Department of Aerospace Engineering, Indian Institute of Technology Madras, Chennai, 600036,
India
Email: ae15d007@smail.iitm.ac.in

Abstract. Sound radiation analysis of simply supported and clamped functionally graded sandwich
plates under transient loading is reported in this work. Square sandwich plate configurations of different
thickness ratios are modelled using the first-order shear deformation theory to incorporate the effects of
transverse shear and rotary inertia. The structural system matrices of the functionally graded sandwich
plate are computed using the finite element method. The radiated acoustic pressure in the far-field is
determined using the time domain Rayleigh integral which is solved numerically by an elementary
radiator approach. The time history of the structural response is obtained using the Newmark Beta time
marching scheme. The effective material properties of the sandwich plate are derived by considering an
approximate laminated model in MATLAB where the Poisson’s ratio of the constituents of the sandwich
is assumed to be constant. The influence of the volume fraction index and the thickness ratio on the
transient vibroacoustic response of different sandwich configurations is investigated by a detailed
parametric study.

119
 Third-Order Shear Deformation Theory for the Low-Velocity Impact
Response of 3D Braided Composite Plates

Pabitra Maji1 and Bhrigu Nath Singh2

Department of Aerospace Engineering, IIT-Kharagpur, India
Email: pabitraaero@iitkgp.ac.in, bnsingh@aero.iitkgp.ac.in

Abstract. Advanced 3D braided composites are increasingly used in the assorted fields for their distinct
characteristics. The equivalent Young's modulus of the 3D braided composite is predicted based on the
volume average method (VAM) using Bridging theory. A third-order shear deformation theory (TSDT)
with twelve degrees of freedom per node is implemented for the Low-Velocity Impact Response of the
Three Dimensional Braided Composite Plate. In this theory, the transverse displacement is the function
of the plate thickness coordinate, which can predict accurate results of thick plates. The present results
are generated based on the finite element procedure. The modified Hertzian contact law is implemented
to calculate the contact force of the impact phenomenon. The Newmark beta time integration is utilized
to solve the time-dependent governing equations. Various comparison studies are carried out to judge
the accuracy of the present models. numerous parametric studies are carried out on contact force, central
displacement, impactor displacements, such as the effect of the initial velocity of the Impactor, braided
volume fractions, braided angle, thickness ratio, and boundary conditions.

120
 Design and analysis of thermal control system for SSS-1 satellite

Shenyan Chen1, Xingwang Yan2 and Shuchong Wang3

1,2,3
Department of Aerospace Vehicle Technology, Beihang University, Beijing 102200, China
Email: chenshenyan@buaa.edu.cn

Abstract. According to the space environment and structure characteristics of SSS-1 microsatellite, the
thermal control problem under limited thermal control resources was solved. Firstly, based on the outer
space hea t flow in orbit, combined with the requirements of satellite missions and thermal control, the
design idea of passive thermal control as the main and active thermal control as the auxiliary is
determined. Then, according to the overall layout of the satellite and its own characteristics, the
isothermal design of the whole and the local thermal design of the key parts are adopted, and the finite
element thermal analysis model of the satellite is established to calculate the temperature distribution.
Finally, outside the ground simulation including heat flow, black background in low temperature and
vacuum environment, such as satellite space environment, design and carry out the whole vacuum
thermal balance test, the test results show that: under the extremely cold and hot conditions, satellite
components temperature can satisfy the requirements of design index, effectively solve the SSS - 1
satellite heat dispersion and heat preservation problem, achieve the effective control of the entire satellite
temperature.

121
 An analytical approach to sense the presence of damage through
electro-mechanical impedance (EMI) response for a step-lap joint

Umakanta Meher1 and Mohammed Rabius Sunny2

1,2
Indian Institute of Technology Kharagpur, Kharagpur, West Bengal, 721302, India

Abstract. The present work involves the development of an analytical model to sense structural
damages using EMI response of the structure. The impedance responses of a PZT-host structure with
single damage present have been obtained through the developed analytical model employing Euler-
Bernoulli’s beam theory. The analytical model is validated with ANSYS model for a pristine state
aluminium step-lap joint with a PZT patch connected to it. Disbonds present inside the structure at
different areas are considered as the damage here. The impedance responses of the step joint at the PZT
transducer location have been obtained through the developed analytical model for different damage
scenarios. The results obtained through the comparative assessment of the impedance responses
provided some reliable information about the damage status of the structure which in turn describes the
applicability of the analytical model to identify the structural damages employing EMI method.

122
 Sensor/actuator position optimization for large size structure using
multi-objective optimization

Jianhongyu Li1, Hai Huang2 and Shenyan Chen3

1,2,3
School of Astronautics, BEIHANG University, Beijing 100191, PR China
Email: hhuang@buaa.edu.cn

Abstract. With the increasing size of spacecraft in orbit, or the increasing size of additional flexible
structures (e.g., solar sails, antennas) due to increased performance targets, the impact on the spacecraft's
attitude or pointing performance that may be caused by vibrations in space from flexible structures is
coming to the fore. Adding intelligent units containing sensors and actuators into the flexible structure
to form an intelligent structure is an effective way to control the vibration of the flexible structure. The
number of smart structures needs to be strictly controlled due to the mass constraint of the spacecraft in
orbit, the energy cost constraint, and the computational cost constraint of the on-board computer. To
provide more effective vibration suppression, the position of sensor/actuator should be optimized. The
objective function of the sensor/actuator position optimization should be the performance index of the
control system, rather than the mechanical properties in a conventional structural optimization problem.
Many scholars have proposed various objective functions. The structure optimized in this paper is a
large size truss structure and there are several characteristics should be considered when building the
optimization model and making the optimization calculation. First, the structure is complex, and the
impact of sensor/actuator placement of the structure should be considered. During the optimization
process, the structural finite elements need to be rebuilt and structural analysis needs to be performed
each time the position of the sensor/actuator changes. Second, the number of sensor/actuator and the
number of positions that can be placed sensor/actuator both are large. This leads to a huge number of
options for sensor/actuator distribution. And at the same time, there exits the possibility that some
different sensor/actuator distribution has the same or similar control effect. Finally, the control method
also affects the final optimization results. In this paper, we have taken several steps to ensure that the
optimization can be completed successfully. We build the linear system based on the eigenvalues and
the eigenvectors generated by modal analysis. Modes are selected according to the frequency band to
be considered. The method of modal reanalysis was introduced to obtain the new eigenvalues and
eigenvectors after a small change in the structure by relatively much smaller calculations compared with
rebuild the FEM and modal analysis. We choose multiple objective functions, which are divided into
two classes. One class of objective functions is independent of the control method including control
force input energy maximization and sensor output energy maximization. The other class is related to
the control method including total system energy storage maximization. Two classical control methods,
the collocated negative feedback and LQR, are chosen in building the objective function. Several
constraint functions are considered such as controllability/observability, maximum control voltage,
complex modal damping ratio. The multi-objective optimization problem can be established. Multi-
objective genetic algorithm is chosen in this paper. Let the structure have n positions where
sensor/actuator can be arranged and use a binary string of length n to create the design variables. 1

123
means the sensor/actuator is arranged while 0 means no sensor/actuator is arranged. The number of
sensors/actuators constraint is a constraint that strictly cannot be violated. When the number of
sensor/actuator selectable positions is large, the conventional crossover and variation functions in the
genetic algorithm yield a low probability that the number constraint is satisfied by the offspring. This
can lead to a large number of invalid calculations, and for large size structures, the computational cost
of each optimization calculation is expensive. So, we also design a new crossover improved from
uniform crossover, and mutation function. Let the two individuals of the parent generation have m codes
that are different. There is 2^m species of individuals gained by consistent crossover and most of them
do not satisfy the constraint. We randomly select m/2 of the m different codes and assign a value of 1
to them and assign 0 to the other m/2 positions. This ensures that the number of sensors satisfies the
constraint and, at the same time, that the probability of the children's codes coming from the codes of
the two parents is the same. We randomly exchange the coding information at two different positions in
the individual code to achieve individual mutation. By using the crossover and the mutation can make
all individuals satisfy the number of sensors constraint throughout the optimization process. A
sensor/actuator position optimization work for a large flexible structure of 50-meter size, whose optional
positions could reach more than 200 was done and a set of sensor/actuator layout solutions was obtained.
And this is the basis for control system design in future.

124
 Dynamic Modelling of a Porous Functionally Graded Rotor-bearing
System for Different Temperature Distributions

Aneesh Batchu1, Bharath Obalareddy2 and Prabhakar Sathujoda3

1,2,3
Bennett University, Mechanical & Aerospace Engineering, Greater Noida, Uttar Pradesh, India
201310

Abstract. In high-temperature environments, delamination of layers occurs in fibre reinforced

composites due to the development of inter-laminar stresses between the layers. Therefore, the
traditional composites are substituted by functionally graded materials (FGMs) to mitigate the problems
of delamination, residual stresses and debonding for better structural performance. FGMs are non-
homogeneous micromechanical composites that are generally made from using different phases of metal
and ceramic. High mechanical strength of the metal and elevated thermal resistance of the ceramic
influence the structural performance of the functionally graded (FG) rotors/structures. Modelling of a
porous functionally graded rotor-bearing system has been developed for various radial temperature
distributions such as linear, non-linear, and sinusoidal to compute the natural frequencies. An FG rotor-
bearing system, consisting of an FG shaft, uniform steel disc and linear isotropic bearings shown in Fig.
1, is considered in the present work. Power-law is used to assign the material properties along the radial
direction of the porous FG rotor. Material properties and temperature are varied only across the cross-
section of the porous FG shaft. By considering the effects of translational inertia, rotational inertia, and
transverse shear deformations, a two-nodded porous FG shaft element with four degrees of freedom on
each node (two translational and two rotational) has been developed using the finite element method
(FEM) based on Timoshenko beam theory (TBT). An FEM code has been developed to compute the
elemental mass and stiffness matrices of porous FG shaft. Fig.1. An FG rotor-bearing system A metal-
ceramic FG shaft, whose inner core is composed of Stainless Steel whereas the outer layer is made of
Zirconia, is considered to analyse the porous FG rotor system's natural frequencies for different
temperature distributions to validate the modelling. An FE code is developed in Python to calculate the
natural frequencies of the porous FG rotor-bearing system. The code validation has been carried out to
check the correctness of the code. The natural frequencies of porous FG rotor-bearing system are
computed at ΔT = 600 for different power-law indices, volume fractions of porosity and temperature
distributions. Since the material properties of the FG rotor decrease with an increase in the power-law
index and volume fraction of the porosity, the stiffness of the porous FG shaft is decreased.
Consequently, the natural frequency of the porous FG rotor-bearing system is also decreased. For 0 ≤ k
< 1, the natural frequency of the system is higher compared to other temperature distribution types when
the temperature is distributed using sinusoidal temperature distribution (STD). However, for k ≥ 1, the
natural frequency is the highest when the temperature is distributed using the non-linear temperature
distribution law.

125
Vibration of a damped Euler-Bernoulli cantilever beam with a tip mass

Khogesh K Rathore1 and Saurabh Biswas2

1,2
Mechanical Engineering Department, IIT Jammu, Jammu, India 181221,
Email: 2019rme0030@iitjammu.ac.in

Abstract. We study vibrations of a hysteretically damped Euler-Bernoulli cantilever beam with lumped
mass at the free end. The damping is modelled with a scalar rate-independent hysteresis. We derive
Lagrange’s equations for the modal coordinates. Equations include discrete hysteretic states. When a
single mode dominates, the free vibrations decay exponentially, and when multiple modes are active,
higher modes decay relatively faster. With harmonically forced, lightly damped responses of the beam
are studied using a frequency sweep and a shooting method.

126
 Design and Performance Analysis of Axial Flow Wind Turbine for
Household Applications

Dr. Venkatesu Sadu1, Dr. Pol Redy Kukutla2, Dr. Syamsundar C3 and Dr. Sivaiah P.4
1,2
Department of Mechanical Engineering, Annamacharya Institute of Technology and Sciences
(Autonomous), Rajampet, Andhra Pradesh, India
3
Department of Mechanical Engineering, Narasimha Reddy Engineering College (Autonomous),
Maisammaguda Medchal, Telangana, India
4
Department of Mechanical Engineering, CMR Engineering College (Autonomous), Medchal,
Telangana, India
Email: polireddyk01@gmail.com

Abstract. The rural territories are confronting inconvenience because of absence of power from years.
To defeat this trouble and give power through wind vitality is the best option source to deliver the power.
The primary goal of present research is to plan and advancement of axial flow wind turbine with 3-
blades rotor (120̊ apart each) with gearing system to produce power. The kinetic energy of wind strikes
the blades of rotor tends to rotate and this wind energy converts into mechanical energy by gearing
system and the mechanical energy further converts into electrical energy with help of dynamo and stores
in the battery and it will be useful for the household applications. In this paper the plan, improvement
and execution examination analysis of the wind turbine with 3-blades rotor system has been explained
briefly and the experimental results have been compared with analytical results

127
 Performance assessment of five probe flow analyser suitable for wind
tunnel calibration

Akhila Rupesh1, Sanas Uthaman2 and J V Muruga Lal Jeyan3

1,3
Department of Aerospace Engineering, School of Mechanical Engineering, Lovely Professional
University, Phagwara, Punjab, India- 144411
2
Cryogenic Engineering Centre, Indian Institute of Technology Kharagpur, West Bengal, India-
721302

Abstract. In the field of inviscid fluid flow studies, theoretical concept has to be developed even more.
In order to make it possible, it is very important to supplement the concepts with strong experimental
results. While performing experimentation, various accepts of design can be determined with factors
influencing the and also required modification can be recommended in a more systematic and economic
manner. Also, the aim objective of experiment is to extend the underlying theory and to produce new
designs with improvements that can be great support to the advancement in technology. In experimental
analysis, wind tunnels are used for the flow analysis over a flying object to be tested. Analyzing the
flow plays a predominant role in aerodynamics study. The flow in the test section has to be uniformly
streamlined and has to be parallel to the axis of the wind tunnel. The change in flow properties inside
the tunnel with respect to the time should be negligible. So, before conducting a test process, calibration
of wind tunnel has to be done. Normally, calibration of subsonic wind tunnel is done by the Pitot static
tube. It has the limitations of deprived accuracy and misalignment of probe with the flow direction.
Therefore, new calibrating instruments are proposed by overcoming the limitations of Pitot static tube.
In this paper, experimentation using wind tunnel has been discussed and the truth flow analysis of a
low-speed open circuit wind tunnel has been recorded using a five probe flow analyser respectively.
Also, the results obtained have been compared with the data obtained using a pitot static probe.

128
 Study of evolving regular water-waves under steady wind forcing

Santosh Kumar Singh

School of Mechanical Engineering, SRM Institute of Science and Technology, Kattankulathur-603203,
Chennai, India

Abstract. Numerical simulations of wavemaker-generated waves evolving under steady wind forcing
are presented. The computational model accounts for effects of nonlinearity, wind input, and dissipation,
as well as for the stochastic nature of wind-waves. The accuracy of simulations is assessed for a range
of wavemaker forcing frequencies and amplitude by comparison of the numerical results with detailed
measurements performed in a wind-wave tank

129
 Equilibration of Van der Waals liquid drop with vapour in smoothed
particle hydrodynamics

P. C. Harisankar1, C. F. Sagar Zephania2, Tapas Sil3

1,2,3
Indian Institute of Information Technology, Design and Manufacturing, Kancheepuram,
Department of Physics, Tamil Nadu, 600127, India
Email: phy18d003@iiitdm.ac.in

Abstract. Smoothed particle hydrodynamics (SPH) is a Lagrangian based mesh free method, which is
useful to model high deformation dynamic problems. This article presents a liquid-vapour static
equilibrium model in SPH considering Van der Waals equation of state. A hyperbolic shaped kernel
function and variable smoothing length is considered along with a periodic boundary condition to model
liquid drop-vapour coexistence for different vapour densities. Effect of the existence of the vapour on
the coefficient of surface tension is studied.

130
 Design and development of a piezoelectric XY micro-displacement
scanning stage

Xiaoyan Zhang1, Weipeng Li2, Jie Liu3 and Shuo Yang4

1,2
School of Astronautics, BEIHANG University, Beijing 100191, PR China
4,5
The First Military Representative Office of the Air Force Equipment Department in Luoyang,
Luoyang 471000, China
Email: liweipeng@buaa.edu.cn

Abstract. This paper presents the design, analysis, and testing of a piezoelectric XY micro-displacement
scanning stage (MDSS). The stage is composed of piezoelectric actuation mechanisms (PAMs),
compliant restraint mechanism, and moving frame. Due to the limited displacement of stack-type
piezoelectric actuator, diamond shaped amplification mechanism (DSAM) is applied in PAM to increase
displacement. Since the coupling problem in two-dimensional motion, elliptical compliant restraint
mechanism (ECRM) is applied to constrain in-plane parasitic rotation and coupling error between the
two motion axes of moving frame. Finite element models of DSAM, ECRM, and XY MDSS are
established and structural analysis is carried out. Analysis results show that: 1) the displacement
amplification ratio of DSAM is 2.08; 2) compared with the stage without ECRM, the in-plane parasitic
rotation and the coupling error between the two motion axes of moving frame are decreased about
96.1%, 61.5%; 3) the first resonant frequency of XY MDSS is 586.90Hz. Moreover, a prototype of XY
MDSS is manufactured, a testing system is established, and a preliminary test is carried out. Testing
results show that the displacements of piezoelectric actuators are 23.17μm, 18.82μm. It follows that the
displacements after magnification by DSAM are 48.19μm, 39.15μm.

131
 Comparative study of dampers on a G+26 storey building subjected to
lateral loading

Ritik Saxena1, Divyansh Tewari2, Akshit Gupta3 and Dr M Abdul Akbar4

1,2,3,4
Department of Civil Engineering, Dr. B.R. Ambedkar National Institute of Technology,
Jalandhar, Punjab, India
Email: ritiks.ce.20@nitj.ac.in

Abstract. Due to increase in urbanization, popularity of high-rise buildings has increased which are
vulnerable to the effect of wind and seismic loads. In the design of these structures, dampers are proven
to be effective in resisting the effect of lateral loads. In this paper, a realistic G+26 story RCC building
is modelled and analysed. Structure under observation is unsymmetrical which induces torsional
moments, in order to avoid that shear walls are added along with dampers. The structural response of
the building is compared using pall friction damper (PFD), lead rubber bearing (LRB) base isolators,
and fluid viscous dampers (FVD) as a viable energy dissipating system. PFD and FVD are provided on
the corners of the structure and LRB is provided at the base. The overall performance of the
aforementioned structure is simulated by performing response spectrum analysis in the different seismic
zone, using ETABS. Further stability of the structure is studied for Kobe and El Centro earthquakes by
performing time history analysis. Base Shear calculated by the analytical formula is 2512.7 kN which
is in acceptance with the simulated model i.e. 2538.84 kN. It is observed that design parameters of FVD
and PFD varies with ground motion frequency and variation of inter storey drift is least for LRB. In
addition, the structural response of the PFD for the Kobe earthquake is lower than that of the others in
terms of displacement and stiffness.

132
A Study on Vibration Characteristics of Cantilever Conical Shell Made
of FG Sandwich Material with Porosity and Thermal Effect

Apurba Das1, Subhendu Pal2, Korak Sarkar3, and Amit Karmakar4

1,3
Aerospace Engineering & Applied Mechanics Department, Indian Institute of Engineering Science
and Technology, Shibpur, Howrah-711103, India
2,4
Department of Mechanical Engineering, Jadavpur University, Kolkata-700032, India
Email: apurba.besu@gmail.com

Abstract. Free vibration behavior of a cantilever conical shell made of functionally graded sandwich is
studied using finite element method. The effect of porosity due to manufacturing defects and the effect
of operating temperature are analyzed. The finite element formulation consists of an eight-noded
isoparametric shell element with five degrees of freedom at each node. Lagrange’s equation is employed
to derive the governing equation for free vibration analysis at moderate rotational speeds where Coriolis
effect is not considered. Mesh convergence study and validation of the present solutions are performed
to confirm the accuracy. Isotropic metallic core and two FGM face-sheet (top and bottom) of sandwich
conical shells are considered. Two type’s porosity function namely even and uneven configurations are
considered to model the void/defects in the FGM configuration. The material properties of FGM are
varied with a simple power-law distribution of the volume fractions of their constituents through FGM
face sheet thickness. First four natural frequencies are determined and Campbell diagrams are plotted
for resonance study. Influences of operating temperature and porosities on the free vibration behavior
are evaluated. Parametric studies in terms of twist angle, thickness ratio of core to face-sheets, rotational
speed on the natural frequency are evaluated and analyzed.

133
 Numerical study of a square plan shape building with corner
modification

Geetam Saha1, Dibya Jyoti Basu2, Aritro Roy Mitra3 and Dipesh Majumdar4
1,2,3,4
Department of Construction Engineering, Jadavpur University, Faculty of Engineering
&Technology, Jadavpur University, Kolkata, West Bengal, India, 700032),
Email: dipeshce@jadavpuruniversity.in

Abstract. Generally, aerodynamic boundary conditions are overlooked for the design of the external
shape and orientations of buildings. These designs are normally made in accordance with architectural
and functional requirements. Under such circumstances, the structures are more susceptible to wind-
structure interaction induced loads. The present study focuses on investigating the wind pressure
developed on different faces of a square plan shape tall building. Developments in hardware, software
technology along with reliable turbulence models had made the use of CFD possible for prediction of
wind effects in the atmospheric boundary layer. A numerical study was performed to evaluate the
performance of a square plan building with corner modifications. The study was performed using
commercial code CFX with k-ε turbulence model. The faces of modified square plan model
demonstrated different pressure distribution as compared to the typical square plan shape model with
major differences observed in case of side faces. A square plans shape building was also investigated
for compassion of results and validation of the CFD package with IS 875:2015 (Part III). For better
understanding of different phenomenon occurring around the building, the flow pattern around the
model was also studied in detail.

134
 Induction Heating of Thermoplastic using Fe3O4

Inseok Baek1 and Seoksoon Lee2

1,2
School of Mechanical and Aerospace Engineering, Gyeongsang National University, 501 Jinju-
daeroJinju Gyeongnam 660-701, Republic of Korea
Email: leess@gnu.ac.kr

Abstract. Thermosetting composites are commonly used, but these composites are increasingly being
replaced by thermoplastic counterparts because thermoplastics offer an equivalent performance and can
be recycled via heating. Induction welding is a fast, clean, non-contact process that uses a metal-mesh
susceptor to facilitate localized controlled heating, but the metal mesh presents various problems. In this
study, the induction heating behavior of a 450-μm-thick thin-film susceptor, fabricated by mixing
magnetite (Fe3O4) nanoparticles (NPs) and polyamide 6/CF (30%) thermoplastic resin, was examined
with respect to the weight ratio of Fe3O4 (50, 67, 75, and 80 wt%). The high induction heating behavior
of the 75-wt% Fe3O4 susceptor was selected for additional heat-treatment experiments carried out at
3.4 kW at a frequency of 100 kHz. The resulting welded joints had lap shear strength values of 44, 30,
and 36 MPa under tensile test loads of 1.1, 0.75, and 850 kN, respectively. Scanning electron microscopy
images confirmed a uniform weld quality. Thus, the proposed manufacturing method involving the
incorporation of Fe3O4 NPs into thermoplastic resin should help expand the application range of
thermoplastic composites

135
 Experimental Verification of Stiffness behavior of Multilayer Metal
bellows

Istiyak Khan1, Nilesh Gohel2, Samiran Sengupta3 and Sujay Bhattacharya4

1,2,3
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai
4
Reactor Projects Group, Bhabha Atomic Research Centre, Mumbai
Email: ikhan@barc.gov.in

Abstract. Metal bellows are used in wide spread industrial applications. One of the application of
multilayer bellows is in design of pneumatic loading system wherein the imposed load is governed by
bellows internal pressure and its stiffness. Multilayer bellows have important characteristics of large
pressure retaining capability and less stiffness compared to single layer of equivalent thickness. For
designing the precision loading system, it becomes necessary to know accurate stiffness of bellows.
Design standard like EJMA does not consider the interlayer behavior including friction between the
layers. Therefore, need arises to determine the stiffness using detailed numerical simulations as well as
experimental verifications. The aim of the present work focuses on estimation of stiffness of small
diameter the multilayer (3 layers/ plies) metal bellows at different temperature using numerical
simulations and theoretical calculations. Experimental verification was carried out to predict the
deviations from estimated results. Consequently, the sensitivity analysis considering the effect of
friction between the different layers of bellows was performed to understand the stiffness behavior.

136
 New Response Branch for Undamped 2-DOF VIV of a Diamond
Oscillator

Kumar Sourav1, and Deepak Kuma2

1
Department of Aerospace Engineering, IIT Madras, Chennai – 600036, India
2
School of Mechanical Engineering, Dr. Vishwanath Karad MIT World Peace University, Pune –
411038, India
Email: ksourav678@gmail.com

Abstract. Undamped simultaneous in-line and transverse oscillations of a rigid diamond cylinder is
investigated numerically at a Reynolds number of 100. A stabilized space-time finite-element method
has been used to discretize the governing incompressible fluid flow equations in two dimensions. The
non-dimensional displacement and oscillation frequency of the diamond oscillator is compared with the
corresponding response and frequency data of the same oscillator executing undamped transverse-only
vibrations. From the frequency and response plots, it is established that the response curve of the present
study consists of the following response branches: first and second desynchronization regimes (DS I &
DS II), initial branch (IB) and lower branch (LB). A novel and previously unreported response branch,
ELB connecting LB and DS II branches has been obtained for a vibrating diamond cylinder. The
identification of the response branches are done on the basis of the slope change in the variation of
oscillation frequency with reduced speed.

137
 Drop Test of an Aircraft Landing Gear Equipped with MR Damper

Banghyun Jo1, Jaihyuk Hwang2, and Daesung Jang3

1,2,3
Department of Aerospace of Mechanical Engineering, Korea Aerospace University
Email: jhhwang@kau.ac.kr

Abstract. The commercial landing gear equips an oleo-pneumatic passive damper which has a
limitation to achieve optimal landing performance in specific landing cases. A landing gear system
equipped with a magnetorheological(MR) damper receives attention to replace that passive damper.
This paper adopts the simulation of a single landing gear equipped with an MR damper. A drop test
experiment of a scale prototype of the landing gear equipped with an MR damper is set up to verify the
simulation results. The main result shows that there is a small gap between simulation results and
experimental data.

138
 Dynamic response control of adjacent structures connected by viscous
damper using inerter-based isolation systems

Sudip Chowdhury
PhD research scholar, Civil Engineering Department, IIT Delhi, India,
E-mail: iamsudpchowdhury@gmail.com

Abstract. In the present study, the seismic performance of two adjacent SDOF systems connected by
viscous dampers has enhanced by inerter-based isolation systems. Two hybrid passive control schemes
have proposed and analytical solutions have derived to evaluate the seismic responses of both adjacent
structures under harmonic ground motion. The responses of uncontrolled adjacent structures have
compared with responses of the controlled structures. It is observed that the responses of the controlled
adjacent structures are significantly less than the responses of the uncontrolled structures. It has also
observed that the vibration reduction capacity of hybrid passive control two is 52.24% superior to the
hybrid passive control one.

139
 Capture Region of Realistic True Proportional Navigation Based on
Closed-form Solutions

Xiangxiang Li1, Wanchun Chen2, Zhongyuan Chen3 and Yizhong Fang4

1,2,3
National Key Laboratory of Science and Technology on Test physics & Numerical Mathematics,
China Academy of Launch Vehicle Technology, Beijing 100076, China
4
School of Astronautics, BEIHANG University, Beijing 100191, PR China
Email: Zhongyuan_buaa@163.com

Abstract. In this paper, a new method to obtain the exact closed-form solutions of realistic true
proportional navigation (RTPN) is proposed without any linearization of equations of motion. During
the relevant derivation of closed-form solutions, state equations of missile-target system and the
hyperbolic property of relative velocity are employed. A geometric scheme of high efficiency to
determine the orientation of missile velocity is suggested. Based on the closed-form-solution, some
relevant important characteristics, such as the commanded acceleration and time-to-go, are also
discussed.

140
 Experimental Investigation of Flow characteristics for Natural
Circulation Valve

Nikhil Pandey1, Samiran Sengupta2, Vijay K. Veluri3, Manoj Tilara4

and Sujay Bhattacharya5
1
Research Reactor Maintenance Division, Bhabha Atomic Research Centre, Mumbai, India, Homi
Bhabha National Institute, Mumbai, India
2,3
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai, India
4
Research Reactor Maintenance Division, Bhabha Atomic Research Centre, Mumbai, India
5
Reactor Projects Group, Bhabha Atomic Research Centre, Mumbai,India
Email: samiran1sengupta@gmail.com

Abstract. Experimental investigation was carried out to establish flow characteristics of a Natural
Circulation Valve for Pool type Research Reactor. Normally these valves are kept closed by the pump
pressure and are opened by the spring action when core cooling using natural circulation needs to be
established. When the valve needs to be closed by small pressure differential, the spring design is not
feasible. Hence a special type of Natural Circulation Valve is developed which actuates due to difference
between buoyancy force and self weight of NCV. The aim of the design of the NCV is that it can be
kept closed with very low system pressure and it will open once system pressure falls below this. The
flow characteristics for this valve have been established experimentally which have been reported in the
paper. Computational simulations have been done and compared with experimental results.

141
 Aerothermal Predictions of High-Pressure Turbine Flows Using RANS
Methods

Pranjal Anand1 and Rajesh Ranjan2

1
Department of Mechanical Engineering, BITS Pilani K K Birla Goa Campus, Goa, India
2
Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, Uttar Pradesh, India

Abstract. In this study, the flow around an uncooled high-pressure turbine guide vane cascade is
simulated using RANS methods. A well-experimented VKI cascade at Re(exit)= 10^6 and isentropic
Mach no. at exit = 0.84 is investigated using the SST k-ω, Realizable k-ε, Spalart- Allmaras and
Transitional SST models. The results show a good match for aerodynamic parameters against
experiments for classical turbulence models, however, predictions for heat transfer coefficients fail
miserably. Inclusion of transitional formulation in the SST model dramatically improves these
predictions. This is likely attributable to the largely laminar and transitional nature of flow which is not
predicted well by purely turbulent models.

142
 Numerical Study of the Effect of Shear Connectors in Insulated
Sandwich Panel Building System

Devjit Acharjee1, Dibya Jyoti Basu2 and Debasish Bandyopadhyay3

1,2,3
Department of Construction Engineering, Jadavpur University, Kolkata 700106, India
Email: devjitacharjee1996@gmail.com

Abstract. A low cost energy efficient earthquake resistant building system seems to be an alternative
solution for the much needed affordable housing in India. Insulating Building Panel is one of the
advanced building system consists of panel of expanded polystyrene (EPS) insulation confined with
galvanized welded steel reinforcement mesh and shear connector, which are subsequently applied with
pressurized concrete at site. A layer of mesh on either side of EPS welded together by shear connector
steel, penetrating through the polystyrene. However, the structural stability of these buildings greatly
depends on the performance of these shear connectors. The proposed paper studied the effect of the
spacing and different scenarios of shear connector failures in addition to the reduction of bond between
concrete and polystyrene core. Parametric study on the thickness of the wall panel, reinforcement
spacing, and grade of steel is also attempted. The effect of through-thickness shear behavior is also
studied. Various static as well as dynamic responses are compared. It is observed that the structural
stability of these composite sandwich panel depends on the spacing, diameter and adequacies of the
shear connectors. It may be concluded that these insulated precast building panel structural system has
a great potential for practical implementation and it is able to achieve the goal of efficient affordable
housing.

143
 Near - Wake Flow Structures of a Rectangular Wing at the Onset of
Stall

Aritras Roy1 and Rinku Mukherjee2

1,2
Department of Applied Mechanics, IIT Madras, Chennai -600036, India

Abstract. Flow field surveys f the near-wake behind a rectangular wing, Aspect Ratio,6.4, NACA4415
as section have been carried out around stall. The velocity fields are measured using single component
Laser Doppler Velocimetry at different span-wise and chord-wise locations. The detailed results include
mean, and root mean square velocity components with fluctuations, wake half-width variations, and
detailed higher moment turbulent statistics. The profile drag coefficient is calculated from the
distribution of stream-wise velocity profiles, and an attempt is made to compare with the total drag
values measured from the force balance data with the addition of induced drag computed from a
numerical method.

144
Effects of Column Orientation on Building Structure- Verified Through
Pushover Analysis

Suchintya Halder1 and Abhishek Hazra2

1,2
Civil Engineering Department, Narula Institute of Technology, 81 Nilgunj Road, Agarpara, Kolkata
-700109, India
Email: abhishek.hazra@nit.ac.in

Abstract. Recognizing the capability of destruction for the last few decades many research works have
been directed towards the safety of the RCC structure through the development of earthquake-resistant
structures. From the past research and different codal provisions available worldwide it can be found
out that moment-resisting capability greatly affects the overall seismic stability of the structures. In this
regard, it can be observed that the column orientation is one of the prominent factors of seismic stability.
Generally, the distribution of column orientation has been done according to the span lengths and
aesthetic values of the structures. In this backdrop, the present study aims to provide an overview of the
effect of column orientations for asymmetric structures.

145
 An Improved Unsteady CFD analysis of combined pitching and
plunging airfoil using Open Foam

P Srinivasa Murthy
Scientist ‘F (Retd.), Aeronautical Development Establishment, Bengaluru-560075
Email: dr_ps_murthy@yahoo.co.in

Abstract. There is a need to improve the propulsive efficiency of flapping airfoil by combining pitching
and plunging kinematics. Unsteady Aerodynamics study of combined pitching and plunging airfoil at
various Strouhal numbers and at low Reynolds Numbers of the order of Insect/Birds flight is of
importance to design and fly Micro Aerial Vehicle to meet the requirement of Para-military forces,
Border Security forces and other homeland service forces. A new methodology including customized
solver has been developed for the analysis of combined pitching and plunging airfoil based on CFD tool
'OpenFoam'. Since experimental data available for NACA 0012 Airfoil in combined pitching and
plunging motion, conditions relevant to the experiment are chosen for the analysis. As Strouhal number
increases there is an increase in mean thrust coefficient as well as mean propulsive efficiency. Similar
trends are observed from experiment. However, OpenFoam agreement with experiment is reasonably
good at all Strouhal numbers. Combined pitching and plunging motion produces higher propulsive
efficiency when compared to pure plunging motion

146
 Study of Stability Parameters for Multi-Rotor Aircraft using CFD
Analysis and Validation with Theoretical Calculations

Manoj S Naik1, Sumedha Y D2, Anish G P Nand3, Yeshas M N Bharadwaj4

and Promio Charles F5
1,2,3,4,5
Dept of Aerospace Engineering, R V College of Engineering, Bengaluru, India

Abstract. The quick development of Unmanned Aerial Vehicles has led to development in different
designs of the UAV to counter the challenges faced by conventional aircraft and helicopters. One such
solution is using tilting multi-rotor aircraft, the rotors offer thrust for VTOL, and the fixed wings
provides lifting force due to the motion of the complete aircraft. Since the rotors can be configured to
be more efficient for propulsion (e.g., with variation of root-tip twist), it avoids a helicopter's issues of
retreating blade stall. The tilt-rotor can also improve the cruising speeds and take-off weights as
compared to helicopters. With a population of 4.2 billion, Asia Pacific is the largest market in the world
by people and will soon have a clear future growth in some of its economies like India, Vietnam, etc. It
is on track to become the most important economic region in the world. The biggest problem in this part
of the world is infrastructure and the social capital is relatively low, in other words, there is a shortage
of runways and thus poor connectivity. The tilt-rotor aircraft market is therefore very large in this region
as these do not require a fully-fledged runway that is difficult to operate in mountainous regions and
also because of low cost. This demands a high-fidelity model with accurate knowledge about the
stability parameters for the different modes of flight. In this project, a study on the stability is done using
Computational Fluid Dynamics analysis for the full aircraft model. The stability parameters evaluated
are in the Longitudinal, Lateral and Directional planes for different conditions of angles and centre of
gravity positions. This requires a Preliminary aerodynamic study on the full aircraft model to understand
the lift and drag characteristics of the aircraft design. A MATLAB code is developed using the
theoretical equations for aerodynamic and stability analysis. The values obtained from this code is
considered to be the theoretical base values. The values from CFD and from MATLAB are compared
to obtain a validation study. This study gives us an understanding about the variation of stability
parameters according to the changing conditions, and will be useful for determining the placement of
rotors and other parts in the fuselage. These comparisons are also helpful in determining the efficiency
of the aircraft design and the flight dynamics model to obtain few significant conclusions, that are
beneficial for the future design of the tilt rotor vehicle.

147
 An Improved Homotopy Perturbation Method to Study Damped
Oscillators

C F Sagar Zephania1 and Tapas Sil2

1,2
Department of Physics, Indian Institute of Information Technology, Design and Manufacturing
Kancheepuram, Chennai-600127, Tamil Nadu, India
Email:phy18d002@iiitdm.ac.in
Abstract. This article introduces a new approach for finding out the approximate analytical solutions
for damped oscillators. In this approach (LHTT) the two-timing method (TT) is coupled with the
improved homotopy perturbation method (LH) [1]. Results obtained from LHTT for the van der Pol’s
oscillator are compared with the numerical solutions (RK4). Variation of displacement with time and
the limit cycle computed by LHTT mimics those from the RK4 method.

148
 Satellite topology and continuous size optimization based on Two-level
multi-point approximation method

Shuanjun Liu1, Hai Huang2, Shenyan Chen3 and Jiayi Fu4

1,2,3,4
School of Astronautics, Beihang University, Beijing, China
Email: liushj@buaa.edu.cn

Abstract. In view of the in-plane stiffening characteristics of the initial structure layout of a box-plate
satellite, optimal design of a certain satellite structure is carried out under several working conditions
based on the Two-level multi-point approximation method. Firstly, the finite element model of a satellite
structure and the mathematical model of the optimization problem are established. Secondly, the two-
order sequence problem is established by using the multi-point approximation method. The approximate
problem is solved by the genetic algorithm and the dual method to approach the original problem.
Finally, the method is used to carry out the integrated optimization design from the topological
configuration/layout of the satellite to the detailed size of the section, in which the in-plane reinforced
beam is the topological variable, and the section size of the beam and the thickness of the plate are the
continuous variables. The results show that the satellite weight can be reduced effectively under the
requirements of frequency and static force, and the optimization results can provide reference for the
design of other satellite structures.

149
 CFD Investigation of Geometrical Truncation effect of Typical Winged
Re-entry Vehicle on Pressure Coefficient at FADS ports

Kunal Garg1, Jathaveda M2, G Vidya3, Babu C4, Dr Patil M M5, and Dr Ashok V6
1,3
ACMD/ADSG/AERO, VSSC, ISRO, Thiruvananthapuram, Kerala, India
2
HSFC, ISRO, Thiruvananthapuram, Kerala, India
4
HSFC, ISRO, Thiruvananthapuram, Kerala, India
5
ADSG/AERO, VSSC, ISRO, Thiruvananthapuram, Kerala, India
6
AERO, VSSC, ISRO, Thiruvananthapuram, Kerala, India
Email: g_vidya@vssc.gov.in

Abstract. FADS system allows for determination of Air-data state using non-intrusive surface pressure
measurements. Current system employs nine port configuration all being placed on spherical nose cap
region. The algorithm determines the flight conditions based on the local surface pressure measurement.
The wind tunnel size and pressure probe spacing constraints in nose cap region restricts the scaling of
the model and subsequently requires model truncation for data generation for algorithm calibration.
CFD studies are carried out over full body and truncated body to bring the effect of truncation on flow
field near nose cap region and quantify the same. CFD Simulations are carried out at Mach 0.2 & 0.85,
α = 0ᵒ to 10ᵒ. The pressure coefficient at ports are compared. The cp distribution at nose cap region is
minimally effected by the geometrical truncation. Simulation at other Mach–α-β will be undertaken to
establish the same for full flight spectrum.

150
 Turbulence Model Selection for Low Reynolds Number flight

Somashekar V1, Chaitra Shashikant Paragi2, Varshitha N3, and Brinda N4

1,2,3,4
Department of Aeronautical Engineering, Acharya Institute of Technology, Bengaluru, Karnataka
- 560107, India

Abstract. While Reynolds number aerodynamics is important to natural and manufactured flyers, low
Reynolds number aerodynamics is critical for a variety of nature and man-made fly operations. For
years, people have wanted to know more about birds, bats, and insects, and recently, research in the
aerospace engineering community has become extremely active. Compatible turbulence model must be
chosen for the exact predictions of low Reynolds number aerodynamic characteristics. In this report,
numerical analyses of low Reynolds number flight 2D airfoil are done to compare the outputs of
different types of turbulence models for the prediction of aerodynamic characteristics for various flight
conditions i.e., 0° to 20° at chord based Reynolds number 2×〖10〗^5. The turbulence models tested
were: one equation Spalart Allmaras (S-A), two equation k-ε, two equation k-ω, three equation transition
k-kl-omega, four equation transition SST. However, the variation in flow physics differs between these
turbulence models. Procedure to establish the accuracy of the simulation, in accord with previous
experimental results, has been discussed in detail.

151
 First-ply failure load prediction of pre-twisted delaminated composite
conical shells

Suman Karmakar1, Tripuresh Deb Singha2, Tanmoy Bandyopadhyay3

and Amit Karmakar4
1
Mechanical Engineering Department, Dr. B. C Roy Engineering College, Durgapur-713206, India
2
Mechanical Engineering Department, Govt. College of Engineering and Textile
Technology,Serampore, Hooghly-712201, India
3,4
Mechanical Engineering Department, Jadavpur University, Kolkata-700032, India
Email: suman.karmakar@bcrec.ac.in

Abstract. In this research work, a finite element method based computational procedure is developed
to predict first-ply failure (FPF) load of thin pre-twisted delaminated composite conical shell subjected
to uniformly distributed load. An eight-node isoparametric shell element is chosen in the formulation
which considers the effect of transverse shear deformation based on Mindlin’s theory. The delamination
crack front is modeled employing multi-point constraint algorithm. Different failure criteria such as
maximum strain, maximum stress, Hoffman, Tsai-Hill, and Tsai-Wu are considered to estimate the FPF
loads. The accuracy of the present method is established by validating with the benchmark results
available in the published literature. The numerical results are obtained to analyze the influence of some
important parameters such as stacking sequence, pre-twist angle and delamination on the FPF loads are
analyzed.

152
 Design and Analysis of Active Phased Array Antenna for 80 kg-Class
Micro-Satellite SAR

Chan Mi Song1, Seung Joo Jo2, Chang Hyun Lee3, Myeong Jae Lee4, Seung Hun Lee5,
Sung Chan Song6 and Hyun-Ung Oh7
1,2,3,4,5,6
Satellite system 1 team, Aerospace R&D Center, Hanwha Systems, Inc., 491-23 Gyeonggi-
Do,South Korea
7
Space Technology Synthesis Laboratory, Department of Smart Vehicle System Engineering,Chosun
University, (Agency for Defense Development: Additional Post), 375 Seosuk-dong, Dong-gu,Gwangju
501-759, Korea
Email: cm.song@hanwha.com

Abstract. In this paper, an active phased array antenna with high gain characteristic for micro-satellite
SAR was designed and analysed. This active phased array antenna consists of array antenna with 1×16
sub-arrays and semiconductor transceiver modules, which are operating at X-band. The antenna element
based on radiating patch, spacers, slotted ground, and cavities. By applying a honeycomb-structured
spacer and a perforated PCB on the antenna elements, lightweight characteristic is achieved. Also, the
semiconductor transceiver module is designed to control the amplitude and phase of the each exited
signal on the radiating elements. Based on the designed this active phased array, beamforming
performance were confirmed (in case that beam steering angle is 10°). Also, the mechanical analysis
results show the compliance with the structural stiffness and thermal stability.

153
 Agile Turn Guidance Law based on Deep Reinforcement Learning

Xiaopeng Gong1, Yizhong Fang2, Wanchun Chen3 and Zhongyuan Chen4

1,3,4
School of Astronautics, BEIHANG University, Beijing 100191, PR China
2
National Key Laboratory of Science and Technology on Test physics & Numerical
Mathematics,vBeijing 100191, China
Email: Zhongyuan@buaa.ed.cn

Abstract. In this paper, a deep reinforcement learning (DRL) based agile turn guidance law for air-to-
air missiles is proposed. Facing the complex aerodynamic environment with large angle of attack, the
proposed data-driven guidance law can effectively address the problem of modeling difficulties caused
by inaccurate aerodynamic parameters. By utilizing the DRL-based guidance law, the missile can track
the maneuvering target during the turn phase, providing advantageous initial conditions for the terminal
guidance. Experimental results indicate that the DRL-based guidance law is suboptimal compared with
the optimal solution given by a direct method and robust to aerodynamic disturbances. Furthermore, the
executing time is short enough for online guidance effectively.

154
 Study of effect of rotational rate of a cylinder on the volume fraction of
vapor formed during nucleate boiling phenomenon of water

Manjunath S V1, Maharana Sarat Kumar2, Abdul Sharief3 and Venugopal M M4

1
Dept. of Aeronautical Engineering, Gopalan College of Engineering and Management, Bengaluru-
560048
2
Dept. of Aeronautical Engineering, Acharya Institute of Technology, Bengaluru-560107
3
Professor and Dean, Dept. of Mechanical Engineering, School of Engineering, Presidency
University, Bengaluru-560064
Email: msvmanju@gmail.com, skmaha123@gmail.com, abdulsharief2010@gmail.com

Abstract. The problems of fluid flow and heat transfer phenomena over an array of cylinders gives rise
to some of the important aspects in fluid dynamics theory such as fluid flow interaction, interferences
in flow, vortex dynamics and a variety of engineering applications such as compact heat exchangers,
cooling of electronic equipment, nuclear reactor fuel rods, hot-wire anemometry and flow control. These
structures are subjected to air or water flows and therefore, experience flow induced forces which can
lead to their failure over a long period of time. Basically, with respect to the free stream direction, the
configuration of two cylinders can be classified as tandem, side-by-side and staggered arrangements. In
the present study, two heated cylinders in tandem are immersed in water and are involved in the phase
change phenomenon due to nucleate boiling process. Different study situations have been created by
making both or one of the cylinders rotating or stationary and the volume fraction (VF) of vapor is noted
when the simulation of phase change is completed. The Eulerian multiphase mixture model has been
used along with the RANS (Reynolds-averaged Navier-Stokes) equations to simulate the two-phase
(water and vapor). At a specific location of one cylinder, the VF values over a time period are observed
and compared with that of the other cylinder. The rotational rate of the cylinder versus VF of vapor
produced during the nucleate boiling process has been reported. A significant rise (about 85%) of VF of
vapor around a rotating cylinder against the value obtained for a stationary cylinder confirms that there
is an impact of rotational rate on the production of water vapor. Fig.1 shows the contours of volume
fractions of water vapor when the saturation temperature water is 100 oC and the surface temperature is
120 oC. The maximum value of VF recorded is 0.99 (maximum achievable value is 1= volume fraction
of water + volume fraction of vapor). In the Fig.2 is shown the variation of VF of vapor with respect to
the rotational rates. It is noted that VF has accelerated from a value of 0.5 when the cylinder was at rest
to 0.90 when the rpm is 1000 and afterwards, for each 500 rpm increase in the rotational speed, the VF
has remained in a stable range from 0.93 to 0.98. The objective of this part of the study is achieved
because it is confirmed that there is a significant impact of rotation on the overall phase change
phenomenon and, in particular, on the volume fraction of vapor.

155
 Modelling method of 3-Dimensional woven composite considering
realistic features

Hiyeop Kim1, Pyunghwa Kim2, Yongun Jun3 and Jungsun Park4

1,2,3,4
Korea Aerospace University, Department of Aerospace and Mechanical Engineering, 10540
Goyang, South Korea
Email: hykim@kau.kr

Abstract. The yarns forming 3-Dimensional woven composites are bent and contracted in cross-
sections due to interference between them. Therefore, it is necessary to calculate the mechanical
properties of the composite in consideration of these geometric shapes to obtain a more accurate
prediction of results. In this article, cross-sections of the 3D woven composite are obtained using an
optical microscope to observe the bend and contracted shapes of yarns. The properties of the composite
are predicted using the modeled RUC and the weighted average model. The proposed method is
validated by comparing test and prediction results using the idealized model. We conclude that the
present method is useful for the design of structures to which the 3D woven composite is applied.

156
 Organic Dye based sensitized solar cells: A performance study

Ashish J. Chaudhari1, Ravirajan Mishra2, Yash Narkar3, Smith Tawar4, Archies Mhatre5
and Vinay D. Patel6
1,2,3,4,5,6
Department of Mechanical Engineering, Vidyavardhini’s College of Engg. And Tech., Vasai,
INDIA-401202
Email: ashish.chaudhari@vcet.edu.in

Abstract. Dye-sensitized solar cell (DSSC) which is a alternative to the conventional p-n junction
devices The key difference of the DSSC over traditional single junction solar cells is the use of a organic
dye, which enhance the absorption rate of the wide band gap semiconductor and thereby increase the
efficiency of the working electrode. The natural dyes as sensitizers are the emerging sources due to their
availability, low cost and environmentally safe. Moreover, absorption field of the dye and their
adherence to the surface of the nanostructured TiO2 are important parameters related to the efficiency
of the cell. To have uniformity of layers and precision, the cells are manufactured inhouse using fully
automatic special purpose machine. Ferreira et al, 2020 explains fresh daisy flowers namely Yellow
Daisy, Purple Daisy and Wine Daisy based organic dye were utilized attained efficiency of 0.88% .
Najm et al, 2019 were utilized pinang fruit crusts crushed in a grinder, 400 mL of ethanol based dssc
were tested and attained 0.118% efficiency. Chaudhari et al, 2020 manufactured the DSSC using
automated special purpose machine and evaluated performance of glass based synthetic dye solar cell.
This study examined the performance of DSSC by using organic dyes with organic and synthetic
electrolyte. For testing, natural dyes were extracted from dried black currant, java plum as both this fruit
contains large amount of Anthocyanin which is responsible for absorption of light. Parsley extract was
also added to both the fruits as it has excellent amount of Chlorophyll which helps in absorption of
sunlight as in natural photosynthesis. The concentration level of black java, Black currant and parsley
were added in the ratio of 2:2:1. The counter electrode used was graphite and the electrolytes used were
concentrated Vinegar as organic electrolyte and ethylene glycol-potassium iodide as synthetic
electrolyte. The performance characteristic of both DSSCs being observed throughout the day of the
cell. The performance parameters such as power output and maximum efficiency and corresponding fill
factor are plotted and analysed.

157
 APSCO SSS-1 Communication System Design and Implementation

Hao Tian1, Jikai Wang2 and Hai Huang3

1,2,3
School of Astronautics, Beihang University, No.9, Nansan Street, Shahe Town, Changping District,
Beijing, China
Email: hhuang@buaa.edu.cn

Abstract. Students Small Satellites (SSS) project was initiated by Asia-Pacific Space Cooperation
Organization (APSCO). This project is aimed to train students from member states to study space
technology and satellite engineering through practical design of satellites. SSS-1 microsatellite is the
principal satellite in the SSS constellation with other two nanosatellites. SSS-1 communication system
needs to transmit payload data and serve as an international space education platform. In this paper, it
presents the design of this system including the onboard part and the ground station. The onboard part
includes a UV transceiver and an S-band transceiver. Low-speed and high-speed transmission
complement. For data receiving, analysis and sharing, Beihang ground station has been built with a 3.3m
parabolic antenna and a UHF/VHF Yagi antenna. Cost-effective SDR solution is used for signal
demodulation and decoding. Ground station network scheme will be adopted for APSCO member states
to sharing telemetry data and control satellite’s payload with a tracking and control center built in
Beihang. At present, SSS-1 satellite’s communication system has passed the test and the satellite will
be launched in October 2021.

158
 Numerical Investigation for Selection of Airfoil with Regard to Flying
Wing Applications

Sandhya Rani S1, Sachin Raj R2, G R Rakshith3, Yeturi Sreenu4 and V Somashekar5
1,2,3,4,5
Department of Aeronautical Engineering, Acharya Institute of Technology, Bengaluru,
Karnataka -560107, India
E-mail ID: somashekar.v@acharya.ac.in

Abstract. Future airfields will become increasingly intrigued with UAVs due to their versatility. These
robots can conduct a multitude of tasks, including carrying out strategic reconnaissance, offering
telecommunications links, and aiding in metrological research, as well as finding and mapping
resources, detecting forest fires, monitoring natural disasters, and defending borders, to name a few.
When UAVs fly at low altitudes, they usually have multiple abilities, such as on-site information
gathering, target classification, photogrammetric survey, or audio broadcasting. They may be better
equipped to help with emergency management or disaster relief. In the case of low Reynolds number
flights, the airfoil plays a crucial role in generating lift. This paper presents an approach using open
source/free software and commercial software ANSYS to evaluate and choose the airfoil for low
Reynolds number flight designs and suggests a set of criteria used to evaluate the airfoils. The numerical
simulations of the flow around obtained/selected (Eppler-326, Eppler333, and Marske7) 2D airfoil were
carried out by using the computational fluid dynamics (CFD) software, Analysis system (ANSYS) at
Reynolds number 2×〖10〗^5. From the results, the recorded maximum coefficient of lift for Eppler-
326, Eppler333, and Marske7 airfoils are 1.1584, 1.3468, and 1.0391 at stall angle of attack (12°).
Applications of this philosophy were demonstrated through the successful selection of a suitable airfoil
(Eppler-333) for the design and development of a flying wing that achieved a maximum coefficient of
lift of 1.34. The Eppler-333 airfoil is strongly recommended for the design and development of flying
wings applications.

159
 Evolution of heat transfer at the stagnation point during the detached
bow shock establishment

Qiu Wang1, Jinping Li2 and Wei Zhao3

Abstract. The diffraction of a shock wave by a stationary body is a problem of interest associated with
the starting of shock tubes and expansion tubes which are well suited to the study of hypersonic flows.
However, these facilities come at the expense of test time. The transient parameters during the
establishment of the detached bow shock in such short impulsive facilities are important for both data
processing and experimental design. In the present study, numerical simulations are conducted to
investigate the diffraction of a normal shock wave by a sphere and the subsequent transient phenomena
in a viscid, perfect-gas flow field. The incident shock Mach number ranges from 3 to 5 with a specific
heat ratio of 1.4. Based on the theoretical description of the reflected shock position during bow shock
formation, approximate solutions for the time histories of the stagnation point heat flux are also derived.
Analytical and numerical results match well. The results also show that the stagnation point pressure
and heat flux approach the steady value much more rapidly than the shock detachment distance.

160
 Design and fabrication of biocompatible quadcopter board

Vignesh Kumar R1, Pravalika R2, Shrinidhi H M3 and Varshini D E4

1,2,3,4
Department of Mechanical Engineering, Vidyavardhaka College of Engineering, Mysuru, India

Abstract. The role of hybrid composites in aerospace structures has widely increased due to enhanced
mechanical properties, low cost of production and ease of manufacturing. The fibers used being raw
untreated silk and jute, both biodegradable and natural fibers. Manufacturing of composite in
combination of these two fibers prove to have superior mechanical properties. The manufacture of
hybrid composite has been carried out and the obtained laminate is used as a quadcopter board, capable
of carrying payload of 1-1.5 kilogram and natural fibers used being 100% biodegradable.

161
 Numerical Study of Multiple-Impingement Jet Arrays on Iso-Thermal
Horizontal Flat Plate

Dr. Pol Reddy Kukutla1, Dr. Venkatesu Sadu2, Dr. Syamsundar C3

and G. Venkata Sbbaiah4
1
Dept. of Mechanical Engineering, Narasimha Reddy Engineering College (Autonomous),
Maisammaguda, Medchal, Telangana, India,
2
Dept.of Mechanical Engineering Annamacharya Institute of Technology and sciences (Autonomous),
Rajampet, Andhra Pradesh, India
3
Dept.of Mechanical Engineering CMR Engineering College (Autonomous), Kompally, Medchal,
Telangana, India
4
Dept.of Mechanical Engineering MVSR Engineering College (Autonomous), Nadurgul, Telangana,
India
Email: polireddyk01@gmail.com

Abstract. The numerical investigations were performed with CFD commercial code of COMSOLE 5.2
In the present paper, both the modeling and computational analysis was carried by the COMSOLE. The
grid independence test was obtained with the fine and coarse meshes. The fine meshes exhibit higher
effectiveness and coolant distribution with reduced mesh size. The study was performed for coolant air
with constant Prandtl’s number and isothermal wall. The Reynolds number was c varied between 25
and 100 in laminar flow conditions.The obtained numerical results exhibit good agreement with
experimental data.

162
 Linearized control of an axisymmetric spinning top to a regular
precession trajectory

Anirudh Chandramouli1 and Abhijit Sarkar2

1,2
IIT Madras, Mechanical Engineering Department, 600036 Chennai, India
Email: a1nirudh@gmail.com

Abstract. In this work, we consider the problem of controlling a pivoted axisymmetric spinning top to
a steady precession trajectory with a constant nutation angle. In the 3-1-3 Euler angle convention, we
show that the linearization of the equations of motion about nutation-free trajectories leads to a time-
independent Jacobian matrix. A control system with two actuators, providing input to the base in two
globally fixed directions, is developed using eigenvalue placement techniques on the linear time-
invariant system and assuming full state feedback. A numerical example is presented to demonstrate the
effectiveness of the developed control system.

163
 Theoretical & experimental study on a miniature jet pump with low
area ratio

Vimal Kotak1, Samiran Sengupta2, Anil Pathrose3, Sugilal Gopalkrishnan4

and Sujay Bhattacharya5
1
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai, India,
2,3
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai, India
4
Homi Bhabha National Institute, Mumbai, India
5
Reactor Projects Group, Bhabha Atomic Research Centre, Mumbai, India
Email: kotakvk@barc.gov.in

Abstract. Jet pump is used for many conventional applications. For some special applications like in
experimental device in a nuclear reactor, miniature size jet pump with low area ratio is to be used for
achieving comparatively high flow amplification with lower primary flow rate. Since sufficient data are
unavailable in the open literature for miniature size jet pump with low area ratio, theoretical
investigation with complementary experimental study are carried out. Results obtained using an
axisymmetric CFD models are compared with those of the analytical model. Effect of flow ratio on
internal pressure & velocity profile is presented. The computed results are then compared with the
experimental results. It was observed that results obtained from the CFD model is in very good
agreement with the experimental results for flow ratios up to 2.

164
 Heat Treatment of AISI 1045 Specimens using High-Frequency and
Simulation

Jinkyu Choi1 and Seoksoon Lee2

1,2
Department of Mechanical Engineering Research Institute, Gyeongsang National University, 501,
Jinju-daero, Jinju-si, Gyeongsangnam-do 52828, Korea
Email: leess@gnu.ac.kr

Abstract. AISI 1045 specimen was compared through a high-frequency heat treatment simulation and
experiment considering metal phase transformation. Hardening zone predictions were confirmed
through cooling and metal phase transformation simulations after obtaining the results from
electromagnetic heat transfer simulations. The cooling process was modeled by applying the cooling
coefficient of the cooling water in the same way as the actual heat-treatment process. Experimental and
simulated results of the heating temperature and curing depth of an AISI 1045 specimen with a carbon
content of 0.45% were compared; the comparison indicated good agreement between the two. We
established a method for obtaining the high-frequency thermal treatment simulation method considering
metal phase transformation.

165
 Investigations in Flapping Wing Ornithopters Modelled as Nonlinear
Compliant Mechanisms

Nitin Mathew Daniel1, Richard Wilson2, Premchand V P3 and Vaisakh S Nair4

1,2,3,4
Department of Mechanical Engineering, Mar Baselios College of Engineering and Technology,
Thiruvananthapuram, Kerala

Abstract. Nature’s flapping wing systems are a precious source of inspiration for efficient propulsion
and lift generation devices used in micro air vehicles. The use of flapping wing devices is very attractive,
because they are able to operate in different regimes of motion, combine the function of control device,
stabilizer, and provide high maneuverability. The potential application of Flapping Wing MAVs mainly
focuses on sensing, information gathering, relevant for disaster monitoring and security surveillance,
which plays a major role in civil and military sectors. Deficiencies of conventional fixed-wing or rotary-
wing approaches in terms of aerodynamic performance and achieving the necessary specifications for
small-scale MAV designs have directed attention to the biologically inspired flapping-wing approach.
Stanley S. Baek et al[1] experimentally demonstrated that the average power and the peak torque can
be reduced by resonant excitation with a constant voltage for motor-driven oscillating systems.
Avadhanula et al[2] analysed the kinematics of the mechanism which converts piezoelectric actuation
into complex wing motion. A complete non-linear modelling of the system based on the Lagrangian
energy technique is also presented. Three piezoelectrically actuated flexure-based mechanisms are
described by A. Cox et al[3] that transforms the linear output of piezoelectric unimorph actuators into
single degree of freedom flapping motion. Fernando and Ronald [4] conducted experimental studies
using a simple biomimetic optical flow algorithm which extracted net motion direction by averaging the
flow field across the whole sensor, demonstrating the significance of pitch oscillations due to wing
flapping on the optical flow direction estimates. Bor-Jang Tsai and Yu-Chun Fu’s[5] analysed the
aerodynamic performance of a planar membrane wing as shape aerofoil for the micro aerial vehicle.
They employed the concept of four-bar linkage to design a flapping mechanism which simulates the
flapping motion of a bird. In this work a DC motor driven flapping robot modelled as a nonlinear motor
driven crank arm mechanism coupled to spring mass system (Compliant Mechanism) is considered. The
nonlinearities in the system includes nonlinearity in the damping, modelled by Coulomb friction model
and the cubic nonlinearity in the spring. Non dimensional analysis is carried out to demonstrate a relation
between the resonant frequency of the mechanism and the ideal motor input voltage to achieve
maximum input power reduction. The main focus of this study investigate the effect of nonlinearities
on the system performance by conducting a numerical study using MATLAB.

166
RANS modeling for short and long separation bubbles in flow past low-
pressure turbine cascades

Shruti Rajpara1 and Rajesh Ranjan2

1
Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Engineering
Science and Technology, Shibpur
2
Department of Aerospace Engineering and Applied Mechanics, Indian Institute of Technology,
Kanpur

Abstract. The flow within low-pressure turbines (LPTs) at high altitudes is essentially complex,
involving separation-induced transition, leading to the formation of a separation bubble. These bubbles
can be classified as short or long, based on their influence on aerodynamic parameters of interest. In this
work, we study the transitional flow in a high-lift LPT cascade T106C using low-cost turbulence and
transitional models. The study is performed for Reynolds numbers (Re): 80,000, 120,000, and 160,000,
each of which exhibits a different kind of separation bubble. None of the classical turbulence models
show the ability to correctly predict the separation and hence transition. However, modern transitional
models, Transitional SST (TSST) and Laminar Kinetic Energy (LKE), show reasonable predictions of
separation regions. While the TSST model is superior in high Re flows, where closed separation bubbles
are found, the LKE model better predicts the long open bubble in the low Re case. Lastly, the effect of
variation of pitch-to-chord ratio is examined on the separation bubble as well as blade-load distribution.
This can serve as an initial step for potential blade shape optimization.

167
 Porous Scaffold by Additive Manufacturing for Bone Replacement in
Biomedical Application

Apurba Das1, Arghya Mondal2, Palash Mondal3, Masud Rana4 Amit Roy
Chowdhury5 and Amit Karmakar6
1,4,5
Aerospace Engineering & Applied Mechanics Department, Indian Institute of Engineering Science
and Technology, Shibpur, Howrah-711103, India,
2
School of Laser Science and Engineering, Jadavpur University, Kolkata-700032, India
3,6
Department of Mechanical Engineering, Jadavpur University, Kolkata-700032, India
Email: apurba.besu@gmail.com

Abstract. Porous Scaffold structures are widely used in biomedical application for bone replacement.
In the present study, porous Ti–6-Al-4V alloy scaffolds with different structures are successfully
fabricated by a selective laser melting (SLM) method. The fabrication of porous scaffold by
conventional techniques mostly offer control in varying composition and hardly offer control in varying
structural design. The flexibility of structural design provided by additive manufacturing such as
selective laser melting (SLM) makes it an outstanding technique to fabricate scaffold. In this work, an
overview of porous scaffold fabrication techniques is presented using additive manufacturing
techniques. On the other hand, fabrication of a porous scaffold with varying structural design is
demonstrated using SLM technique and titanium alloy as material. The structural design fabricated by
SLM was periodic cellular structures with 15 mm cubic unit. To obtain porous scaffold, the structure
was varied by change in strut thickness continuously and linearly in single direction. Results showed
that the complex design is successfully fabricated by SLM and achieved nearly bone properties of the
fabricated scaffold to use in bone replacement.

168
 Al/epoxy adhesion strength by a modified butt joint test configuration

Madhusudhanan U1 and Rajesh Kitey2

1,2
Department of Aerospace Engineering, Indian Institute of Technology, Kanpur 208016, India
Email: madhusud@iitk.ac.in

Abstract. Al/epoxy adhesively bonded joints are quite common in aerospace applications. The
reliability of such joints highly depends upon their interfacial properties. Often pull tests are conducted
to evaluate the interface strength of bonded joints. Unless the effect of stress concentration is taken into
account, a reliable interface strength data cannot be obtained from the experiments. In this investigation,
the interface strength between Al 6063-T6 alloy and epoxy is evaluated under quasi-static loading
conditions. Test specimen is designed by performing a systematic computational analysis. The effect of
stress concentration on the interface stress is subdued by opting for an Al/epoxy/Al configuration with
300 tapered aluminum cylinders. The modified axisymmetric butt joint specimen is prepared by
naturally bonding the epoxy layer with the aluminum. Pull tests conducted on the specimens with
tapered and untapered edged specimens showed that the interface strength is enhanced by nearly 2.3
times in the absence of stress concentration.

169
 Numerical Study on Transient Transverse Jet Effect of the Two-
Dimensional Slot Under Supersonic Conditions

Song Xue1, Tianyixing Han2 and Chongwen Jiang3

1,2,3
National Laboratory for Computational Fluid Dynamics, School of Aeronautic Science and
Engineering, Beihang University,100191 Beijing, China
Email: qieerbushexs@163.com, cwjiang@buaa.edu.cn

Abstract. Reaction control system (RCS) has the advantages of high response speed, wide adaptability
and small shape interference. In practical engineering applications, in order to achieve high-precision
control under high-speed conditions, the jet usually runs only a few milliseconds. During this time, the
complex wave system and vortex structure in the jet flow field have not been fully established.
Therefore, it is especially significant to study the transient process of lateral jet flow under supersonic
conditions for the realization of RCS. However, there is a lack of research on the transient process of
transverse jet. In this paper, the transient developing and fading process of the jet through the two-
dimensional slot is studied. Based on this, more researches are carried out, including the effects of jet
pressure ratio and freestream Mach number on the transient process of two-dimensional slot jet.

170
 Mode Transition in Strut Based Parallel Fuel Injection in Scramjet
Engine

Rajesh Kumar1, Prudhvi Narne2 and Amardip Ghosh3

1,2,3
Department of Aerospace Engineering, IIT-Kharagpur, India.

Abstract. This study focuses on numerical investigation of strut-based parallel fuel injection in
supersonic reacting flows. A Two dimensional, density-based solver has been used with the k-ɛ
turbulence model. Reacting flow has been simulated using the Species transport model to better estimate
the species concentration and reaction rates. Short residence time in conjunction with compressibility
effects in supersonic reacting flow regimes leads to problems like inadequate mixing, flame blowout,
and incomplete combustion. High-speed propulsive systems exploit the presence of shock to increase
the efficiency of combustion as well as mixing. This study focuses on the dynamic switching between
ram and scram mode of operation for a dual-mode scramjet engine and quantifies the effect of fuel
injection to air pressure ratio on combustion, shock cell pattern, thermal chocking, and ram-scram
transition. Observations were made regarding changes in the flow field and combustions zones during
the mode transition.

171
 Simulating the impact of ground vortex ingestion on inlet performance

Dr. Rajesh Kumar1 and Pramodkumar Vanam2

1,2
Siemens Industry Software (India) Pvt Ltd, Unit 4, 7th Floor, Navigator Building ITPL, Bangalore,
Email: rajesh.kumar1@siemens.com

Abstract. Abstract. Simulating the aerodynamic impact of ground vortex ingestion on aero-engine inlet
performance, close to the ground under crosswind conditions. There can be notable interaction between
the intake aerodynamic and the surface. This interaction results in a concentrated vortex originating at
the ground plan and terminating inside the engine. The rotational flow field induced by the ground
vortex is the cause for ingestion. This is the major source of engine performance deterioration and
reduced service life. This interaction is primarily dependent on the intake ground clearance and the
stream tube contraction ratio of the intake. Computational fluid dynamics (CFD) analysis have been
performed to predict the ground vortex, its strength and characteristics of the flow-field. Simulation
using Simcenter STAR-CCM+ have been executed to provide insight into this important phenomenon.
The characteristics of the ingestion location have been studied for range of crosswind conditions and
simulation results have been compared with experimental data to assess the numerical prediction
capability.

172
 Modeling damage evolution of laminated composites under high strain
rate loading

Bipin Kumar Chaurasia1 and Deepak Kumar2

1,2
Department of Mechanical Engineering, National institute of technology, Jamshedpur, 831014,
India
Email: deepak.me@nitjsr.ac.in

Abstract. Carbon fiber laminates are widely used in defense and aerospace applications. These types of
components are subjected to dynamic loads, such as ballistic impacts and high velocity impacts, which
cause high strain rate deformation. The high strain rate deformation results in localized damage and the
impact energy is dissipated near the contact area. In this paper, using the modified Matzenmiller-
Lubliner-Taylor (MLT) method, the behavior of a nonlinear rate-dependent constitutive composite
model is investigated. The composite model consists of carbon fibers with balanced stacking sequences
[0/45/90/-45]3s. In the model, the modified method considers six types of damage, axial (d11), normal
(d22,d33) and shear (d12,d23,and d31) on seven damage envelopment criteria of material criteria. The
method introduces three levels of shear damage that provide fiber and matrix shear and improves
damage prediction. These damage equations are based on the micromechanical strain energy method to
predict the nonlinear deformation of the composite as a function of strain rate. The failure criteria of the
composite model depend on the stiffness, strain rate as well as the progression of damage. Thus, the
model based on the modified method predicts the strength and damage behavior of the carbon fiber
composite more accurately than the MLT method.

173
Wall effect on the Drucker Prager model parameters for pebble beds in
nuclear fusion reactor

Deepak K Pawar1, Maulik Panchal2, Paritosh Chaudhuri3, Ratna Kumar Annabattula4

and Narasimhan Swaminathan5
1,4,5
Department of Mechanical Engineering, Indian Institute of Technology Madras, Chennai 600036,
India
2,3
Institute of Plasma Research, Bhat, Gandhinagar 382428, India

Abstract. Lithium ceramics in the form of pebble beds are used as tritium breeder materials for future
fusion reactors. Drucker Prager (DP) model has been found to be an appropriate model for predicting
the macroscopic thermomechanical behaviour of these granular pebbles. Discrete element method can
be used to simulate triaxial compression tests to extract DP model parameters which can then be used
to describe the constitutive relationship of a homogenized finite element model of a pebble bed. In the
present work, the effect of nearby wall on DP parameters is studied by considering the various bed
geometries.

174
 Stochastic finite element modelling of the graded cellular arches

Mohammad Amir1, Mohammad Talha2, Sang-Woo Kim3 and Changduk Kong4

1,3
Hankyong National University, Anseong, 17579, Republic of Korea
2
Indian Institute of Technology, Mandi, Himachal Pradesh, 157075, India
4
Chosun University, 309Pilmundaero, Dong-go, Gwangju,61452, Republic of Korea
Email: swkim@hknu.ac.kr

Abstract. In the present work, an efficient stochastic finite element model based on the three-nodded
element has been utilized for the stochastic vibration analysis of graded cellular arches. The present
formulation is based on the higher-order shear deformation theory and orthogonal curvilinear coordinate
axes. The internal pores in the graded cellular arches follow the two distinct types of distributions. The
material properties of the graded cellular arches vary in the thickness direction as a function in terms of
porosity coefficient and mass density. In the present study, a stochastic finite model in conjunction with
the first-order perturbation technique (FOPT) has been used to analyze these kinds of structures with
material stochasticity.

175
 Unsteady Aerodynamic Force Approximation for Flutter Prediction

Promio Charles F1, Pooja Bhat2, Sushma V3, Varalakshmi T S4 and Vedavathi G A5
1,2,3,4,5
Department of Aerospace Engineering, R V College of Engineering, Bangalore
Email: promiocharlesf@rvce.edu.in, vedayadav123456@gmail.com

Abstract. Abstract. The existing aerospace industries are mostly dependent on finite element-based
software, for extracting the air loads at the discrete frequency and velocity conditions. Further, the
unsteady air loads can be used to predict flutter. In the present work, unsteady aerodynamic forces are
used to compute flutter in time domain, using Matric Polynomial Approach (MPA). The flutter analysis
input parameters, namely, frequency and mode shapes are obtained from normal mode analysis. Then
discrete unsteady aerodynamic forces are obtained from the frequency-based flutter analysis performed
in MSC PATRAN. Then Matrix Polynomial Approach is used to transform the three-dimensional
discrete aerodynamic parameters into continuous function, thus facilitating to build a Linear Time-
Invariant (LTI) state-space system. The state-space model built is a Multi Input Multi Output (MIMO)
system that can be easily solved as an Eigen value problem. From the characteristic (Eigen value) value
problem, the dynamic instability conditions are determined for predicting the onset of flutter in time
domain. This approach is bench marked by validating the flutter results obtained from the simulation
using CFD, in comparison with the NASTRAN flutter result. In the proposed work, it is directed to
validate the procedure by using a simple aluminum cantilever plate, and thereby studying the novelty in
dealing with the aeroelastic studies more efficiently and practically. Introduction The present aerospace
industries are very keen in identifying the problems associated with aeroelasticity, and it paves wide
opportunities for practicing researchers all around the globe. Among the different aeroelastic problems
identified, flutter appears to be more dangerous and may sometimes lead to catastrophic failure, if it is
not controlled. Hence, aeroelastic studies are very much essential in qualifying the aircraft to fly safely
at different flight conditions. Air load approximation techniques are the algorithms used for computing
unsteady aerodynamic forces that are required to transform the discrete values to a continuous function.
The importance of air load approximation technique is that it transforms the discrete frequency domain
data into a continuous time domain function, so that it can be used for aeroservoelastic studies. The
aeroservoelastic equations of motion must be translated into a first-order, time-domain (state-space)
form in order to use various current control design approaches, simulations, and optimization
procedures. The order of the resulting state-space model is a function of the number of selected modes,
the number of aerodynamic approximation roots, and the approximation formula, while this
transformation requires the aerodynamic matrices to be approximated by rational functions (ratio of
polynomials) in the Laplace domain. Methodology Structural modelling and meshing is done to carry
out flutter analysis in frequency domain. Then unsteady aerodynamics forces is extracted in modal
domain. By implementing Matrix Polynomial Approach, the three dimensional discrete aerodynamic
parameters is transformed into continuous function, thus facilitating to build a Linear Time-Invariant
(LTI) state-space system. The state-space model built is a Multiple Input Multiple Output (MIMO)
system that can be easily solved as an Eigen value problem. From the characteristic (Eigen value) value

176
problem, the dynamic instability conditions are determined for predicting the onset of flutter in time
domain. This approach is bench marked by validating the flutter results obtained from the simulation in
comparison with the NASTRAN flutter result. In the proposed work, it is directed to validate the
procedure by using a simple aluminum cantilever plate, and thereby studying the novelty in dealing with
the aeroelastic studies more efficiently and practically.

177
 Analysis and control of Aeroelastic performance of delaminated
composite plate using AFC

Jayant Prakash Varun1 and Prashanta K. Mahato2

1,2
Indian Institute of Technology (Indian School of Mines), Dhanbad, Department of Mechanical
Engineering, Dhanbad -826004, Jharkhand, India
Email: pkmahato.iitism.ac.in

Abstract. Aeroelastic analysis of a delaminated composite plate with integrated active fiber composite
(AFC) as actuator/sensor is considered for the present study. A region-wise approach is adopted to
incorporate delamination defects at the mid-plane of eight layered laminate. Firstly, first-order shear
deformation theory based finite element code is written in MATLAB to perform modal analysis of smart
delaminated composite plate followed by flutter analysis in MSC/NASTRAN. Flutter velocity and
frequency are calculated for a laminate with square delamination. The effect of different locations of
delamination on flutter performance is also investigated. The delaminated plate performance is
compared with a healthy laminated plate and voltage-imposed actuators are used to enhance the flutter
properties which were degraded due to the presence of delamination defect. It has been found that the
presence of delamination in composite degenerates the aeroelastic performance which was later
improved by a voltage-imposed AFC actuator.

178
Effect of graphene nanoplatelets on the thermomechanical behaviour of
smart polymer nanocomposites

Nilesh Tiwari1 and A. A. Shaikh2

1,2
Mechanical Engineering Department, Sardar Vallabhbhai National Institute of Technology, Surat-
395007, India
Email: nileshbwtiwari@gmail.com

Abstract. Smart polymers have been in significant utilization for the various structural, aerospace,
flexible electronics and biomedical engineering applications. These polymer could be sensitive to heat,
electricity, moisture, pH or magnetic. Shape memory polymer (SMP) are one of these smart material
which are temperature sensitive. SMP have capability to deform into the programming orientation and
to regain its original state under the influence of heat above the glass transition temperature (T_g) of
SMP. In the present study, thermomechanical and morphological characterization of graphene
nanoplatelets (GNP) reinforced shape memory nanocomposites. Incorporation of 0.4 an 0.6% GNP in
the epoxy matrix considerably enhanced the elastic modulus of the nanocomposite prior to the glass
transition region. The improvement in the interfacial bonding between the nanofillers and matrix was
the primary cause of improvement which was depicted in the FESEM morphology. However, the decline
in the properties were observed at 0.8% GNP because of the initiation of agglomeration of nanoparticles
in the matrix. The simulation of the dynamic mechanical analysis was performed through the
phenomenological approach based on the theory of superposition. The comparison indicated appreciable
congruence which could be used as a reference for the future numerical investigations.

179
 Effects of vertical inclinations of square prism on the performance of
piezoelectric energy harvester: An experimental study

Rakesha Chandra Dash1, Dipak Kumar Maiti2 Bhrigu Nath Singh3

1,2,3
Department of Aerospace Engineering, IIT Kharagpur, India),
Email: rakeshdash22@gmail.com

Abstract. This paper experimentally investigates the effects of various orientations of a square prism
(about the vertical axis) on the performance of a galloping based piezoelectric energy harvester (GPEH).
Regulation of galloping amplitude at constant wind speed is the prime objective. Again, it is found that
5 degree rotation of the square prism about the vertical axis produces more power compared to
conventionally used upright square cylinder. This research can be utilized to design a GPEH with a
movable bluff body that can produce specific power output in a natural fluctuating flow field without
any structural damage.

180
 Electro-mechanical Impedance response of delaminated glass-fibre
composite beam

Umakanta Meher1, Praveen Shakya2 and Mohammed Rabius Sunny3

1,3
Indian Institute of Technology Kharagpur, Kharagpur, West Bengal, 721302, India
2
Malla Reddy College of Engineering and Technology, Hyderabad, India
Email: umakanta.meher11@gmail.com
s
Abstract. The Electro-mechanical Impedance (EMI) technique has been gaining wide acceptance in
various engineering applications for structural health monitoring purpose since last two decades due to
its ease of implementation. In this work, the EM response of a delaminated composite beam is studied
for some possible delamination scenarios. At first, glass-fibre composite was fabricated by standard
vacuum resin infusion process. The surface bonded PZT patch and the host structure interaction was
obtained by an E4990A impedance analyzer in terms of impedance responses experimentally. The
impedance response of the pristine state composite beam was obtained through ANSYS and validated
with the experimental results. Various delamination scenarios between different layers of the composite
were incorporated in the ANSYS model to obtain the impedance signatures. The changes in EM
response of the structure due to occurrence of damage are observed to investigate the delamination here.

181
 Low-Velocity Oblique Impact Response of Pre-twisted Sandwich
Conical Shell with CNTRC Facings

Tripuresh Deb Singha1, Tanmoy Bandyopadhyay2 and Amit Karmakar3

1
Mechanical Engineering Department, Govt. College of Engineering and Textile Technology,
Serampore, Hooghly-712201, India,
2,3
Mechanical Engineering Department, Jadavpur University, Kolkata-700032, India

Abstract. A finite element approach coupled with higher-order shear deformation theory (HSDT) is
employed to investigate the dynamic responses of cantilever pre-twisted sandwich conical shells with
carbon nanotube-reinforced composite (CNTRC) facings and homogeneous core under low-velocity
oblique impact. The carbon nanotubes reinforcement in the facings follows either uniform or
functionally graded distribution along its thickness direction. A refined rule of mixture is utilized to
evaluate the effective elastic properties of the nanocomposite facings. The derived dynamic equilibrium
equations are based on Hamilton's principle, while the contact force between the spherical impactor and
the target sandwich shell is formulated using the modified Hertzian contact law. The solution of the
resulting equations in the time domain is obtained using Newmark time integration method. After
accomplishing the validity of the present model, some numerical examples are furnished to analyze the
influences of important parameters on the impact responses of the nanocomposite sandwich conical
shell.

182
 Development of a Flight Simulator for Low-End Computers

Amish Jindal1, Manini Mittal2, Gandharv Jaggi3, Abha Gupta4 and Shiv Mehta5
1,2,3,4,5
Aerospace Department, Punjab Engineering College, Chandigarh, India
Email: maninimittal1999@gmail.com

Abstract. Commercially available flight simulators are computationally heavy software and thus this
makes them inaccessible to people who have low-end compatible office laptops. This project aimed to
develop a flight simulator that is computationally less intensive and has a near-real world and optimized
physics model. We decided to use the Unity game engine since it’s user friendly and develops
applications to have a wide compatibility range. We kept physics and motion modelling as the highest
priority and graphics at the lowest priority. To make the flight mechanics model of our simulator
accurate and simultaneously less CPU intensive, certain non-iterative methods (as opposed to iteratively
solving NavierStokes Equation) are used for the computation of aerodynamic coefficients and were
further modified to account for change in parameters like Mach number and Reynolds number. Different
models and empirical data have been considered along with a custom wind and gust model to simulate
the environmental effects on the aircraft. Minimum graphics elements were added to minimize the
rendering requirements. The comparison with other available simulators shows that the present model
gives better performance on low-end computers, mainly because it has low CPU and GPU requirements.

183
 Numerical analyses of re-entry module - Apex cover separation
aerodynamics at low subsonic Mach number for various angles of attack

B Venkatshivaram Jadav1, Babu C2 and Vidya G3

1
Scientist/Engineer-SF, Aero Combustion Modelling Division,ADSG, Aeronautics entity, VSSC,ISRO,
Thiruvananthapuram, Kerala, India
2
Scientist/Engineer-SF, HSFC, ISRO, Bengaluru, Karnataka, India.
3
Division Head, Aero Combustion Modelling Division, ADSG, Aeronautics Entity, Vikram Sarabhai
Space Centre,ISRO, Thiruvananthapuram, Kerala, India
Email: jadav.shiva@gmail.com, babuc-hsfc@isro.gov.in, g_vidya@vssc.gov.in

Abstract. Aerodynamics of re-entry bodies is one of the most critical aspects of design for any space
missions. The velocity of a re-entry body varies from hypersonic Mach number in outer-inner
atmosphere to supersonic, transonic and finally subsonic Mach numbers till it touches down on earth.
Generally, a bluff body is chosen for re-entry missions. Flow over multiple bluff bodies (two or more)
in proximity is a very interesting topic and it has wide variety of applications in the area of aerospace
engineering. An attempt has been made to study the aerodynamics of pair of separating bodies in tandem
at low subsonic Mach number. This separation event occurs when apex cover is separated from re-entry
module before the deployment of drogue chutes. In this study re-entry module is considered as fore body
and apex cover as aft-body. CFD studies have been carried out to estimate drag coefficient of the aft-
body using CFD software FLUENT. The effect of gap (axial distance) on axial force coefficient of aft
body placed at various axial distances (∆X/D), at subsonic Mach number and different angles of attack,
is the subject of this paper. D is the maximum diameter of the fore body.

184
 Finite element analysis of biaxial cuboid voided slab under one way
bending load

N Nareshnayak1 and B N Rao2

1,2
Civil Engineering Department, IIT Madras, Chennai, Tamil Nadu, India
Email: nareshnyk8448@gmail.com

Abstract. This article presents a nonlinear finite element approach on the one-way flexural strength
determination of biaxial hollow slabs (voided slab). Voided slab appears as traditional solid slab.
Primary advantage of voided slab is lighter than conventional solid slab, as a result of it, studies have
done on capacity analysis of voided slabs. In the paper, eight node brick finite element slab model was
analysed. Nonlinearities of concrete and reinforcement bars was incorporated in the numerical
programme using stress-strain relationship of each material. Numerical load-deflection plot was
compared with experimental plot. Experimental and numerical results are matched appropriately in
terms of ultimate load and deflection. A parametric study was performed to study the impact of cuboid
voids on the deflection and ultimate load. Numerical findings were shown. Results obtained from the
numerical analysis showed that presence of voids will significantly affect the initial stiffness and not the
ultimate load.

185
 A detailed analysis of improved mathematical models of secondary
velocities along perpendicular and transverse directions for steady
uniform turbulent flow

Titas Chattopadhyay.
Department of Mathematics, NIT Jamshedpur, Jharkhand-831014, India.
Email: chatterjeetitas1610@gmail.com, tusu.max09@gmail.com

Abstract. Cellular secondary flows are generally present in turbulent flows through natural or artificial
streams / chennels and significantly modify the characteristics of turbulence and primary flow. In this
study, the proper mathematical models of secondary velocities along vertical and transverse directions
are derived for steady turbulent flows. Till now most of the studies regarding secondary currents
reported in the literature assume the models numerically or empirically using boundary conditions.
Starting from the continuity and Reynolds averaged Navier-Stokes equation, first the equation is derived
and then using appropriate boundary conditions the analytical models for cellular secondary currents
are developed using the separation of variable method and Fourier sine series approximation. These
models include the effects of viscosity of the fluid and the eddy viscosity model of turbulence. Models
are validated with existing experimental flume data for the rectangular open channel, open compound
channels, and duct flows, and satisfactory results are obtained. Further, models are also compared with
empirical models from literature to show the effectiveness of the proposed models. Apart from these,
the obtained results in this study are used to investigate the effect of secondary current on settling
velocity and stream-wise Reynolds shear stress. Effective alternate models for the settling velocity
vector and the Reynolds shear stress distribution in a cross-sectional plane are proposed. Both these
models are also validated with experimental data as well as previous models. To get quantitative idea
about the prediction accuracy of experimental data of the proposed models, error analysis has been
carried out and results show that present models are more effective then all previous models. Finally,
all results are justified from a physical viewpoint. This study proposes effective mathematical models
of vertical and transverse secondary velocities in steady uniform turbulent flows through open
rectangular channels, compound rectangular channels and closed ducts. The work has represented the
consideration of viscous effect in the model, the new solution methodology, and the broad applicability
of the proposed model. This study is further applied to investigate the effects of secondary currents on
the hindered settling velocity vectors and stream-wise Reynolds shear stress distributions in a cross-
sectional yz plane. New effective alternative models for settling velocity vector and cross-sectional
Reynolds shear stress distribution are proposed.

186
 Unsteady Simulation of Frontal Cavity in Supersonic Flows

Jayraj Deshmukh1, Dinesh Bajaj2, Devabrata Sahoo3 and Ashish Vashishtha4

1,2,3
Department of Aerospace Engineering, School of Engineering, MIT ADT University, Pune, India
4
Department of Mechanical and Aerospace Engineering, Institute of Technology Carlow, Ireland

Abstract. This study is motivated to develop the understanding of bow-shock instability observed
around a frontal hemispherical shell in supersonic flow through numerical simulations. This kind of
unsteadiness is generally observed in the supersonic parachute decelerators adopted in many space
missions as well as during wind tunnel testing of rigid hemispherical shell in supersonic and hypersonic
flows. In very few previous numerical studies, initiation of rapid large amplitude fluctuation in bow
shock in front of hemispherical shell leads to failure in simulation. Hence, the principal objective and
novelty of the study is to capture and analyse the experimentally observed “large amplitude” shock
unsteadiness in front of hemispherical shell in a supersonic flow of Mach 4 using the recently emerging
numerical concept of Detached Eddy Simulations (DES) in two dimensional axisymmetric domain.

187
Turbulence model and grid Sensitivity analyses of T-shape tall building
using Computational Fluid Dynamics technique

Ajay Pratap1 and Neelam Rani2

1,2
Civil Engg. Department, Dr B R Ambedkar NIT Jalandhar,144011, India

Abstract. This paper represents the numerical study carried out on wind effects on T-shaped tall
building using computational fluid dynamics (CFD) technique. The boundary layer wind tunnel
experiment on the scaled model of T-shape building were conducted at Indian Institute of Technology
Roorkee, India. The numerical simulation is carried out in the ANSYS FLUENT in which the wind flow
parameters i.e., velocity and turbulence intensity profile obtained from experiment are validated
numerically. Sensitivity analyses for turbulence model and mesh convergence are conducted on T-
shaped tall building at a wind incidence angle of 0°. Three-dimensional Reynolds -average Navier-
Stokes (RANS) equation is used to conduct the sensitivity analyses in which four different turbulence
model are taken: Standard k-ε model, Renormalization Group (RNG) k-ε model, Realizable k-ε model
and k-ω shear stress transport (SST) model. The main aim of this study is to compare the wind pressure
coefficient obtained from sensitivity and mesh convergence analyses with the wind tunnel experiment
on the various faces of T-shape building at a wind incidence angle of 0° and identifying which turbulence
model and grid size is best fitted for the proper wind flow around T- Shaped buildings.

188
 Experimental study on two octave Indian flute acoustics

Praful K1 and Sudarshan B2

1,2
Department of Mechanical Engineering, B.M.S. College of Engineering, Bengaluru-560019,
Karnataka, India

Abstract. The Indian classical flute called ‘Bansuri’ is a side blown flute originating from the Indian
subcontinent. The air blow makes the oscillation of the air column in the flute passage and sounds
differently as the exit volume changes. Accordingly, the different notes are configured with an octave
and currently two octaves are in practice. In the direction of exploring the third octave nodes, the
standard two octave nodes are analyzed in the present study using the analytical correlations and
experimental data by frequency analysis performing the Fourier Transformation considering an ‘E’ base
flute. Technical parameters affecting the acoustics of flute such as note frequency, wavelength and
sound pressure levels are studied in detail using various diagnostic tools like sound pressure level meter
and MATLAB programming tool. The variation in such technical parameters corresponding to each
note of two octaves is described in detail with graphical results. It is observed that the frequency of the
middle octave notes is nearly two times of the lower octave nodes thereby octave shift forms.

189
 Applicability of duffing oscillator on the dynamic analysis of bistable
variable stiffness laminates

K. S. Akhil1, P. M. Anilkumar2 and B. N. Rao3

1,2,3
Structural Engineering Division, Department of Civil Engineering, IIT Madras, Chennai 600036
Email: ce18d755@smail.iitm.ac.in

Abstract. Bistable composites provide an alternative to traditional designs in shape-adaptable structural

systems due to their multiple stable equilibrium configurations. In this study, the response of a square
curved bistable plate has been analyzed by focusing on the snap-through mechanism. An appropriate
finite element model has been used to predict the load-deflection characteristics of the bistable plate.
Nonlinear dynamic analysis of bistable plates with large degrees of freedom can be computationally
expensive. The load-deflection response has been approximated using polynomial expansions, where it
has been included as the restoring force in the dynamic equations of motion. A single degree of freedom
(SDOF) model from literature is chosen for the present analysis. Single well and double-well potential
systems associated with the dynamic behavior of bistable variable stiffness (VS) plates are explored in
the analysis.

190
 Modeling and design of hybrid reluctance actuator for fast steering
mirror

Weipan Zhang1, Weipeng Li2 and Bin Ren3

1,2
School of Astronautics, Beihang University, Beijing 100191, China
3
China Academy Of Space Technology(Xian), Xian 710100
Email: liweinpeng@buaa.edu.cn

Abstract. As the key component of the fast steering mirror (FSM), the actuator’s quality directly
determines the performance of FSM. To achieve high compactness, high efficiency, large output torque
and good linearity, a new hybrid reluctance actuator for FSM (NHRA) is designed. In order to get high-
force density and small flux leakage, four permanent magnets (PM) are designed on the side near the
lens, which also make the NHRA has essentially linear characteristics by generating bias flux.
Meanwhile, to obtain maximum output torque in a limited size, the structural model of NHRA is
established in ANSYS Maxwell, and all structural dimensions are optimized. In addition, an analytical
model of NHRA is established via the equivalent magnetic circuit method. In order to improve the
modeling accuracy, both PM flux and coil flux leakages are taken into consideration. The theoretical
and simulation results are in good agreement，and both show that under the same volume, the output
force of NHRA is almost twice that of a state-of-the-art actuator HPHRA, while the linear characteristic
of the output is also improved.

191
 Quadratic Wachspress Shape Functions for Polygonal Finite Element
Method

Shalvi Singh1 and Pritam Chakraborty2

1,2
Indian Institute of Technology, Kanpur, Aerospace Engineering Department, India,
Email: shalvi@iitk.ac.in, cpritam@iitk.ac.in

Abstract. Voronoi tessellation can alleviate issues of discretization and skewed elements arising from
inappropriate meshing of complex domains. Significant reduction in computational cost can also be
achieved due to decrease in the number of degrees of freedom in the polygonal mesh. Polygonal Finite
Element Method (P-FEM) can also be effectively used to simulate crack propagation and fracture
problems. In P-FEM, the linear Wachspress rational polynomial shape functions are widely used since
they are comparatively easy to develop and fulfill all requisites of node-based shape functions such as
positivity, interpolation, and the partition of unity[1]. A plethora of examples in the context of elasticity,
linear elastic fracture mechanics and elastic plasticity using P-FEM can be found in the literature. The
higher order Wachspress shape functions are less popular. However, the higher order functions in the
same domain when compared to linear element can lead to less error and fulfil the C^1 continuity. The
higher order approximation can assist in capturing gradients in response more effectively with lesser
number of elements. Due to these inherent advantages, quadratic Wachspress shape functions have been
developed in this work for small strain elasticity and elasto-plasticity.

192
 Numerical Analysis of Aerodynamic Characteristic of Aircraft Wing
Using Cant-Angle and Taper Ratio

Sarvagya Srivastava1 and Dr.Dharamvir Mangal2

Abstract. Aerodynamic performance of an Aircraft is highly affected by the friction drag over the
surface and the induced drag due to wingtip vortices. To obtain an efficient wing configuration which
produces maximum lift these drag forces have to be reduced. A Numerical Analysis of Three
dimensional fluid flow over an aircraft wing is conducted to study the variation in lift-to-drag ratio by
varying cant-angle of the winglet and taper ratio of the wing. The simulation is performed with fixed
wing and air as a flowing fluid with static inlet temperature of 275k, constant density through control
volume and negligible heat transfer using CFX solver in ANSYS. The static outlet pressure was kept as
0.7846 atm. Twelve different configuration designed by varying taper ratio (0.6, 0.8, 1) and cant-angle
(0 , 30 , 60 , 90 )degrees to evaluate the effect on drag and lift force by comparing the lift-to-drag ratio.
The Spalart-Allmaras turbulence model used to study the effect of eddy-viscosity. Results shows that
with the use of winglet, the size of the wingtip vortices reduces and by reducing cant-angle the lift-to-
drag increases. On reducing the taper ratio the drag force decreases and hence the lift-to-drag ratio
increases.

193
Numerical Performance Studies of a Small Scale Horizontal Axis Wind
Turbine Blade with Humpback Whale Tubercles

Supreeth R1, S K Maharana2 and Bhaskar K3

1
Dept. of Aeronautical Engg, Acharya Institute of Technology, Bengaluru
Assistant Professor, Dept. of Aerospace Engg, R V College of Engg, Bengaluru
2
Dept. of Aeronautical Engg, Acharya Institute of Technology, Bengaluru
3
Dept. of Aerospace Engg, R V College of Engg, Bengaluru
Email: supreethr@rvce.edu.in

Abstract. Attributing to the idea of portable power generation, small scale wind turbines are
aggressively expanding across rural areas disconnected from the power grid. However, due to their small
size and low operating altitudes, the performance of the small wind turbines are severely affected
resulting in low power outputs. In the study, efforts are made to passively improve the performance of
a 2kW wind turbine baseline blade by implementing humpback whale tubercles. Tubercle geometry
with amplitude A(LEP) =5% and wavelength λ(LEP) =7% of the local chord ci is interspersed to the
leading edge of the baseline blade. Numerical evaluation of the blade performances at various flow
conditions proved the modified blade to outperform the baseline blade. From the outcomes, the tubercled
blade manifested a total power output P of 26% and coefficient of power CP of 7% greater than the
baseline blade at design conditions

194
 Numerical Investigation of Cavity Flow Field in Presence of Store

Bhaskar K1, Rakesh Kumar2, Punit N3, Gwalani4, Anagha Mandayam Bhulokam4,
Gargi S. Pantoji5 and Aishvarya D. Joshi6
1
Aerospace Engineering, R V College Engineering, Bangalore, Karnataka, India
2
Aeronautical Development Establishment, DRDO, Bengaluru, Karnataka, India
3
Mechanical Engineering, R V College Engineering, Bangalore, Karnataka, India
4,5,6
Aerospace Engineering, R V College Engineering, Bangalore, Karnataka, India

Abstract. Weapon bays are the internal store carriage of the aircraft and provide better aerodynamic
performance and stealth over external store carriage systems. However, the flow field within a cavity
results in numerous challenges for the carriage and release of weapons. This study aims to
computationally obtain the quantified effect of the interaction of a flow field with a store mounted in
two different cavity configurations. The cavity configurations selected are rectangular and oblong
hexagonal cavities with a length-to-depth ratio of 5 and width-to-depth ratio of 1, to simulate an open
cavity flow condition. Additionally, the geometries are differentiated by offset-to-depth ratios of 0 and
0.25 for rectangular and oblong cavities respectively. The store considered for the study is the B-57
model. The flow field is numerically calculated using ANSYS® Fluent, with a constant input free stream
velocity of 70m/s (M∞=0.2) at yaw angles = 0°-6°. The static-pressure distribution is studied for various
sections in the cavity in the presence of the store. Finally, the results obtained for both the cavities with
store in it are compared to understand the effect of change in cavity configuration on the flow field.
Moreover, the results of empty cavities are also studied and compared with the store-mounted cavities.

195
 Experimental and Numerical Simulation for Residence Time
Distribution of Deactivation Tank

Prince Kumar Jain1, Samiran Sengupta2, Vimal Kotak3, Kajal Dhole4, Nilesh Gohel5 and
Sujay Bhattacharya6
1,2,3
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai, India),
4
Research Reactor Services Division, Bhabha Atomic Research Centre, Mumbai, India),
5
Research Reactor Design & Projects Division, Bhabha Atomic Research Centre, Mumbai, India)
6
Reactor Projects Group, Bhabha Atomic Research Centre, Mumbai, India
Email: samiran1sengupta@gmail.com

Abstract. Deactivation tank is sometimes used in nuclear reactors to increase the delay time for the
radioactive fluid to decay its radioactivity level. Short lived but hard gamma emitters radioisotopes like
N-16 and O-19 are produced during nuclear fission reactions and lead to increase in radiation field in
working areas of process & equipment rooms. To reduce the radiation level, the fluid containing the
short-lived radioisotopes are passed through a deactivation tank. Time spent by fluid particle inside the
deactivation tank is important parameter to consider in design of the same. Experiments were carried
out to estimate the residence time distribution by injecting in pulse mode, aqueous NaOH solution at the
inlet of the tank with the fluid and by measuring conductivity of fluid at outlet of deactivation tank using
online electrical conductivity meter. CFD studies were also carried out using species transport method
and results are compared with experimental measurements to validate the model. The validated CFD
model can be used for predicting the delay time of larger deactivation tanks of similar geometry where
experiment may not be feasible.

196
Design and verification of electrical power subsystem for a student small
satellite “SSS-1”

Liu Bohan1, Yu Xudong2 and Huang Hai3

1,2,3
School of Astronautics, Beihang University, Beijing 100191, China
Email: hhuang@buaa.edu.cn

Abstract. As advances in space technology, much effort has been devoted to the field of microsatellite,
due to its cost-effectiveness for conducting various space mission. The present article investigates design
and verification of electrical power subsystem (EPS) for the SSS-1 platform, which is a student small
satellite proposed by Beihang University, Beijing, China. EPS consists of three units, including solar
array (SA), battery pack unit (BPU), and power control and distribution unit (PCDU). Their main design
index and the initial design results are first briefed. Due to the energy shortage arose from energy balance
analysis, an iterative design of the EPS has been adopted, involving optimization of the SA layouts,
over-discharging protection for BPU, as well as adjustment of payload strategy. To achieve this, the
EPS is modelled via MATLAB®/Simulink® combined with Satellite Tool Kit (STK) simulation, in
which sunlight conditions, photovoltaic cell equations and the characteristics of Li-con battery are
considered. The verification modelling results manifest that ultimate design of EPS is capable of
sustaining the energy consumption of SSS-1, and thus associated energy balance can be attained.

197
 Effect of Hygrothermal Environment on Dynamic Behavior of Folded
Laminated Composite Plate

Babu Ranjan Thakur1, Surendra Verma2, Bhrigu Nath Singh3 and Dipak Kumar Maiti4
1,2,3,4
Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, W. Bengal
721302, India
Email: brt.iitkgp@gmail.com, surendraverma2501@gmail.com, bnsingh@aero.iitkgp.ernet.in,
dkmaiti@aero.iitkgp.ernet.in
Abstract. In this paper, the effects of hygrothermal environment on the free vibration and transient
response of one-fold and two-fold folded laminated composite plates are analyzed. A nine-noded C0
continuity finite element approach utilizing a non-polynomial shear deformation theory is employed for
the analysis. To model the induced stress due to thermal loading, the Green-Lagrange non-linearity has
been employed. Newmark's method is employed to integrate the spatial-temporal partial differential
governing equations. The effect of the thermal environment on the natural frequency and transient
response of folded composite plates has been illustrated through various examples. The obtained
solution has been validated with the available solution in the literature. The effect of fiber orientation,
crank angle, and boundary condition is assessed extensively and some insightful solutions and
interpretations have been presented.

198
 PIC/MCC Simulation of Axial Ring-Cusp Hybrid Discharge in the
Micro Ion Thruster Ionization Chamber

Wei Liu1, Weizong Wang2, Guobiao Cai3, Shuwen Xue4, Yifei Li, Haibo Wang5
and Guangqing Xia6
1,2,3,4,5
Advanced Space Propulsion and Energy Laboratory (ASPEL), School of Astronautics, Beihang
University, Beijing 100191, People’s Republic of China
6
State Key Laboratory of Structural Analysis for Industrial Equipment, School of Aeronautics and
Astronautics, Dalian University of Technology, Dalian 116024, People’s Republic of China

Abstract. Micro DC ion thrusters have broad application prospects as the propulsion system of micro
spacecrafts due to their advantages of high discharge reliability and efficiency. The experiments in the
literature show that the plasma discharge under axial ring-cusp hybrid (ARCH) magnetic field has higher
discharge efficiency in the ionization chamber of micro DC ion thruster. In this paper, a 2D
axisymmetric particle in cell/ Monte Carlo (PIC-MCC) numerical model is developed for plasma
discharge under ARCH magnetic field. This model takes the thermal electron emission including the
Schottky effect, various collision processes and the uneven background gas density distribution in the
cathode-anode gap into account. The formation and transport process of DC discharge plasma are
presented and the spatiotemporal dynamic characteristics of plasma are investigated. The plasma
characteristics under the ARCH magnetic field and the traditional 3 ring-cusp field are compared and
the sensitivity of the thruster performance to the magnetic field intensity at the cusp point are explored.
The above results provide a further support for the design optimization of the micro DC ion thruster
ionization chamber.

199
 Aerodynamics Analysis of Fighter Aircraft in Formation Flight

Jaemuk Kim1 and Cheolheui Han2

1,2
Korea National University of Transportation, Chungju, 308-702, Republic of Korea
Email: chhan@ut.ac.kr

Abstract. Formation flight is one of typical methods that migrating birds use for a long distance flight.
It has been known that aircraft in formation flight have the advantage that their aerodynamic efficiencies
increase with a optimal combination of axial and lateral distance between the aircraft. The disadvantage
is that the slight change of the relative distance can result in the unstable operating conditions. In the
present study, a potential based panel method is utilized in order to compute the aerodynamics of the
aircraft in formation flight. In the conference, the effect of the changes in the relative distances(axial,
lateral, and vertical) on the aerodynamic performance will be addressed.

200
 Three-dimensional PIC-MCC Analysis of Ion Thruster Grid
Misalignment

Yifei Li1, Weizong Wang2, Guobiao Cai3, Chencong Fu4, Wei Liu5 and Guangqing Xia6
1,2,3,4,5
School of Astronautics, Beihang University, Beijing 100191, People’s Republic of China
6
State Key Laboratory of Structural Analysis for Industrial Equipment, School of Aeronautics and
Astronautics, Dalian University of Technology, Dalian 116024, People’s Republic of China
Email: wangweizong@buaa.edu.in

Abstract. The assembly deviation between screen and accelerator grid apertures is one of the critical
reasons for the erosion failure of optic systems of ion thruster, which can also cause an unexpected roll
torque about the ion beam axis. A three-dimensional computer model of ion optics is developed to
analyze the focusing properties and erosion characteristics of ion thrusters. In this model, the movement
of particles is conducted by the particle-in-cell (PIC) method, while the collision between different
species is conducted by the Monte Carlo collision (MCC) method. The influences of the non-uniformity
of neutral density and the charge exchange (CEX) collision are considered. In the present study,
variation of beam deflection angle with misalignment of apertures, acceleration voltage and current
density are investigated. The calculated space charge distribution is consistent with the results in the
literature. The results show that the upstream sheath of the grid is the main factor affecting the beam
deflection. The influence of sheath on deflection increases with the decrease of current density. In
addition, the erosion of accelerator grid caused by misalignment of apertures and CEX is also studied.

201
 Design of Propulsion System for Propeller-less UAV

Rohith J1, Shashank H K2, Akshay S Prasad3, Dheeraj R4 and B Sudarshan5

1,2,3,4,
Department of Mechanical Engineering, BMS College of Engineering, Bengaluru 560019, India
5
Department of Mechanical Engineering, BMS College of Engineering, Bengaluru 560019, India

Abstract. Unmanned Aerial Vehicles (UAVs) are extensively used in many applications, including drug
delivery, agricultural applications, fire monitoring, civil survey, etc. These uses make the UAV industry
have a positive growth trajectory in the future. The current generation UAVs consist of a propeller-
based mechanism that develops the thrust to propel the vehicle. The exposed blades of the propeller lead
to safety and efficiency issues. To overcome this, UAVs reported in the literature were depending on
combustion-based systems like micro gas turbine engines and internal combustion (IC) engines. In the
current study, we are attempting to design a novel battery-powered propeller-less propulsion system for
UAVs without any exposed blades. The preliminary CFD results have shown the enhancement in the
performance and efficiency of the propulsor.

202
 SCHEDULED LIST OF PAPERS

NAME OF THE AUTHORS PAPER TITLE

Titas Chattopadhyay A detailed analysis of improved mathematical models of
secondary velocities along perpendicular and transverse
directions for steady uniform turbulent flow
Sudip Chowdhury Dynamic response control of adjacent structures connected by
viscous damper using inerter-based isolation systems
Arun Kumar Perumal and Ethirajan Rathakrishnan Scaling law for core length in supersonic free jets
Dr. Rajesh Kumar and Pramodkumar Vanam Simulating the impact of ground vortex ingestion on inlet
performance
Aneesh Batchu, Bharath Obalareddy and Prabhakar Dynamic Modelling of a Porous Functionally Graded Rotor-
Sathujoda bearing System for Different Temperature Distributions
Bharath Obalareddy, Aneesh Batchu and Prabhakar Free Vibration Analysis of a Rotor-bearing System having
Sathujoda Corrosion Defect
Yagya Dutta Dwivedi, N Lakshmi Narasimhan, Parametric study of bio-inspired corrugated airfoil geometry in a
Jayendra Rajanala and Kameswara Sridhar Vepa forward flight at Reynolds number 80000
Arun Kumar, Sourabh Borchate and C.S. Upadhyay A numerical study of integrity of Z-pinned laminates
B Sudarshan, V Viswanath, S Mukund, J V Sujan AERODYNAMIC STUDY ON AIRFOIL WITH U-SHAPE
and S Suhas TUBERCLE GEOMETRY
P Srinivasa Murthy An Improved Unsteady CFD analysis of combined pitching and
plunging airfoil using OpenFoam
M V Nitya, Vineeta Bhat, Sai Swaroop and Snehal Numerical Simulation of flow over blunt body with Passive
UM Control Technique
Manoj K. Singh and R. Kitey Assessing post impact mechanical characteristics of glass fiber
laminates by using beam coupons: A simplistic approach
Kuldeep Narwat, Vivek Kumar, Simran Jeet Singh, Performance Analysis of Circular and Lemon Bore
Abhishek Kumar and Satish C Sharma Hydrodynamic Journal Bearing Considering Surface Roughness
and Shear Thinning Effect
Pushpendra K Kushwaha, Vivek Kumar, Vinay Performance analysis of rough surface multi-recess porous hydro-
Vakharia and Satish C. Sharma static thrust bearing
Shashank H K, Rohith J and B Sudarshan AEROACOUSTIC STUDY ON HVLS FAN BLADE WITH
SERRATIONS
Rohith J, Shashank H K, Akshay S Prasad, Dheeraj Design of Propulsion System for Propeller-less UAV
R and B Sudarshan
Madhusudhanan U and Rajesh Kitey Al/epoxy adhesion strength by a modified butt joint test
configuration
Ritik Saxena, Divyansh Tewari, Akshit Gupta and Comparative study of dampers on a G+26 storey building
Dr M Abdul Akbar subjected to lateral loading
Aritras Roy and Rinku Mukherjee Near - Wake Flow Structures of a Rectangular Wing at the Onset
of Stall
Amit Arora Flow modifications & capacity augmentation due to streamwise
deployment of longitudinal vortex generators in a finned tube
bank
Nilesh Tiwari and A. A. Shaikh Effect of graphene nanoplatelets on the thermomechanical
behaviour of smart polymer nanocomposites
Pranav H A and B Sudarshan Shock wave effects on Chitosan bio-polymer for drug delivery
applications

203
Aditya Deshpande and Bhrigu Nath Singh Effects of internal length scale parameter on damage initiation
and evolution using gradient enhanced damage mechanics theory
A Arun Kumar and Amit Kumar Onkar Robust flutter analysis of a sweptback wing using μ method
Sanjay A V and B Sudarshan Effect of oblique shocks interaction on the inlet structure in a
hypersonic flow
Praful K and Sudarshan B Experimental study on two octave Indian flute acoustics
Bipin Kumar Chaurasia and Deepak Kumar Modeling damage evolution of laminated composites under high
strain rate loading
Devjit Acharjee, Srijani Bandyopadhyay and Numerical Study of Tilted Multi-Storied RCC Buildings on
Debasish Bandyopadhyay Shallow Foundations Considering Soil-Structure Interaction
Dr. Pol Reddy Kukutla, Dr. Venkatesu Sadu, Dr. NUMERICAL STUDY OF MULTIPLE-IMPINGEMENT JET
Syamsundar C, Dr. Maruthi Prasad Yadav G and ARRAYS ON ISO-THERMAL HORIZONTAL FLAT PLATE
Dr.Sekhar Babu P
S. Mustafa Kazim, Kartik Prasad and Pritam A homogenized crystal plasticity model for lamellar transformed
Chakraborty β colony of titanium alloys
Ritwik Mandal, Tanmoy Bandyopadhyay and Amit Transient Low Velocity Impact Response of Functionally-Graded
Karmakar Rectangular Plates – A Finite Element Approach.
Akhila Rupesh Performance assessment of five probe flow analyser suitable for
wind tunnel calibration
Shalvi Singh and Pritam Chakraborty Quadratic Wachspress Shape Functions for Polygonal Finite
Element Method
Dr. Venkatesu Sadu, Dr. Pol Redy Kukutla, Dr. DESIGN AND PERFORMANCE ANALYSIS OF AXIAL
Syamsundar C and Dr. Sivaiah P FLOW WIND TURBINE FOR HOUSEHOLD APPLICATIONS
Gangadhar Venkata Ramana Pinapatruni, Sunil A Numerical Study on the Negative Lift and Point of Non-
Manohar Dash, Jit Sinha and Kalyan Prasad linearity in Lift Curve of NACA 0012 Airfoil at Low Reynolds
Sinhamahapatra Number
Manoj S Naik, Sumedha Y D, Anish G P Nand, Study of Stability Parameters for Multi-Rotor Aircraft using CFD
Yeshas M N Bharadwaj and Promio Charles F Analysis and Validation with Theoretical Calculations
Spandan Bandyopadhyaya, Rajesh Kitey and C.S. Effect of carbon black content on quasi-static compression
Upadhyay behaviour of filled rubber
Priyanka Nimar, Kanwarpal Singh and Arvind ICETACM2021-EXPERIMENTAL STUDY OF FLOW
Kumar BEHAVIOURS OF FLY ASH SLURRY WITH AND
WITHOUT CHEMICAL ADDITIVES
Inseok Baek and Seoksoon Lee Induction Heating of Thermoplastic using Fe3O4
Venugopal Mm, S K Maharana and Mahantayya K Experimental Prediction of Wind Flow and Pressure Distributions
Hiremath Around a Low-Rise Building
Suchintya Halder and Abhishek Hazra Effects of Column Orientation on Building Structure- Verified
Through Pushover Analysis
Banghyun Jo, Jaihyuk Hwang and Daesung Jang Drop Test of an Aircraft Landing Gear Equipped with MR
Damper
Promio Charles F and Vedavathi G A Unsteady Aerodynamic Force Approximation for Flutter
Prediction
Shine S R, Shantanu Saha, Harshavardhan E and Risk assessment of cerebral aneurysms using FSI
Jayanand Sudhir B
K. S. Suraj, P. M. Anilkumar, C. G. Krishnanunni Parametric perturbation studies on the behaviour of bistable
and B. N. Rao unsymmetrical laminates
Shivashree S Design and Numerical Study of Variable Geometry Scramjet
Inlet for Mach 5 to Mach 7
Swagatika Pradhan and Somnath Ghosh LES of compressible round jet impinging on a flat isothermal
plate

204
Hao Tian, Jikai Wang and Hai Huang APSCO SSS-1 Communication System Design and
Implementation
Jayraj Deshmukh, Dinesh Bajaj, Devabrata Sahoo Unsteady Simulation of Frontal Cavity in Supersonic Flows
and Ashish Vashishtha
Amit Arora Three dimensional computational investigation of the geometric
design of delta-type vortex generators deployed in finned tube
arrays
Apurba Das, Arghya Mondal, Palash Mondal, Porous Scaffold by Additive Manufacturing for Bone
Masud Rana, Amit Roy Chowdhury and Amit Replacement in Biomedical Application
Karmakar
Natraj H, B. Nageswara Rao and K. Srinivas Reddy Finite element modelling and Monte Carlo ray tracing for the
solar parabolic trough collector with torque box
Hiyeop Kim, Pyunghwa Kim, Yongun Jun and Prediction of Mechanical Properties for 3-D woven composite
Jungsun Park considering realistic features
Avnish Pandey and K V Nagendra Gopal Vibroacoustic analysis of simply supported and clamped
functionally graded sandwich plates under transient loading
Manjunath S V, Maharana Sarat Kumar and Abdul Study of effect of rotational rate of a cylinder on the volume
Sharief fraction of vapor formed during nucleate boiling phenomenon of
water
Amish Jindal, Manini Mittal, Gandharv Jaggi and Development of a Flight Simulator for Low-End Computers
Abha Gupta
Vipin Chandra and Pritam Chakraborty Comparison of Full-field Solution between Virtual and
Experimental Digital Image Correlation for Model Verification.
Samiran Sengupta, Vijay K. Veluri and Sujay Experimental Investigation of Siphon breaker for Small Pipe
Bhattacharya breaks
Chan Mi Song, Seung Joo Jo, Chang Hyun Lee, Design and Analysis of Active Phased Array Antenna for 80 kg-
Myeong Jae Lee, Seung Hun Lee, Sung Chan Song Class Micro-Satellite SAR
and Hyun-Ung Oh
Jongkee Ahn, Dongyeop Lee, Bohee Kim, Chiwon Mechanical and microstructural characterization of Incoloy 901
Kim, Hyun-Uk Hong and Je-Hyun Lee repair by DED for aerospace gas turbine engine parts
Ms. Swetha S, Dr. Sarat Kumar Maharana, Dr. Experimental study of inflight icing conditions on coefficient of
Abdul Sharief and Ms. Steffi Thangachan pressure distribution around NACA0012 aerofoil
Chenhao Xu, Chongwen Jiang, Siyuan Pi, Shuyao Numerical simulation of wind-driven rain on gabled roof
Hu and Zhenxun Gao buildings
Ravindar Reddy Dadapur, Chittimalla Srinu and Robust Navigation with NavIC Software Receiver using Vector
Laxminarayana Parayitam Delay Lock Loops
Song Xue, Tianyixing Han and Chongwen Jiang Numerical Study on Transient Transverse Jet Effect of the Two-
Dimensional Slot Under Supersonic Conditions
Kaidi Wan, Yunzhe Huang, Zhenxun Gao, Yong LES of a Swirl-Stabilized Turbulent Kerosene Spray Flame in a
He and Chongwen Jiang Model Combustor
Shenyan Chen, Xingwang Yan and Shuchong Design and analysis of thermal control system for SSS-1 satellite
Wang
Yipeng Zhang, Hai Huang and Shenyan Chen Structure analysis and optimization of SSS-1 microsatellite
Anirudh Chandramouli and Abhijit Sarkar Linearized control of an axisymmetric spinning top to a regular
precession trajectory
Shuanjun Liu, Hai Huang, Shenyan Chen and Jiayi Satellite topology and continuous size optimization based on
Fu Two-level multi-point approximation method
Samarth S Bhatt, Amritanshu Dixit, Ahmad Shaikh, A quasi-longitudinal study of the effect of hemodynamical
Tejas Canchi and Rangavittal Hk parameters on the biomechanics of rupture in Abdominal Aortic
Aneurysms

205
Apurba Das, Subhendu Pal, Korak Sarkar and Amit A Study on Vibration Characteristics of Cantilever Conical Shell
Karmakar Made of FG Sandwich Material with Porosity and Thermal Effect
Nikhil Pandey, Samiran Sengupta, Vijay K. Veluri, Experimental Investigation of Flow characteristics for Natural
Manoj Tilara and Sujay Bhattacharya Circulation Valve
Prince Kumar Jain, Samiran Sengupta, Vimal Experimental and Numerical Simulation for Residence Time
Kotak, Kajal Dhole, Nilesh Gohel and Sujay Distribution of Deactivation Tank
Bhattacharya
Vimal Kotak, Samiran Sengupta, Anil Pathrose, Theoretical & experimental study on a miniature jet pump with
Sugilal Gopalkrishnan and Sujay Bhattacharya low area ratio
C F Sagar Zephania and Tapas Sil An Improved Homotopy Perturbation Method to Study Damped
Oscillators.
Babu Ranjan Thakur, Surendra Verma, Bhrigu Effect of Hygrothermal Environment on Dynamic Behavior of
Nath Singh and Dipak Kumar Maiti Folded Laminated Composite Plate
Jeongseok Kang, Younglin Yoo, Hong-Gye Sung, The Spray Characteristics Of Pintle Injector Using Homogeneous
Minchan Kwon and Junyoung Heo Mixture Model And Eulerian To Lagrangian Transformation
Lavala Srinivasa Rao, Partha Mondal and Sudip Influence of tab blockage on asymmetric under- expanded sonic
Das free jet
Supreeth R, S K Maharana and Bhaskar K Numerical Performance Studies of a Small Scale Horizontal Axis
Wind Turbine Blade with Humpback Whale Tubercles
Vagish Mishra, Ashish Mishra, Luv Verma and Failure Mechanisms of SMA Reinforced Composites under
Anindya Roy Impact Loading
Nandni Sharma, Gaurav Chhabra and Abha Gupta Modelling and analysis of winglet morphing for aerial vehicles
Sidharth Pc and B.N Rao A comparative study of recent phase-field implementations for
fracture prediction in solids
Pabitra Maji and Bhrigu Nath Singh Third-Order Shear Deformation Theory for the Low-Velocity
Impact Response of 3D Braided Composite Plates
Vivek Khare and Sudhir Kamle Measuring deformation in lightweight structures with revamped
DIC system: wind tunnel study
Tripuresh Deb Singha, Tanmoy Bandyopadhyay Low-Velocity Oblique Impact Response of Pre-twisted Sandwich
and Amit Karmakar Conical Shell with CNTRC Facings
Bhaskar K, Rakesh Kumar, Punit N. Gwalani, Numerical Investigation of Cavity Flow Field in Presence of
Anagha Mandayam Bhulokam, Gargi S. Pantoji Store
and Aishvarya D. Joshi
Bhaskar K., Rakesh Kumar, Arjun R. Prasad, Numerical Analysis of Weapon Bay Cavities of Different
Akshay M. M., Rahul Ithal H. L. and Siddalingana Configurations
Gowda M. P.
Mahir Dursun A Review of Predictive Control for Autonomous Flight Systems
Agneev Roy and Somnath Ghosh LES of shock-turbulence interaction in a Bell-shaped Convergent
Divergent Nozzle.
Santosh Kumar Singh Study of evolving regular water-waves under steady wind forcing
K. S. Akhil, P. M. Anilkumar and B. N. Rao Applicability of duffing oscillator on the dynamic analysis of
bistable variable stiffness laminates
Hyunbum Park and Yonggyu Lee Numerical Analysis of Structural Design Result for UAV applied
to Composite Structure considering on Self-Healing Method
Rakesha Chandra Dash, Dipak Kumar Maiti and Effects of vertical inclinations of square prism on the
Bhrigu Nath Singh performance of piezoelectric energy harvester: An experimental
study
Jaemuk Kim and Cheolheui Han Aerodynamics Analysis of Fighter Aircraft in Formation Flight
Jinkyu Choi and Seoksoon Lee Heat Treatment of AISI 1045 Specimens using High-Frequency
and Simulation

206
Chun Wang The Effect of Mole Weight Ratio of Reaction on the Propagation
of Cellular Detonations
P. C. Harisankar, C. F. Sagar Zephania and Tapas Equilibration of Van der Waals liquid drop with vapour in
Sil smoothed particle hydrodynamics
Mohammad Amir, Mohammad Talha, Sang-Woo Stochastic finite element modelling of the graded cellular arches
Kim and Changduk Kong
Zhongyuan Chen, Shitao Wang and Wanchun Chen Connectivity Preserving Multi-Spacecraft Formation Control for
Trajectory Tracking with Obstacle Avoidance
Himalaya Sarkar, Pavan Kumar Yadav and Transverse-only VIV of a freely vibrating hybrid cylinder at low
Subhankar Sen Reynolds number
Liu Bohan, Yu Xudong and Huang Hai Design and verification of electrical power subsystem for a
student small satellite “SSS-1”
Bo Yin, Guowei Yang and Zhanzhou Hao A modified sharp interface immersed boundary method
Xiaoyan Zhang, Weipeng Li, Jie Liu and Shuo Design and development of a piezoelectric XY micro-
Yang displacement scanning stage
Zijian Liu, Weipeng Li, Hai Huang and Bin Ren Optimization Design of Modified Stewart Platforms for Isotropic
Force Output
Deepak K Pawar, Maulik Panchal, Paritosh Wall effect on the Drucker Prager model parameters for pebble
Chaudhuri, Ratna Kumar Annabatuala and beds in nuclear fusion reactor
Narasimhan Swaminathan
Hyoju Nam, Haejin Kwon, Keunho Yun, Jia Kim Performance Analysis of Autonomous Flight Models Based on
and Kyutae Cho Reinforcement Learning for Military UAV
Xiaopeng Gong, Yizhong Fang, Wanchun Chen Agile Turn Guidance Law based on Deep Reinforcement
and Zhongyuan Chen Learning
Weipan Zhang, Weipeng Li and Bin Ren Modeling and design of hybrid reluctance actuator for fast
steering mirror
Kartikeswar Dwibedy and Anup Ghosh Damage Analysis of Multi-layered Composite Structures
Xiangxiang Li, Wanchun Chen, Zhongyuan Chen Capture Region of Realistic True Proportional Navigation Based
and Yizhong Fang on Closed-form Solutions
Devashish Bhalla, Vidya Gurumurthy and Manoj T. Aerodynamic Characterisation of a Re-entry Module in
Nair Supersonic Flow Regime
Guo Dilong, Liu Wen and Yang Guowei Effects of jet flow on wake of high-speed train
Jie Huang, Guannan Zheng, Guowei Yang, Application of finite element direct integration method in flutter
Chengde Huang and Yingjie Yu analysis
Jianhongyu Li, Hai Huang and Shenyan Chen Sensor/actuator position optimization for large size structure
using multi-objective optimization
Sambhaji Lore, Aditya Deshpande and Bhrigu Nath Static and free vibration analysis of functionally graded shells
Singh using non-polynomial quasi 3D shear deformation theory
Md Gulam Sarwar, Priyank Kumar and Sudip Das Insight into the mechanism of drag reduction for a spiked blunt
body
Guowei Yang, Chengde Huang and Guangnan Numerical Analyses on Free-Play Nonlinear Aeroelasticity
Zheng
Yiqing Shen, Shiyao Li and Ke Zhang A robust fifth-order WENO-Z type scheme with improved
accuracy at second-order critical point
Umakanta Meher and Mohammed Rabius Sunny An analytical approach to sense the presence of damage through
electro-mechanical impedance (EMI) response for a step-lap joint
Ajay Pratap and Neelam Rani Turbulence model and grid Sensitivity analyses of T-shape tall
building using Computational Fluid Dynamics technique

207
Bhaskar K, Mithil K, Pushkar Chaudhary, Sacheet Study of influence of vortices on trailing airfoil
S Amblekar and Sachin Maruti Shet
B Venkatshivaram Jadav, Babu C and Vidya G Numerical analyses of re-entry module - Apex cover separation
aerodynamics at low subsonic Mach number for various angles of
attack
Haibo Wang, Guobiao Cai, Chencong Fu, Wei Liu Research on Thrust Measurement System Design and Intelligent
and Weizong Wang Thrust Prediction Method Applied to Micro-electric Propulsion
Wei Liu, Weizong Wang, Guobiao Cai, Shuwen PIC/MCC Simulation of Axial Ring-Cusp Hybrid Discharge in
Xue, Yifei Li, Haibo Wang and Guangqing Xia the Micro Ion Thruster Ionization Chamber
Yufeng Cheng, Jinrui Zhang, Guobiao Cai and Stably electrospraying Concentrated aqueous solution with outer
Weizong Wang ionic liquid
Yifei Li, Weizong Wang, Guobiao Cai, Chencong Three-dimensional PIC-MCC Analysis of Ion Thruster Grid
Fu, Wei Liu and Guangqing Xia Misalignment
Shuwen Xue, Yuanyuan Gao, Wei Liu, Yifei Li, Numerical investigation of discharge mechanism and plasma
Guobiao Cai and Weizong Wang behavior in an external discharge plasma thruster
Hai Huang and Jiayi Fu An aircraft wing structural layout and cross-sectional size
optimization design
Kunal Garg, Jathaveda M, G Vidya, Babu C, Dr CFD Investigation of Geometrical Truncation effect of Typical
Patil M M and Dr Ashok V Winged Re-entry Vehicle on Pressure Coefficient at FADS ports
Jayant Prakash Varun and Prashanta K. Mahato Analysis and control of Aeroelastic performance of delaminated
composite plate using AFC
N Nareshnayak and B N Rao Finite element analysis of biaxial cuboid voided slab under one
way bending load
Geetam Saha, Dibya Jyoti Basu, Aritro Roy Mitra Numerical study of a square plan shape building with corner
and Dipesh Majumdar modification
Pranjal Anand and Rajesh Ranjan Aerothermal Predictions of High-Pressure Turbine Flows Using
RANS Methods
Haseung Lee, Younggyu Lee, Changduk Kong and Study on Multiscale Modelling Method for Investigation on
Hyunbum Park Damage of Wind Turbine Composite Blade
Praveen Shakya and Umakanta Meher Flutter Investigation of MW Sized Hybrid Composite Wind
Turbine Blade
Chhote Lal Shah, Dipanjan Majumdar, Chandan Wake Dynamics of a Flexible Flapping Filament at Low
Bose and Sunetra Sarkar Reynolds Number
Kumar Sourav and Deepak Kumar New Response Branch for Undamped 2-DOF VIV of a Diamond
Oscillator
Peng Wang, Wanchun Chen and Zhongyuan Chen FOV-constrained 3D impact angle and impact time control
guidance
Shruti Rajpara and Rajesh Ranjan RANS modeling for short and long separation bubbles in flow
past low-pressure turbine cascades
Ayush Raikwar, Vidya Gurumurthy and Devendra Understanding the Strapon Separation Dynamics in atmospheric
Ghate phase
Rajesh Kumar, Pruthvi Narne and Amardip Ghosh Mode Transition in Strut Based Parallel Fuel Injection in
Scramjet Engine
Suman Karmakar, Tripuresh Deb Singha, Tanmoy First-ply failure load prediction of pre-twisted delaminated
Bandyopadhyay and Amit Karmakar composite conical shells
Ch Narendra Kumar and K P Sinhamahapatra Mixing characteristics of circular and elliptical twin jets
Istiyak Khan, Nilesh Gohel, Samiran Sengupta and Experimental Verification of Stiffness behavior of Multilayer
Sujay Bhattacharya Metal bellows
Umakanta Meher, Praveen Shakya and Mohammed Electro-mechanical Impedance response of delaminated glass-
Rabius Sunny fibre composite beam

208
Devjit Acharjee, Dibya Jyoti Basu and Debasish Numerical Study of the Effect of Shear Connectors in Insulated
Bandyopadhyay Sandwich Panel Building System
Kyungwon Oh and Changduk Kong A study on Applicability in Super Cavitation with SLBM
Vaibhav Suryawanshi, Shailesh Palekar, Prasad Based on Natural Frequencies, Crack Analysis of Fixed Support
Patare, Prasad Bojage and Atul Joshi Fibre Glass Composite Beam
Shailesh Palekar, Achchhe Lal, Prasad Patare, Atul Probabilistic Mixed Mode Stress Intensity Factors of Single Edge
Joshi and Prasad Bojage Cracked Laminated Composite Plates Using Stochastic Extended
Finite Element Method

209
 AUTHOR INDEX

A A. Shaikh 9,14, 179, 203 Gwalani 12, 195, 206

A.K. Ghosh 13, 30 Hai Huang 7,14,37, 42, 117, 123,149, 205
Ajoy Kanti Ghosh 14, 82 Hao Tian 7,158, 205
Akshay M. M 12, 35, 206 Hong-Gye Sung 38, 206
Amardip Ghosh 2, 7, 10, 12, 171, 208 Hyunbum Park 11, 13, 80, 106, 206, 208
Amit Arora 10, 50, 104, 203, 205 Inseok Baek 10, 135, 204
Aneesh Batchu 7, 39, 125, 203 J V Muruga Lal Jeyan 128
B Venkatshivaram Jadav 14, 184, 208 Jayanand Sudhir B 15, 78, 204
Bajrang Sharma 22 Jayant Prakash Varun 10, 178, 208
Banghyun Jo 10, 138, 204 Je-Hyun Lee 11,34, 205
Bhaskar K 12, 14, 35, 56, 194, 206 Jeongseok Kang 11, 38, 206
Bhrigu Nath Singh 2, 9, 12, 33, 61,120, 206 Jia-Lin Tsai 11, 18
Byungkyu Kim 85 Jiayi Fu 10, 117, 149, 205
C F Sagar Zephania 10, 148, 206 Jinkyu Choi 13, 165, 206
Changduk Kong 10, 14, 23, 92, 175, 207 Jongyun Oh 58
Chengde Huang 14, 40, 45, 207 Junyoung Heo 11, 38, 206
Cheolheui Han 10, 200, 206 K P Sinhamahapatra 10, 43, 208
Chongwen Jiang 11, 15, 72, 75, 170,205 K. S. Akhil 13, 190, 206
Chun Wang 44, 207 Kajal Dhole 8, 196, 206
Deepak Kumar 13, 173, 204, 208 Keunho Yun 69, 207
Devabrata Sahoo 7, 187, 205 Khogesh K Rathore 126
Devendra Ghate 9, 101, 208 Kiyoung Joo 85
Dongyeop Lee 34, 205 Kyungwon Oh 10, 92, 209
G Vidya 14, 150, 208 Lavala Srinivasa Rao 10, 47, 206
Getce Marcina A 41 Liu Bohan 14, 197, 207
Guangnan Zheng 13, 40, 207 Liu Wen 13, 89, 207
Guo Dilong 13, 89, 207 Liying Tang 73
Guobiao Cai 9, 15, 60, 109 Madhusudhanan U 8, 169, 203
Guowei Yang 13, 40, 45, 51, 207 Maharana Sarat Kumar 155, 205
210
Mahir Dursun 5, 8, 10, 93, 206 Titas Chattopadhyay 12, 186,203
Manini Mittal 7, 183, 205 Tripuresh Deb Singha 14, 152, 182, 206
Manoj T. Nair 11, 70, 207 Umakanta Meher 12, 15, 48, 122, 181,207
Md Gulam Sarwar 11, 100, 207 Varalakshmi T S 176
Mohammed Rabius Sunny 12,15,122,181, 207 Vijay K Veluri 112
Myeong Jae Lee 8, 153, 205 Wanchun Chen 9, 11, 62, 98, 140
Neelam Rani 11, 188, 207 Wei Liu 9, 60, 114,199, 200, 207
Nitin Mathew Daniel 166 Weipeng Li 9,14, 42, 131,191, 207
Palash Mondal 13, 168, 205 Weizong Wang 9, 15, 60, 109,200,208
Peng Wang 98, 208 Xiaoyan Zhang 14, 131, 207
Pol Reddy Kukutla 12, 162, 204 Yagya Dutta Dwivedi 7, 57, 203
Praful K 9, 189, 204 Yang Guowei 13, 89, 207
Pranjal Anand 9, 142, 208 Yeturi Sreenu 159
Pravalika R 161 Yifei Li 9, 114, 199,201, 208
Pyunghwa Kim 11, 156, 205 Yingjie Yu 14, 45, 207
Qiu Wang 160 Yipeng Zhang 12, 37, 205
R. Kitey 46, 203 Yu Xudong 14, 197, 207
Ratna Kumar Annabattula 174 Yunzhe Huang 8, 75, 205
Richard Wilson 166 Zhongyuan Chen 8, 62,98, 140, 154, 207
Rohith J 10, 36, 202, 203
S K Maharana 9, 90, 113, 194, 204, 206
Sanjay Mane 95
Saptarshi Basu 7, 20
Sarvagya Srivastava 193
Shalvi Singh 10, 192, 204
Shenyan Chen 7,8,14,37, 121, 149, 205
Shiyao Li 14, 103, 207
Shuchong Wang 14, 121, 205
Snehal U M 8, 74, 203
Steffi Thangachan 10, 87, 205
Sugilal Gopalkrishnan 8, 164, 206
Tanmoy Bandyopadhyay 13, 14,116,152, 182
Tianyixing Han 11,170, 205
211