ROCKET SCIENCE
at
BRAHMASTRA AEROSPACE SYSTEMS
INTERSHIP REPORT [18ASP102L]
submitted to
SRM INSTITUTE OF SCIENCE & TECHNOLOGY
By
VINOTH KUMAR G – RA1911019010100
In partial fulfilment for the award of the degree
of
BACHELOR OF TECHNOLOGY
In
AEROSPACE ENGINEERING
DEPARTMENT OF AEROSPACE
ENGINEERING SRM INSTITUTE OF SCIENCE
& TECHNOLOGY
KATTANKULATHUR 603203,
CHENNAI, INDIA.
July 2021
ACKNOWLEDGEMENT
Being a part of Rocket Science Internship with Brahmastra Aerospace Systems was
interesting. During these 15 days of internship, I learnt a lot on Rocket science,
especially on Rocket designing using “OPEN ROCKET” software.
I have to thank Mr. Subash P Kuppusamy, Founder & CEO of Brahmastra Aerospace
Systems, Mr. Manoj M Ganesan, instructor of Rocket Science Internship program and
Mr. Vignesh Ponnusamy, Design Engineer at Brahmastra Aerospace Systems.
Therefore, I am grateful to the people in Brahmastra Aerospace Systems for the chance
to make this Internship.
Further on, I want to thank the students and interns in the Rocket Science Internship
who made this demanding time joyful but always efficient.
I would to like to acknowledge my sincere thanks to our course guide [Mr. K.
IYNTHEZUTHON] for providing the facilities and incessant encouragement to
make the task successful. I am very grateful for his kind help and genuine advice to
me from time to time.
I am highly indebted to the then Department H.O.D [DR .L.R.GANAPATHY
SUBRAMANIAN] for granting me the permission to use this opportunity for the
best of cause in mid- semester break
SRM INSTITUTE OF SCIENCE AND
TECHNOLOGY
Kattankulathur,Kancheepuram Dt.–60320
BONAFIDE CERTIFICATE
Register no:
RA1911019010100
This is to certify that the internship report entitled "ROCKET SCIENCE AT
BRAHMASTRA AEROSPACE SYSTEMS" submitted by VINOTH KUMAR G of
the SRM Institute of Science & Technology, Kattankulathur, in partial fulfilment
for the award of Degree of Bachelor of Technology in Aerospace Engineering is a
bonafide record of the internship carried out by him during the academic year
2020-21.
Dr.L.R.GANAPATHY SUBRAMANIAN Mr.K.IYNTHEZHUTHON
(Professor and Head) (Course Faculty)
Department of Department of
Aerospace Engineering Aerospace Engineering
ABOUT THE INDUSTRY
BRAHMASTRA AEROSPACE SYSTEMS
No, 6/77,Balaraman street, Nanmangalam, Chennai - 117
Towards a prospective self-sustained India,
Brahmastra Aerospace Systems is a Aerospace & Defence start-up
committed with a team of innovators, enthusiasts, and thinkers established
in 2019 in Chennai.
Came up together with the intention of providing STEM Education based
on Aeronautics & Astronautics to students of various backgrounds. To
create a platform for Research & Development in the field of Aeronautics,
Aerospace & Defence Systems, so that we can exercise the current and
advancing technologies in the mentioned fields and be a forerunner and
self-reliant nation.
Mission’s of the industry:
●To provide STEM education based on aeronautics & astronautics,
which helps in creating an advanced society and bridging the social
gaps between humankind.
●conducting research and development in the areas of aeronautics,
aerospace, and defense systems. That creates an ecosystem of
technologies for the sustainable development of humankind.
CONTENT
1)INTRODUCTION
2)WORKING PRINCIPLE OF ROCKETS
3)CLASSIFICATION OF ROCKET ENGINES
4)PROPULSION
5)PARTS OF A ROCKET
6)PROBLEM STATEMENT
7)COMPONENTS DIMENSIONS
8)CALCULATIONS
9)ROCKET PARAMETERS
10)MOTOR COFIGURATION
11)DIFFERENT VIEW OF MODEL ROCKET
12)SIMULATION RESULTS
13.GRAPH
INTRODUCTION
What is a Rocket?
• A rocket is a projectile that spacecraft, aircraft or
other vehicle that obtains thrust from a rocket
engine.
• Rockets are one of the mode of Transport to reach
the Space for different purposes like to explore and
study the Space, the Planets or to even study the
EARTH, to communicate, to advance the
Technology by using different Satellites like
Communication Satellites, Remote Sensing
Satellite, Navigation Satellite etc.
WORKING PRINCIPLE OF ROCKETS
Rockets generally works under the law’s of
Physics. They are
1.NEWTON’S LAWS OF MOTION
2.LAW OF CONSERVATION OF MOMENTUM.
LAW’S OF PHYSICS:
NEWTON’S FIRST LAW OF MOTION (INERTIA):
An object at rest remains at rest, and an object in
motion remains in motion at constant speed and in a
straight line unless acted on by an unbalanced force.
NEWTON’S SECOND LAW OF MOTION (FORCE):
The acceleration of an object depends on the mass
of the object and the amount of force applied.
F
⃗
= ma⃗
NEWTON’S THIRD LAW OF MOTION (ACTION &
REACTION):
• Whenever one object exerts a force on another object,
the second object exerts an equal and opposite on the
first.
FA
⃗
= - ⃗F B
NEWTON’S LAW OF CONSERVATION OF
MOMENTUM:
• The conservation of momentum states that, within
some problem domain, the amount of momentum
remains constant.
• momentum is neither created nor destroyed, but only
changed through the action of forces as described by
Newton’s laws of motion
CLASSIFICATION OF ROCKET
ENGINES
PROPULSION
WHAT DO YOU MEAN BY PROPULSION?
• Propulsion is the action or process of pushing
or pulling to drive an object forward.
• Propulsion broadly classified into “AIR
BREATHING PROPULSION” and
“ROCKET PROPULSION”
AIR BREATHING PROPULSION
Air breathing propulsion systems use atmospheric oxygen, which is available
up to about 50 km of earth’s surface to burn the fuel stored on-board thereby
making the system much lighter, more efficient and cost effective.
Air breathing propulsion is a solution for a powered long return cruise flight
necessary for reusable launch vehicles.
Commonly aircraft are propelled by air breathing jet engines
Air breathing jet engines are nearly always Internal combustion engines that
obtain propulsion from the combustion of fuel inside the engine
CLASSIFICATION OF AIR
BREATHING PROPULSION
ENGINES
GAS TURBINE ENGINES
PISTON ENGINE
TURBOJET
2 STROKE ENGINE TURBOFAN
4 STROKE ENGINE TURBOPROP
TURBOSHAFT
ROCKET PROPULSION
• The propulsion of all rockets, jet engines,
deflating balloons, and even squids and
octopuses is explained by the same physical
principle: Newton's third law of motion.
Matter is forcefully ejected from a system,
producing an equal and opposite reaction on
what remains.
• Reaction propulsion wherein both the fuel
and the oxidizer, generating the hot gases
expended through a nozzle, are carried as part
of the rocket engine and helps to accelerate
the flow and produce thrust. Specifically,
rocket propulsion differs from jet propulsion
in that jet propulsion utilizes atmospheric air
as an oxidizer, whereas rocket propulsion
utilizes nitric acid or a similar compound as
an oxidizer.
CLASSIFICATION OF ROCKET
PROPULSION ENGINES
Rocket Propulsion
Classification
CHEMICAL SOLID ROCKET ENGINE
LIQUID ROCKET ENGINE
PROPULSION HYBRID
NUCLEAR Nuclear energy is the main source f
Nuclear propulsion engine
PROPULSION
Solar propul
SOLAR Sun as a ma
PROPULSION of energy
SOLID ROCKET ENGINE
Solid Rocket engine uses solid Fuel and
Oxidizer mixture
Easier and safer to store and use
ADVANTAGES
Can be produced at low-cost
Thrust-generating performance is inefficient
Propulsion cannot be fully stopped until the
DISADVANTAGES
propellant is completely consumed
LIQUID ROCKET ENGINE
• Liquid Rocket engine uses Liquid Propellant
tank and Oxidizer tank separately.
More efficient and generate more specific impulse than
solid rockets
ADVANTAGES
Can throttle thrust
Extra rocket mass for the transfer and storage tanks
Liquid propellants are more unstable, toxic, and highly
DISADVANTAGES
reactive
PARTS OF A ROCKET
PARTS OF A ROCKET
NOSE CONE:
• The nose cone of the rocket has a shape that causes the
air to flow smoothly around the rocket. It could be
PARACHUTE:
All model rockets require a recovery system to slow their
descent and return them safely to the ground. The most
common type of recovery system is the parachute. The
parachute may be made from thin plastic or cloth.
The parachute is expelled from the body tube by the ejection
ENGINE MOUNT:
• Engine Mounting brackets provide an important role to
support the engine with the chassis body and at the same
period they should provide the easy flexibility for repair,
FINS:
• The fins of the rocket provide aerodynamic stability in
flight so that the rocket will fly straight (in the same way
IGNITER:
• A rocket motor igniter provides the necessary heat
source to ignite rocket engines. It is typically made from
PROBLEM STATEMENT
Design and analyze
Model rocket with the
payload of 10 Kilogram
capable of reaching 30
kilometers
COMPONENTS DIMENSIONS
COM LE DIA THI MAT
PONE N ME CKN ERIA
NTS GT TER ESS L
H (cm) (cm) (DEN
(c SITY)
m)
NOSE 21 22 0.2 TITA
CONE NIU
(OGIV M
E) (4.5 g/
cm3)
NOSE 5.2 10 O.2 TITA
CONE NIU
SHOU M
LDER (4.5 g/
(OGIV cm3)
E)
BODY 15 22 0.2 STEE
TUBE 0 L
(7.85
g/cm3)
INNE 20 3.07 0.089 STEE
R L
TUBE (7.85
g/cm3)
CENT - 5 0.3 TITA
ERIN NIU
G M
RING (4.5 g/
cm3)
PAYL 2.5 2.5 - 815 g/
OAD cm3
(10 kg)
LAUN 6 2 0.1 CAR
CH DBO
LUG ARD
(0.68g
/cm3)
TRAN 25 22 0.2 CAR
SITIO DBO
N ARD
(CONI (0.68g
CAL) /cm3)
CALCULATIONS
• (Overall Mass ) = =+261840
MO
+ g
MP M PAY
ME
• (Propellant Mass ) = 130238 g
MP
• (Payload Mass )
M PAY
• (Empty Mass )
ME = 10000 g
• (Final Mass ) = -= 121602 g
MF MO MP
• PROPELLANT MASS = 131602 g
FRACTION (ζ) = / MP MO
• MASS RATIO = = 0.4974
M F / MO
= 0.5026
ROCKET PARAMETERS
• TOTAL LENGTH = 196 cm
• MAX. DIAMETER = 34 cm
• MASS WITHOUT MOTOR = 33136 g
• MASS WITH MOTORS = 261840 g
• MAX. VELOCITY = 1287 m/s
• MACH NUMBER = 3.92
• MAX. ACCELERATION = 286 m/ s
2
• APOGEE = 39705 m
• STABILITY = 0 cal
• CG = 119 cm
• CP = 118cm
MOTOR CONFIGURATION
• MANUFACTURER = CESARONI TECHNOLOGY INC.
• DESIGNATION = O8000
• TOTAL IMPULSE = 40960 Ns (100% O)
• AVG. THRUST = 8023 N
• MAX. THRUST = 8624 N
• BURN TIME = 5.1 sec
• LAUNCH MASS = 32672 g
• EMPTY MASS = 14062 g
DIFFERENT VIEW OF
MODEL ROCKET
DIFFERENT VIEW OF
MODEL ROCKET
DIFFERENT VIEW OF
MODEL ROCKET
GRAPH : 1
.
ALTITUDE VS VERTICAL VELOCITY
VS VERTICAL ACCELERATION
GRAPH : 2
.
MASS VS PROPELLANT MASS VS THRUST
GRAPH : 3
CP LOCATION VS CG
LOCATION VS THRUST
SIMULATION RESULTS
