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TEKNOFEST 2022
ROCKET COMPETITION
Medium Altitude Category
Critical Design Report (CDR)
Presentation
EVA X

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Team
Logo Team Structure
Asst. Prof. Doğu Çağdaş
ATİLLA
ALTINBAŞUNIVERSITY
Department of Electric and
Electronics Engineering
Project Advisor

Sohaib ABOUALYAN Eda Nur GÖKSAL

(Foreign student) ALTINBAŞUNIVERSITY
ALTINBAŞUNIVERSITY Software Engineering
Mechanical Engineering 4th year student
4th year student Team Vice Captain
Team Captain

Bedirhan KÖKSOY Gökhan EVLEK

ALTINBAŞUNIVERSITY ALTINBAŞUNIVERSITY
Computer Engineering Computer Engineering
2nd year student 2nd year student
Software Team Member Software Team Member

Kaan Avcı
ALTINBAŞUNIVERSITY Osamah HAMMOODI
Electric-Electronic (Foreign student)
Engineering
1st year student ALTINBAŞUNIVERSITY
Mechanical Engineering
Electric Team Member
4th year student
Mechanical Team Member
Pelin Tüfekçi
ALTINBAŞUNIVERSITY Ömercan LİMLİ
Industrial Engineering ALTINBAŞUNIVERSITY
Prep year student Mechanical Engineering
Mechanical Team Member 3rd year student
Mechanical Team Member

Rabia Kazaz
ALTINBAŞUNIVERSITY
Industrial Engineering
Prep year student
Mechanical Team Member

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Team Competition Rocket

Logo
General Information
About the Competition Rocket General Information Predicted Flight Data and Analyses

Measure Measure
Length (mm): 3090 Takeoff Thrust/Weight Ratio: 7.69:1
Diameter (mm): 130 Ramp Ascent Speed ​(m/s): 33.00
Dry Weight of Rocket (g): 19781 Stability (for Mach 0.3): 1.57
Fuel Mass (g): 4349 Maximum acceleration (g) 9.29
Engine Dry Weight (g): 2683 Maximum Velocity (m/s): 280.43
Payload Weight (g): 4158 Highest Mach Number: 0.84
Total Takeoff Weight (g): 26813 Apogee (m): 3395.00
Table 1. EVA X-1 General Information. Table 2. EVA X-1 Open Rocket Simulation Data.

Engine
Cesaroni M2020
Table 3. EVA X-1 Rocket Engine.

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Team
Logo General Design
Motor 936 mm
Avionics System Coupler
211 mm Root chord 250 mm
Nose Cone 390 mm 195 mm
Spin Height 120 mm

Rocket Diameter
130 mm

Rocket Diameter
130 mm

Tip Chord 50
mm
Boat Tail
Nose Cone PAYLOAD 148 mm Separation 100 mm
Separation
Shoulder 195 mm System 300 mm System 300 mm

Rocket Overall Length 3090 mm

Figure 1. CAD (Above) – Open Rocket (Below) Compression and Dimensions.

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Team
Logo Operation Concept (CONOPS)
Table 4. Flight profile.
Time (s) Altitude Velocity
[4] [6] (m) (m/s)
[5] [1] Launch 0.00 0.00 0.00
[2] RailTip 0.40 6.00 33.02
[3] Motor BurnOut 4.32 756 274.79
[4] Apogee 26.30 3395.00 12.30
DrogueParachute 26.30 3395.00 12.30
[5] Deployment

PAYLOAD/PAYLOAD
[6] Parachute 29.30 3357.75 20.21
Deployment
[7] MainParachute 153.77 493.60 21.46
Deployment
[8] Rocket 211.00 0.00 8.49
GroundHit
[7]
[3] [9] PAYLOAD 373.21 0.00 10.53
GroundHit

[9]

[1] [2]
[8]

Figure 2. Altitude-Time Chart of EVA X-1 Rocket During Flight.

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Team
Logo PDR - CDR Changes - 1
Table 4.1. PDR - CDR Changes – 1.
What Was The Content in What Happened to the
Subject of Change On Which Page in the PDR? On which Page in CDR?
PDR Content in the CDR?
Three members have been
Team Structure 2 Team members . 2
replaced with new ones.
Competition Rocket
3 PDR Tables 1. and 2. CDR Tables 1. and 2. 3
General Information
Rocket general open rocket Rocket general open rocket
General Design 4 4
details. details.
Flight Profile Table 5 Table 4. Flight Profile. Table 4. Flight Profile. 5

PAYLOAD Parachute color 22 Brown. Black. 35

PAYLOAD mass 25 4000 g. 4158 g. 38

2 Pistons with different
Recovery system 19 1 Piston used for recovery. 31-34
dimensions are now used.
Recovery activation Pyrobolt used to activate Servo Motor and CO2
19 33
system CO2 Inflators used to activate .
PAYLOAD 25 Dimensions Figure 15. Dimensions Figure 33. 38

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Team
Logo PDR - CDR Changes - 1
Table 4.2. PDR - CDR Changes - 1
What was the content in What happened to the
Subject of Change On which page in the PDR? On which page in CDR?
PDR content in the CDR?
Boat Tail 15 Wall thickness Figure 10. Wall thickness Figure 14. 18
Spill Hole Area is now 20%
Parachute 22 Spill Hole Area. of the parachute open 36
diameter.
Main avionics and BMP180 MPU6050
26 46
backup avionics sensors MPU6050 BMP180
Main avionics and
24,28 GY-NEO 6M GPS Grove - GPS (Air530) 39,49
payload GPS
Main avionics and
ATmega328PU and Arduino ATmega2560 and Arduino
backup avionics 26 46
Uno Mega Pro Mini
processor and card
Backup Avionics
32 XBee S3B Pro DRF7020D27 55
Telemetry

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Team
Logo PDR - CDR Changes -2nd
Table 5.1. PDR - CDR Changes -2nd
Subject of Change New Content Topic? Content Detail in CDR? Which Page in the CDR?
The IMU and pressure sensors between the
The main avionics pressure sensor was replaced two avionics were replaced, since it was
Main Avionics and Backup Avionics
with the IMU sensor and the backup avionics determined that the main avionics computer 46
Sensors
IMU sensor with the pressure sensor. had triggers other than pressure, which
facilitated separation.
The GY-NEO 6M GPS in the main avionics and Since the GY-NEO 6M GPS module could not
Main avionics and payload GPS payload has been replaced by the Grove GPS operate at the desired performance, it was 39,49
(Air530). switched to the Grove GPS (Air530) module.
The Atmega328PU processors with Arduino Uno Since the ATmega328PU processor with
Main Avionics and Backup Avionics in the main avionics and backup avionics have Arduino Uno card do not have enough pins,
46
Processor and Card been replaced by the ATmega2560 with Arduino multi-pin the ATmega2560 processor with
Mega Pro Mini. Ardunio Mega Pro Mini are preferred.
Since the Xbee S3B Pro module is not
Replaced the XBee S3B Pro module in the
Backup Avionics Telemetry available in Turkey, it has been replaced to 55
backup avionics with the DRF7020D27.
the DRF7020D27 module.
Battery information has been added to the Detailed information was given about
Avionics Computers Battery 46
avionics computers section. avionics batteries.
Avionics Computers and PAYLOAD Antenna information has been added to the Detailed information about avionic antennas
39,46
Antenna avionics computers section. was given.

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Team
Logo PDR- CDR Changes -2nd
Table 5.2. PDR - CDR Changes -2nd
Subject of Change New Content Topic? Content Detail in CDR? Which Page in the CDR?
Ground Station Processors types information Detailed information about ground station
Ground Station Processors 60
has been added to the ground station section. processors was given.
Ground Station Processors types information Detailed information about ground station
Ground Station Telemetry Modules 60
has been added to the ground station section. telemetry modules was given.
The detailed activation system used to
The activation system used to activate the
Separation Activation System activate the separation are servo motor and 32
separation has been changed
CO2 inflators

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Team
Logo Flight Simulation Report (FSR)
Flight Simulation Report (FSR) is located in a zip file in pdf format.

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Team
Logo Mass Budget
Mass Budget is located in a zip file in excel format.

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Team
Logo

Rocket Subsystem Details

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Team
Logo Nose Cone Mechanical View

Figure 3. Nose Cone 3D View (CAD).

Figure 4. Nose Cone Technical Drawing.

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Team
Logo Nose Cone –Detail
Table 6. Nose Cone Material Property [8,9,10].
Elastic modulus
Feature Part Manufacturing
(GPa)
Nose cone (without
E-Glass Fiber 72.3 Medium difficulty
tip)

Carbon Fiber - 230 Medium difficulty

Hard and
7075 T6 Aluminum Nose cone tip 71.7
expensive

• When choosing the material for the nose cone, the strength, durability, and heat resistance that the material must
withstand during flight were all taken into consideration. As a result, we chose E-fiber glass as the primary material since
it outperformed carbon fiber in terms of not blocking RF signals and being robust enough to withstand flight pressures,
as well as having a lower density than carbon fiber and aluminum.
• Because the tip of the nose cone absorbs the greatest heat during flight and aluminum is a superior material when it
comes to heat resistance, it was decided to go with a 7075 T6 Aluminum at the tip of the nose cone.

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Team
Logo Nose Cone –Detail
Table 7. Nose Cone Production Method.
Production Method Production Capability Explanation

CNC Aluminum Nose Cone An Aluminum cut of our nose cone shape would be produced by CNC cutting then a mold will be produced from fiber glass and
then produce a mold and Hard and Expensive polyester resin. Hand laying, with the number of layers desired, of Fiber Glass/Epoxy will then be done to the polyester mold
Vacuum. produced and vacuumed.
A mold has been made from the CAD of the nose cone and then 3D printed. The PLA printed mold had a 50% fill and a 1.2mm wall
thickness to make sure it can handle the vacuum process it will go through. Hand laying is then done, with the number of layers
3D Printed Nose cone Mold
Easy and Cheap desired, from Fiber Glass/Epoxy and finally vacuumed and placed in the oven to dry. This method is cheaper and easier as the mold
and Vacuum.
is immediately printed instead of producing an expensive Aluminum nose cone. For the nose cone tip however it will be CNC cut
from Aluminum as the part is small and wont cost much to manufacture.

To draw the nose cone curve, for the mold, in SolidWorks we used an equation driven curve using the parabolic nose cone
formula (1) shown below. The nose cone shoulder was then added at the end of the nose cone with a length of 1.5*diameter of
the rocket.
𝑥 2 Ln (length of nose cone) set as 390 mm 2
2
𝑥
−𝐾 ′ 2 𝑥 −1 𝑥 2
𝑦 =𝑅 𝐿𝑛 𝐿𝑛 (1) [3] , Rn (Base radius of nose cone) set as 65 mm So, 𝑦 = 65 390 390 ,𝑦 = 1 𝑥− 𝑥
2−𝐾 ′ 2−1 3 2340
K′ (Parabola type constant) set as 1

Simplified Quadratic Equation used for the

nose cone mold curve.

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Team
Logo Fins Mechanical Appearance

Figure 5. Fin 3D View (CAD), Assembled.

Figure 7. Fin Technical Drawing.

Figure 6. Fin 3D View (CAD), Singular.

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Team
Logo Fins –Detail
Table 8. Fins Material Property [8,9,10,11].
Elastic modulus
Feature Manufacturing
(GPa)

E-Glass Fiber 72.3 Medium difficulty

Carbon Fiber 230 Medium difficulty

7075 T6 Aluminum 71.7 Expensive

Plywood 8.30 Cheap and Easy

• Because the fins will be subjected to significant drag forces during flight, the material utilized must be strong enough to
withstand such forces while yet being light enough to avoid causing damage to the frame body. E-Glass Fiber was chosen
with these considerations in mind.
• A 3 mm block of E-Glass Fiber will be purchased, and water jet cut into the necessary shape as shown in Figure 7's
technical drawing. Water jet cutting has been chosen as better suited to cutting fiber glass blocks than a CNC machines.
The generated Fins will have sharp edges, which will increase the drag acting on the fins. To reduce the drag acting on the
fins, we will add an epoxy fillet to the sharp edges.

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Team Body Parts & Body Assembly Parts

Logo (STRUCTURAL) Mechanical View

Figure 8. Primary Frame 3D View (CAD).

Figure 10. Primary Frame

Technical Drawing.

Figure 9. Main Frame 3D View (CAD).

Figure 11. Main Frame

Technical Drawing.
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Team Body Parts & Body Assembly Parts

Logo (STRUCTURAL) Mechanical View

Figure 14. Boat Tail

Figure 12. Boat Tail
Technical Drawing.
3D View (CAD).

Figure 13. Engine Retainer Figure 15. Engine Retainer

3D View (CAD). Technical Drawing.
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Team
Logo Structural – Body Parts
Table 9. Structural – Body Parts Material Property [8,9,10].
Feature Part Elastic modulus (GPa) Manufacturing

E-Glass Fiber Rocket Frames 72.3 Medium difficulty

Carbon Fiber - 230 Medium difficulty
7075 T6 Aluminum Boat Tail 71.7 Hard and Expensive

• For the rocket frames' core material has been chosen as E-Glass Fiber since it has the lowest density of all the materials and
is still robust enough to withstand flight stresses. Furthermore, Fiber Glass will not interfere with the transmission of RF
signals from our avionics system to the ground station and sensor systems, which is critical to the success of our rocket.
Two samples of fiber glass and carbon fiber were manufactured and tested using compression testing to see if fiber glass
could resist the pressures of flight. Fiberglass was able to withstand a force of roughly 50 kN.
• For the Boat Tail and Engine Retainer 7075 T6
Aluminum was chosen since they will be influenced
by the heat generated by the motor during launch.

Figure 16. E-Glass Fiber (1) – Carbon Fiber (2) Sample Compression Test.
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Team
Logo Structural – Body Parts
Table 10. Structural – Body Parts Production Method.
Production Method Production Capability Explanation

An aluminum tube with a outside diameter of 130 mm would be parachuted and prepared to make a 2 female molds from them
Male and Female Very Hard and
using Fiber Glass and polyester resin. Once the molds are ready, we would hand lay, with the number of layers desired, on them
Mold Expensive
using Fiber Glass/Epoxy and vacuum after.
An aluminum tube with a outside diameter of 122 mm has been purchased to be used as our mold. After placing none stick plastic
on the mold hand laying of Fiber Glass/Epoxy is done with the desired number of layers to give us the outside diameter of 130
Male Mold Hard and less costy
mm. While the Fiber Glass/Epoxy is drying, the frame will be vacuumed to make it stronger. This method is cheaper and easier
than the one stated above so with that in mind we selected it.

CNC Aluminum Costy The boat tail and engine retainer will be made from aluminum and CNC cut as desired.

• Two pressure holes with a diameter of 4 mm will be included in the Primary Frame. A pair of three M3 thread holes will
also be drilled for shear pins to be broken by the separation systems. Another set of four M5 thread holes will be drilled
into the rocket to mount the avionics system and separation systems. Two 6.8 mm holes will be drilled within the body to
accommodate rotating switches for the payload and avionics computer.
• The Main Frame will include four M5 thread holes for mounting the coupler and eight M5 thread holes for mounting the
engine block. For pressure, another 4 mm diameter hole will be drilled between the fins. Finally, two 4 mm holes will be
drilled for the rail bottoms on each body, one at the beginning of the fins and the other under the avionics. Figures 10 and
11 show all these perforations.
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Team Structural – Body/In-Body Structural

Logo
Supports (Integration Bodies, etc.)

Figure 17. Coupler 3D View (CAD).

Figure 19. Coupler
Technical Drawing.

Figure 20. Engine Block

Figure 18. Engine Block 3D View (CAD). Technical Drawing.
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Team Structural – Body/In-Body Structural

Logo
Supports (Integration Bodies, etc.)

Figure 21. Engine Block One-Piece 3D View (CAD). Figure 22. Engine Block One-Piece Technical Drawing.

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Team Structural – Body/In-Body Structural

Logo
Supports (Integration Bodies, etc.)
Table 11. Structural – Body/In-Body Structural Supports Material Property[8,9,10,11].
Elastic modulus
Feature Part Manufacturing
(GPa)

E-Glass Fiber Coupler 72.3 Medium difficulty

Carbon Fiber - 230 Medium difficulty

Engine Blocks and Hard and

7075 T6 Aluminum 71.7
Centering Rings Expensive

Plywood Centering Ring 8.3 Cheap and Easy

• The coupler will be made of the same material (E-Fiber Glass/Epoxy) as the Primary and Main Frames for the same reasons, as
E-Glass Fiber is strong enough to handle the forces to it and light at the same time compared to other materials.
• The engine block, on the other hand, will be made of 7075 T6 Aluminum because it will have the motor right under it and will
hold the rocket together, using an M10 eyebolt screwed into it, so it must be strong and heat resistant.
• The engine tube will be constructed of E-Glass Fiber, and the centering rings will be mounted around it to hold the fins and
boat tail in place. A centering will be made of Plywood while the other two that will hold the fins and boat tail will be made of
7075 T6 Aluminum to assure a strong mount is done between the bodies.

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Team Structural – Body/In-Body Structural

Logo
Supports (Integration Bodies, etc.)
Table 12. Structural – Body/In-Body Structural Supports Production Method.
Production Method Production Capability Explanation

A male Aluminum tube with an outside diameter of 75.31 mm will be prepared by a turning machine and
Male Mold Medium then once it’s ready hand laying of E-Glass Fiber/Epoxy will be done to reach the desired outer diameter
and then vacuumed to have a stronger frame.
Centering rings will be cut as desired using CNC machine and then mounted into the inner tube using
CNC Aluminum/Plywood Medium Araldite 2015. The two aluminum centering rings will have 3 cuts in them to insert the fins inside them. The
boat tail will then be mounted at the back of the inner tube and centering ring as well using Araldite 2015.

The coupler will hold the two frames together (Primary and Main). The coupler will have one part attached by shear pins to the
primary body while the other side will be inside the main body and mounted with M5 screws. Once the separation is activated
for the release of the main parachute the piston separation system will push the coupler breaking the shear pins and separating
the bodies (Primary and Main) from each other and releasing the main parachute.

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Team Engine Section Mechanical

Logo
View & Detail

Figure 24. Engine Section Side View (CAD).

Figure 23. Engine Inserted Last (CAD).

As previously stated, the engine inner tube will be an E-fiber/Epoxy
tube that will be made by hand lying on a male aluminum mold,
and then vacuumed. The centering rings will be CNC-cut, and all of
the pieces will be assembled as illustrated with Araldite 2015. The
single-component will then be put into the main frame and
secured to the engine block with eight M5 screws. The engine will
be fitted as depicted in Figure 23 and followed by a rotating engine
retainer after the complete rocket has been built. Figure 25. Engine Section Side View Technical Drawing.
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Team Engine Section Mechanical

Logo
View & Detail
The fins and boat tail will also be mounted into the aluminum centering rings made. A video has been attached showing the
motor (in dark orange) being inserted last into the rocket.
Engine attachment video : https://youtu.be/X4Z-c_iVJyg

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Team
Logo Rocket Assembly Strategy

Figure 25. Exploded CAD of the rocket.

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Team
Logo Rocket Assembly Strategy
• The nose cone, primary frame, and main body are the three main components of the rocket. Two further elements will be
included in the Main Frame: a coupler and a one-piece engine block part.
• To start, the Avionics bay will contain the separation systems inside of it, they will be put into the primary body and secured
with four M5 screws. The Drogue parachute, which is linked to a 5 m shock chord, will then be placed into the primary body,
with the shock chord end secured to the separation system's M10 eyebolt with a locking carabiner.
• After that, the payload and its parachute will be fitted into the frame, behind the Drogue Parachute. Afterward, the other end
of the shock chord will be attached to the Nose Cone tips M10 eyebolt with a locking carabiner. The Nose Cone shoulder will
then be screwed into the Primary body with three M3 nylon shear pins. The main parachute will then be secured to the
opposite end of the separation system's M10 eyebolt using a locking carabiner, located on another 5 m shock cord, from the
other end of the primary body.
• The one-piece engine block part is constructed of an inner tube that houses the motor and is encircled by three centering
rings. The engine block ring will be fastened to one end of the inner tube, and the boat tail will be attached to the other. Two
centering rings will have cuts in them for the three fins that will be installed.
• When the one-piece engine block part is ready, it will be put into one end of the main body, where cuts for the fins will be
made. The coupler will be put in place with four M5 screws on the opposite end of the main body. After attaching the other
end of the Main Parachute to the M10 attached to the Engine block, the main body will be ready to be put into the primary
body, and three nylon shear pins will be screwed into the coupler and primary body to ensure that the two frames (Main and
Primary) are securely attached.
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Team
Logo Rocket Assembly Strategy
• Finally, a revolving engine retainer is used to hold the motor into the inner tube. The avionics bay will contain an extra space
specifically for the Referee Altimeter.

We will not be using a hot gas generator for our separation instead we are using a CO2/Piston system to activate our separations.
Attached below is a video to further clarify our rocket assembly strategy.
Rocket assembly video: https://youtu.be/X4Z-c_iVJyg

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Team
Logo Recovery System Mechanical Appearance

Figure 27. Parachute Section View,

Drogue and PAYLOAD Parachute Detailed CAD.

Figure 28. Parachute Section View,

Main Parachute Detailed (CAD).

Figure 26. Parachute Opening System.

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Team Recovery System–Parachute

Logo
Opening System
When it came to the separation system that would be employed, we weighed all of the choices before making a decision. When
we looked at hot gas generators, it appeared like it would be too dangerous to do, and we'd be limited in our testing since we'd
need a lot of gun powder. When we looked into mechanical spring systems, we found that they take too much weight and
volume to in the rocket, despite the fact that testing would be considerably easier. Finally, we settled on a cold gas
generators/Piston system, deciding that such a system would allow us to test without the risks of hot gas while also allowing us
to rerun tests easily.

We have purchased two 25 mm diameter aluminum pistons that will provide a force of roughly 260 N, which will be enough to
break the shear pins that are holding the nose cone and the main body to the primary body. Each system will be triggered using
a servo motor and a tiny CO2 inflator, as shown in Figure 28. When the servo motor receives a signal from our avionic computer,
it will rotate, pushing the CO2 inflator with a torque of 4.2 kgf.cm, which will release the compressed CO2 into the piston, and
push an Aluminum plate towards either the coupler or the nose cone shoulder with the stated force, breaking the nylon shear
pins that hold the frames together. One piston has two servo motors and two CO2 inflators linked to it; the other piston, on the
other hand, travels through the avionics bay and is mounted on the interior. The servo motor wires also pass through to connect
to the computers. The main parachute separation will be activated by the piston that travels through the avionics bay, while the
drogue and PAYLOAD parachute separation will be activated by the piston that has the servo motors and CO2 inflators. The
separation system will take 448751.99 mm3 of volume inside the rocket.

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Team Recovery System–Parachute

Logo
Opening System
Aluminum Plates that will
CO2 Cartridges and
break the shear pins
Inflators
Servo motors that will
activate the separation
systems

25mm Diameter Piston that

will produce around 260 N
force
Figure 29. Parachute Opening System
Detailed (CAD).
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Team Recovery System–Parachute

Logo
Opening System
Once the rocket reaches apogee, the first recovery
phase will begin. The avionics system will transmit
a command to the appropriate servo motor, which
will then push the CO2 inflator, which will then
force the payload into the nose cone shoulder,
breaking the shear pins. The piston will
Figure 30. 1st Recovery Phase not separate the rocket, but will also force the
Detailed (CAD). parachutes outside of it, kicking off the first phase
of recovery.
The second phase of recovery will begin about
500 meters high. The avionics system will send a
signal to the relevant servo motor to pressurize
the CO2 inflator and push it with the
required force to break the shear pins attached to
Figure 31. 2nd Recovery Phase
the coupler. As a result of the shock chord's
Detailed (CAD).
descent, the main parachute is pushed outside
the rocket, initiating the second recovery phase.
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Team Hot Gas Generator

Logo
Requirements
We will not be using a hot gas generator for our separation.

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Team
Logo Recovery System–parachutes-one
Because of its strong heat resistance and
durability to bear flight forces while also being
light, Ripstop Nylon was chosen as our
parachute material. For the production of each
of the parachutes, calculations were produced
as illustrated in Sheet 1. The results of the
calculations will be supplied to a tailor together
with the amount of fabric required for
manufacturing.
Table 13. Parachutes Features.
Sheet 1. Parachute Fabric Open Spill Hole
Area Descent
Parachute Material Color Geometry Mass (g) Diameter Diameter
Calculations Sheet. (m) (m)
(m2) Velocity (m/s)

The parachutes were designed in Drogue Parachute

40D Ripstop
Red Hemispherical 115.00 1.20 0.24 1.0857 20.26
Nylon
a hemispherical shape because it
40D Ripstop Orang
is the easiest to manufacture and Main Parachute
Nylon e
Hemispherical 435.00 2.70 0.54 5.4965 8.57
calculate the fabric amount while 40D Ripstop
PAYLOAD Parachute Black Hemispherical 70.40 1.10 0.22 0.9123 10.53
maintaining the desired fall rates. Nylon

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Team
Logo Recovery System–parachutes-2nd
Table 14. Parachutes Descent Calculations .
Open Spill Hole Calculated
Air Density at Descend
Parachute Mass to carry (kg) Diameter Diameter Area (m2) Descent Velocity
Altitude (kg/m3) [2]
(m) (m) (m/s)
Drogue
18.306 1.007 1.20 0.24 1.0857 20.26
Parachute
Main
18.306 1.112 2.70 0.54 5.4965 8.57
Parachute
PAYLOAD
4.158 1.007 1.10 0.22 0.9123 10.53
Parachute

Using the velocity during recovery equation (2) [1] the descent velocity was calculated and recorded in Table 14. Where W is
the weight to be carried by the parachute in kg, Cd is the coefficient of drag, 𝜌 is the air density at descending altitude in
kg/m3, and A is the area of the parachute in m2.

2𝑊
𝑉= (2) [1]
𝐶𝑑𝜌𝐴

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Team
Logo Recovery System–parachutes-3rd
Rocket Recovery Process Payload Recovery Process
Table 15. Rocket Recovery Components. Table 16. PAYLOAD Recovery Components.
Copmonent Role in the Recovery Mission
Copmonent Role in the Recovery Mission
Grove - GPS (Air530) Module Data of altitude, latitude and longitude information
GY-NEO 8M GPS Module needed for recovery. Data of altitude, latitude and longitude information
Grove - GPS (Air 530) Module
needed for recovery
LoRa SX1278 Telemetry Module Transfer of data from GPS modules to ground
DRF7020D27 Telemetry Module station. Transfer of data from GPS modules to ground
LoRa SX1278 Telemetry Module
station
433 MHZ TX433-JKD-20P Antenna Ensuring the operation of telemetry modules
5V Buzzer Assisting with sound 433 MHZ TX433-JKD-20P Antenna Ensuring the operation of telemetry modules

During the rescue, the main avionics and backup avionics GPS The Grove - GPS (Air530) GPS module, which is in the payload
modules, which play an active role in the rocket, will transmit and plays an active role during the rescue, will transfer
altitude, latitude, and longitude data to the ground station altitude, latitude, and longitude data to the ground station
with a 5 MHz frequency by LoRa SX1278 and DRF7020D27 with a 5 MHz frequency the LoRa SX1278 telemetry module in
telemetry modules, in line with ANNEX-8 requirements. The line with the ANNEX-8 requirements. The data will be
data will be transferred to the ground station on the 433 MHz transferred to the ground station on the 433 MHz band and
band and with the data packaging on page 38. A 433 MHz with the data packaging on page 28. A 433 MHz TX433-JKD-
TX433-JKD-20P antenna will be used for the telemetry 20P antenna will be used for the telemetry modules to work.
modules to work. 5V Buzzer will be used to assist with sound
during recovery.
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Team
Logo PayLoad
The PAYLOAD will have a hole in the
plexiglass through which a rotating switch
will be linked to turn it on; the switch will
then be connected to another switch
located on the rocket's surface, allowing the
payload to be turned on from the outside.
As the first recovery phase begins at apogee,
the piston system will get a signal from the
avionics to push the PAYLOAD against the
nose cone shoulder, breaking the shear pins,
and pushing the PAYLOAD outside the rocket Figure 33. Payload Technical Drawing.
Figure 32. PAYLOAD 3D View with its parachute. The PAYLOAD will be
(CAD). roughly 4158 g in weight.

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Team
Logo PayLoad
Table 17. PAYLOAD Components .
Component Product Name/Code Purpose of Duty Payload Recovery
Processor ATmega328PU Processor Giving the necessary commands to the sensors and processing the data.
Pressure sensor BME280 Pressure Sensor Calculation of pressure, temperature and humidity data.
Enabling the transmission of data from the GPS module to the ground
Communication Module LoRa SX 1278 Telemetry Module
station.
Grove - GPS (Air530) GPS Sending the necessary data for the recovery process to the ground
GPS module
Module station with the help of the telemetry module.
Battery GP GP1604AU Alkaline Battery Ensuring that the necessary power is supplied to the system.
Figure 34. PAYLOAD Avionics. Antenna TX433-JKD-20P 433 MHz Getting the telemetry module working.

The payload will transmit the BME280 sensor pressure, temperature, and humidity data, and the Grove - GPS (Air530) module
ANNEX-8 requirements of altitude, latitude, and longitude data via telemetry to the ground station with a frequency of 5 Mhz.
LoRa SX 1278 telemetry module and TX433-JKD-20P antenna operating in the 433 MHz band were selected for data transmission.
Data packet <PACKAGE NUMBER>;<TEAM ID>;<GPS ALTITUDE>;<GPS LATITUDE>;<GPS LONGITUDE>;<PRESSURE>;<TEMP>;
<HUMIDITY> will be in the form. The data received by the LoRa SX1278 in the ground station will be sent to the computer with
the Arduino Nano. The data will be displayed on the screen with the application designed by EVA X, Figure 56 on slide 61 .and
location data will be obtained for recovery. The data on the computer will be transferred to the RGS device with the packaging in
accordance with the ANNEX-8 requirements and the data will be transmitted to the referee ground station.
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Team
Logo Recovery System Prototype Test
In the shared test calendar, green boxes indicate the tests that will be completed during the CDR phase. All tests will be held at
Altinbas University Mahmutbey Campus.

Table 18. Schedule of Recovery System Tests.

2022
May 1st May 6th May 8th May 11th
Prototype Manufacturing
Parachute Opening Test
Separation Activation Test
CO2 Recovery System Test
Parachutes Strength Test
Shock Chord Strength Test

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Team
Logo Recovery System Prototype Test
As for the recovery system prototype tests, a prototype nose cone and frame are being prepared and will be ready on the 6 th of
May for testing. Once the protypes are ready a video will be shot from the 6th to 11th of May.

• Prototype level assembly and setup stages of the recovery system and functionality tests:
In the video it will show how the separation system will be assembled into the primary frame with the parachutes and shock
chord and a test of the first and second recovery phase will be done showing the nose cone and coupler being separated from
the primary frame thanks to the CO2 Piston system force that will break the nylon shear pins and releasing the parachute outside.
Success in this test will show that the parachutes will be released out of the rocket and will be functional for recovery and that
the separation will be also be successful.

• Parachutes Opening/Functionality Tests:

The parachutes opening tests will also be done by releasing the folded parachutes out a moving car and held to check if the
parachutes would open once released out the rocket. Also, another test will be done were around 4 kgs of weight will be
attached to the parachutes and released from a certain height showing it can handle descent forces. Once these tests are done
and finished it will proof the functionality of our systems.

Tests will be uploaded on YouTube on our channel and also uploaded into the system before the 12th of May Deadline:
Recovery Prototype Test: [Recovery Prototype Test YouTube link will be placed here]
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Team
Logo Analyzes
Structural/Mechanical Strength Analyses and Computational Fluid Dynamics Analysis were both performed using ANSYS
2020 R1. First, as shown in Figures 35 and 36, a mesh was created for the complete rocket as well as the nose cone. These
meshes were created using a specific body scaling technique in which the element size was reduced near our body. Our
boundary conditions have now been specified as a velocity intake and a pressure outlet, with walls on the other sides. We
created an inflated section surrounding the body, with sizes calculated based on the Y+ value of 100.

Figure 35. Mesh of Entire rocket. Figure 36. Mesh of Nose cone.

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Team
Logo Analyzes
For the structural/Mechanical strength Analyses, the CAD drawing of our rocket has been uploaded into ANSYS and materials
decided earlier in the reports were assigned. We applied some boundary conditions such as pressure effect at 3000-meter
altitude as 0,07 MPa and drag force which affects directly the front section area on X-axis.

The results demonstrate that our rocket, which is made up of 70% E-glass fiber and 30% Aluminum 7075-T6, has enough
durability at 3000-meter Altitude. On the engine block side, deformation was measured in fin plates, and stress was
measured in the engine block. For our rocket design, these values are acceptable.

Figure 37. Total Deformation on Rocket. Figure 38. Equivalent Stress acting on the Rocket.

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Team
Logo Analyzes
We used velocity inlet boundary conditions on the Z-axis for the nose cone. We utilized SST-k omega as a viscosity model and
280 m/s as an inlet value, both of which were supplied through open rocket simulation. Because the rocket is the interval in
the atmosphere, we chose 1 atm as a pressure exit. We choose 1.007 kg/m3 as a reference number since it is the density at
apogee, and the front sectional area is 0.03 m2 as computed from the SOLIDWORKS CAD model. We employed pressure
velocity as a solution approach, with the solar gradient determined using the least-squares method and the pressure and
momentum gradients chosen in the second order. This case is iterated 500 times and is taken as one state of the flight.

Figure 40. Nose Cone Velocity Streamline.

Figure 39. Nose Cone Velocity Contour.
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Team
Logo Analyzes
The values of the tests were determined to
be roughly 140 N of drag force with a drag
coefficient of 0.05. For our design and flight,
the values are deemed acceptable. The flow
around the rocket at the backend is
where the least velocity occurs, which is seen
in the velocity contour. For the pressure Figure 43. Rocket Velocity Contour.
contour, it can be observed that our rocket’s
Figure 41. Drag Force Results. 1 atm is sufficient to manage flight pressures,
with the majority of pressures occurring at
the rocket tips.

Figure 44. Rocket Pressure Contour.

Figure 42. Coefficient of Drag Results.
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Takım
Logosu Avionics– Summary
Avionic computers are originally designed by us. Table 18 shows the components of each system used in our avionics.
Table 18. Main and Backup Avionics Comparison.
Main Avionics System Backup Avionics System
Purpose Purpose Differences Similarity
Parts and Codes Parts and Codes
Processing and application The processors used are the
ATmega2560 Processor ATmega2560 Processor Processing and application of data. -
of data. same.
Acceleration and axis BMP180 Pressure Pressure, temperature and humidity One is for acceleration and It’s used for the same goal
MPU6050 IMU Sensor
measurement. Sensor measurement. the other is for pressure. of activating separation.
The purposes of the
Pressure, temperature and BME 280 Pressure Pressure, temperature and humidity
BME 280 Pressure Sensor - pressure sensors are the
humidity measurement. Sensor measurement.
same.
LoRaSX 1278 Data transmission to ground DRF7020D27 Telemetry Data transmission distances It's used for the same goal
Data transmission to ground station.
Telemetry Module station. Module are different. of data receiving.
Making a position It's used for the same goal
Grove-GPS (Air530) GY-NEO 8M GPS Making a position measurement. Different sensitivity of dBm.
measurement. of ground recovery.
The Buzzers used are the
5V Buzzer Helping to recovery. 5V Buzzer Helping to recovery. -
same.
GP GP1604AU Alkaline GP GP1604AU Alkaline The batteries used are the
Powering the system. Powering the system. -
Battery Battery same.
The antennas used are the
TX433-JKD-20P Antenna Telemetry communication. TX433-JKD-20P Antenna Telemetry communication. -
same.

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Takım
Logosu
Avionics– Summary
The MPU6050 IMU sensor and BME280 pressure sensor will be used by
the main avionics computer to trigger the servo motors linked to the 9th
and 10th pins of the main avionics' computer, which will execute the
separation procedures. The backup avionics computer's BMP180 and
BME280 pressure sensors will be in charge of activating the servo motors
attached to the backup avionics computer's 9th and 10th pins and
executing the backup separation procedure if the main computer fails.
Because there will be no electrical or cable connection between the two
avionic computers, the backup avionic computer will perform the first and
second separations at a 5-second delay from the main computer, that is, if
there is no deviation in the data of the backup avionics BME280 pressure
sensor and the BMP180 pressure sensor within the specified 5-second
period, it will determine that the main avionic computer has failed to
start the separation. If the backup avionic computer detects a variation in
the sensor data within the 5-second time frame, it will cancel its own
separation process and the servo motor will not execute the separation Figure 45. Avionics Bay 3D View (CAD).
process, allowing the main avionics computers to complete the
separation procedures without issue.
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Takım
Logosu Avionics – 1.System Detail/1
Table 19.1. Recovery Roles of Main Avionics Components.
Component Product Name / Code / Type Is Data Used in Recovery Algorithm? The Function of the Data Used in the Recovery Algorithm

Processor ATmega2560 Processor (It will be left blank for the processor) -

According to the acceleration data for the Y axis, the

acceleration value after the previous acceleration value
IMU Sensor MPU6050 IMU Sensor Yes will be subtracted, and the minimum acceleration in the Y
axis will be determined and the necessary condition for
the first separation will be met.

In the incoming data, the pressure value after the previous

pressure value will be subtracted and the separation will
be performed according to the sign of the result. For the
Pressure Sensor BME280 Pressure Sensor Yes
second separation, separation will be carried out
according to the pressure value at 500 meters altitude,
which was calculated beforehand.

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Logosu Avionics – 1.System Detail/1
Table 19.2. Recovery Roles of Main Avionics Components.
Component Product Name / Code / Type Is Data Used in Recovery Algorithm? The Function of the Data Used in the Recovery Algorithm

Communication Module LoRa SX 1278 Telemetry Module No -

GPS Module Grove - GPS (Air530) GPS Module No -

Buzzer 5V Buzzer No -

Battery GP GP1604AU Alkaline Battery No -

TX433-JKD-20P
Antenna No -
433 MHz Antenna

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Logosu Avionics – 1.System Detail/2nd
GP GP1604AU Switch
Alkaline
Battery MPU6050
Buzzer
VCC SPI
DIG
Motor 1 DIG

5V

Motor 2 DIG

Arduino Mega
Ground
Pro Mini

LoRa SX UART
1278
SPI UART
3.3V

TX433-JKD-20P
Antenna
Grove - GPS
BME280
(Air530)

Figure 45. Main Avionics Block Diagram and Schematic.

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Takım
Logosu Avionics – 1.System Detail/2nd
We started with the main avionics system's first schematic
design. Due to various defects in the PCB when produced,
the PCB designs were drawn and soldered on the perforated
plate instead. Main avionic board with 1 battery input, 2
servo inputs, Arduino Mega Pro Mini with Atmega2560 CPU,
MPU6050 IMU sensor, BME80 pressure sensor, LoRa SX1278
telemetry module, Grove GPS (Air530), and Buzzer are
all soldered in a specific order on a perforated plate. Later,
the perforated plate's short-circuited section was utilized as
a power distribution block, and power connections were
built using soldering to ensure that the data link between
the Arduino Mega Pro Mini and the sensors was maintained.
PCB cutting will later be made to replace the perforated
plate. Additional connectors for servo motors and the GP
GP1604AU Alkaline Battery are added, which is only used in
the main avionics as each computer will have its own
battery. Finally, the main avionics system is up and running.

Figure 46. Main Avionics Photo. Figure 47. Main Avionics PCB Design.
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Logosu Avionics – 1.System Detail/3
Launch
BME280 and
MPU6050 apogee
No Backup Avionics When the rocket reaches the apogee point, the BME280 pressure sensor will
Rocket commissioning
measurement compare the next data to the previous one and determine whether the pressure has
Use Kalman Filter for BME280
and MPU6050 data
decreased. When the lowest point on the Y-axis acceleration is reached, the MPU6050
Comparison of
IMU sensor will recognize that it has reached its peak. Once both conditions are met the
No
Apogee previous and next
data values
first parachute will be opened. Otherwise, separation will be done according to the
apogee departure time that has been pre-calculated. The BME280 pressure sensor will
First Backup Leave with
Parachute
No
Avionics
No
Apogee calculate an altitude value based on the pressure at a predefined distance of roughly
opening estimated time
commissioning
500 meters for the rocket's second parachute, once that calculated value is defined the
BME280 500 meters
pressure calculation
rocket to separation will activate. When the rocket lands and the recovery procedure
starts, the Grove GPS (Air530) will broadcast position data to the LoRa SX1278 telemetry
Use Kalman Filter
for BME280
module to allow us to locate it The buzzer will be used to assist during the recovery
process. All data that will trigger the separation will be ran through Kalman Filter.
Second parachute No Backup Avionics No Departure with
estimated time
Table 20. Separation Activation Parameters List (Main).
opening commissioning
of 500 meters Parameters to Trigger the System Reason of Choosing Sensors from Which Data is Received
Rescue with GPS, No Backup Avionics No Recovering Pressure can accurately reflect the altitude of the
Telemetry, Buzzer commissioning based on the Pressure BME280 Pressure Sensor
latest data
rocket as they are proportional.
Y-axis Acceleration Y-axis acceleration is zero at the apogee. MPU6050 IMU Sensor
Rocket
Rescue To be used as a last resort in the event of a
Calculated Time From Simulation Arduino Mega Pro Mini Function
Figure 48. Main Avionics Algorithm. possible inability to leave.

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Logosu Avionics – 1.System Detail/3
Data filtering is a mathematical algorithm for predicting the next data by modeling data when the data read is uncertain. The
main avionics uses the Kalman Filter. The Kalman Filter, by including certain noises, provides more precise data after
mathematical operations are done. The data from the BME280 sensor and the MPU6050 sensor is processed using the Kalman
Filter. The BME280 sensor measures the data in real-time and provides the system with real-time pressure data. The data is put
through the Kalman filter and precise data is generated and used instead because the incoming data is fluctuating, and not
exactly near to reality. The MPU6050 sensor returns data values ​into the system by calculating instantaneous acceleration
changes. Since the data constantly takes different values ​under different conditions, sharper values ​are obtained and used
bypassing the data from the sensor through the Kalman filter as well.

Kalman Filter Formulization

Formula : x̄K = KK.ZK + (1-KK).x̄K-1 (3)[4].
The formula (3) contains the estimated value of the X value, x̄K. The ZK value
is the measured value and does not give the correct output before filtering.
KK is the Kalman gain value multiplied by the measured value. x̄K-1 is the
estimated value of X in its previous state and is multiplied by (1-KK).
After the actual values of the main avionics' computer sensors are found
with the Kalman filter formula, their data is used for separation.
Figure 49. Kalman Filtered Output Chart Example [5].
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Takım
Logosu Avionics – 2.System Detail/1
Table 21.1. Recovery Roles of Backup Avionics Components.
Component Product Name / Code / Type Is Data Used in Recovery Algorithm? The Function of the Data Used in the Recovery Algorithm

(It will be left blank for the processor)

Processor ATmega2560 Processor

Signal status will be determined by subtracting the

previous data from the next data in the calculated
pressure values, and the first separation will take place
Pressure Sensor BMP 180 Pressure Sensor Yes
when it is sense that the apogee point has been reached.
The second separation will take place using a
predetermined 500 meters altitude pressure.
Received data will be calculated from the previous
pressure value difference and separated according to the
Pressure Sensor BME280 Pressure Sensor Yes sign of the result. In the second separation, it will be
separated according to the pressure value at 500 meters
previously calculated.

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Logosu Avionics – 2.System Detail/1
Table 21.2. Recovery Roles of Backup Avionics Components.
Component Product Name / Code / Type Is Data Used in Recovery Algorithm? The Function of the Data Used in the Recovery Algorithm

Communication Module DRF7020D27 Telemetry Module No -

GPS Module GY-NEO 8M GPS Module No -

Buzzer 5V Buzzer No -

Battery GP GP1604AU Alkaline Battery No -

TX433-JKD-20P
Antenna No -
433 MHz Antenna

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Logosu Avionics – 2.System Detail/2
GP GP1604AU Switch
Alkaline
Battery BMP180
Buzzer
VCC SPI
DIG
Motor 1 DIG

5V

Motor 2 DIG

Arduino Mega
Ground
Pro Mini

DRF7020D27 UART

SPI UART
3.3V

TX433-JKD-20P
Antenna
GY-NEO
BME280
8M GPS

Figure 50. Backup Avionics Block Diagram and Schematic.

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Takım
Logosu Avionics – 2.System Detail/2
We started with the backup avionics system's first
schematic sketch. The soldering of the cable
connections between the sensors was then
completed on the perforated plate. A perforated
plate has been soldered with a backup avionics
board, 1 battery input, 2 servo inputs, Ardunio Mega
Pro Mini with Atmega2560 CPU, BME280 pressure
sensor, BMP180 pressure sensor, DRF7020D27
telemetry sensor, GY-NEO 8M GPS, and Buzzer. The
sensors were powered by the short-circuited
portion, which also served as a power distribution
system. The Arduino Mega Pro Mini was then
soldered for features such as a signal exchange.
Additional connectors for servo motors have been
added, as well as a GP GP1604AU Alkaline Battery
for the backup computer. As a result, the backup
avionics system is ready for operation.

Figure 51. Backup Avionics Photo. Figure 52. Backup Computer PCB.
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Logosu Avionics – 2.System Detail/3
Launch
BME280 and Use Kalman Filter By subtracting the data from the prior data, the BME280 and BMP180 sensors will
BMP180 apogee for BME280 and
Rocket measurement BMP180 data identify if the pressure is dropping once the rocket reaches the apogee point. The
Desired altitude No Comparison of
previous and next
backup computer will start 5 seconds after the main computer fails to produce
not reached
Apogee
data values separation at the apogee point, hence starting the separation. Otherwise, separation will
Main
avionics first
No
Activation
of backup
BME280,
BMP180 data
No be done according to the apogee departure time that has been pre-calculated. The
seperation avionics calculation BME280 and BMP180 sensors will allow the rocket to open according to the pressure at
Launching the
First seperation
done rocket in the pre- a predefined distance of around 500 meters if the main computer is unable to complete
calculated time
the second parachute opening. Finally, If the main avionics fail to deliver data for
Main avionics Activation BME280,
second opening
No
of backup BMP180 data recovery after the rocket has landed, the DRF7020D27 telemetry module will receive
with BME280 avionics calculation
location data from the GY-NEO 8M GPS and the recovery procedure will start. During the
Launching the Use Kalman
Second seperation rocket in the No Filter for recovery phase, the buzzer will be used to help. All data that will activate separation will
done pre-calculated BME280,
time BMP180 be ran through Kalman Filter. Table 22. Separation Activation Parameters List (Backup).
Main avionic Activation Rescue with Parameters to Trigger the System Reason of Choosing Sensors from Which Data is Received
No
rocket recovery of backup GPS, Telemetry,
avionics Buzzer Pressure can reflect the altitude of the rocket as
No Pressure BME280, BMP180 Pressure Sensor
they are proportional.
Recovering
Rocket Using a second pressure sensor gives our data
Rescue
based on the Pressure BME280, BMP180 Pressure Sensor
latest data more reliability

Figure 48. Backup Avionics Algorithm. Calculated Time From Simulation

To be used as a last resort in the event of a
Arduino Mega Pro Mini Function
possible inability to leave.

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Takım
Logosu Avionics – 2.System Detail/3
Data filtering is a mathematical algorithm for predicting the next data by modeling data when the data is uncertain. The Kalman
Filter basically includes certain noises, allowing us to obtain sharper and more precise data after mathematical operations. The
spare avionics computer uses the Kalman Filter. Kalman Filtration is used in the BME280 pressure sensor and the BMP180
pressure sensor. BME280 pressure sensor and BMP180 pressure sensor work in similar logic as filtering. In pressure sensors, the
data is measured instantly and gives instant pressure data to the system. Since the pressure data obtained varies and can be far
from realistic, the data is passed through the Kalman Filter and precise results are obtained.

Kalman Filter Formulization

Formula: x̄K = KK.ZK + (1-KK).x̄K-1 [4] (3).
Formula (3) contains the predictive value of X value, x̄K. The ZK value is the
measured value and does not give the correct value before filtering. KK is the
Kalman gain value multiplied by the measured value. x̄K-1 is the estimated value
of X in its previous state and is multiplied by (1-KK). After calculating the actual
values of the redundant avionics' computer sensors with the Kalman filter
formula, their data is used for separation.
Figure 54. Kalman Filtered Output Charts Example [6].
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Takım
Logosu Avionics – Communication
In the ground station, there are three Arduino Nanos. There Link Budget Calculation [7]
is no link between the processors, which ensures that the P P + G - L - L - L + G - L
RX = TX TX TX FS M RX RX
data does not get jumbled up. The main computer sends PRX (dBm) = Received Power
pressure, acceleration, and location data to the LoRa PTX (dBm) = Transmitter Power Output
SX1278s’ ground station, while the backup computer sends GTX (dBm) = Transmitter Antenna Gain
L (dBi) = Loses from Transmitter (Cable)
pressure and position data to the DRF7020D27 ground LTXFS (dB) = Free-Space Loss
Figure 55. Ground station. station. The data for the referee ground station will be sent LM (dB) = Polarization Losses
by connecting the RGS device to the computer with data GRX (dBi) = Receiver Antenna Gain
from the avionics. As a result of the telemetry band LLRX =(dB) = Loses from Receiver (Cable)
FS 32.48*log(Frequency(Mhz) + 20 log(Distance(km))
calculations [12], the main avionics will use the LoRa LM (dB) = 6 dBm (default accepted)
SX1278 module with an 8-kilometer range running in 433 Main Avionic Link Budget:
MHz bands, while the backup avionics will use the Free-Space Loss=32.48*log(433)+20log(10) = 103.6
PRX (dBm) = 20 + 4 - 1 - 103,6 - 6 + 4 – 1 = -83.6 dBm
Figure 56. Telemetry DRF7020D27 module with a 5-kilometer range working in (Since the LoRa SX1278 used can go up to -138 dBm,
Interface. 433 MHz bands. Antennas TX433-JKD-20P are used. the distance can be increased.)
Backup Avionic Link Budget:
Telemetry Package Structure Free-Space Loss=32.48*log(433)+20log(5) = 99.6
<PACKAGE NUMBER>;< TEAM ID >;<ALTITUDE>;<GPS ALTITUDE>;<GPS LATITUDE>;<GPS LONGITUDE>;
PRX (dBm) = 27 + 4 - 1 – 99,6 - 6 + 4 – 1 = -72.6 dBm
<MAIN AVIONIC PRESSURE>;<MAIN AVIONIC Y-AXIS ACCELERATION>;<BACKUP AVIONIC PRESSURE>
(DRF7020DRF can go up to -117 dBm, the distance can
(ANNEX-8 RGS has been taken into account in the package structure, the requested data will be forwarded to
be increased.)
RGS.) The data packet is the final packet consisting of a combination of avionics.
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Takım
Logosu Avionics Prototype Test
Table 23.1. Avionics Prototype Test.
Test Name Test Location Test Method Test Rigs Data from the Test Interpretation of Test Data
The coding and components of the
main avionics and spare avionics The success of the BME280, BMP180
computer components will be installed The data of the sensors at minimum and pressure sensors in the separation
on the perforated plate, and the Avionic computer components, 500 meters pressure, the data of the processes and the first separation success
Altinbas University
Avionic Algorithm Test pressure will be reduced by vacuuming Airtight container, Vacuum IMU sensor on the Y-axis and the buzzer with the Y-axis acceleration of the
Mahmutbey Campus
in the airtight container, and then air machine, Buzzer. data. MPU6050 IMU sensor will be observed by
will be slowly reintroduced. The the operation of the 5V Buzzer if the
assembly will also slowly move outputs are correct.
upwards with 0 horizontally at its apex.
The test setup to be used in the Avionic By observing the data outputs in the
Algorithm test will also be sent to the Avionic computer components, Data outputs of the data in the Avionic Algorithm Test on the computer
Altinbas University
Card Functionality Test ground station by telemetry and the Airtight container, Vacuum application in the Avionic Algorithm Test screen, it will be observed how fast the
Mahmutbey Campus
data outputs of the components will be machine, Buzzer, Laptop on the computer screen. incoming data comes and how well the
displayed on the computer screen. components work.
2 LoRa SX1278 and 2
Telemetry of the main avionics and LoRa SX1278 maximum distance and It will be observed how far the telemetry
DRF7020F27 telemetry
Communication Distance backup avionics computers will be maximum speed data, DRF7020D27 modules can receive maximum data in the
Open area modules (two each for avionic
and Speed ​Test placed at a distance of kilometers from maximum distance and maximum speed open area and how fast they receive the
computers and ground
the ground station. data. data.
station), Laptop
Parachute components are brought to With the command given to the avionics
a certain distance, the pins to which computers, it will be observed whether the
Avionics computer
Activation of Seperation Altinbas University the servo motor is connected will be servo motor is successful in opening the
components, parachute, servo Servo motor 1 and 0 data.
System Test Mahmutbey Campus activated at the time of fall, and the parachute, how many degrees of angle and
motor
process of opening a parachute with rotation time the servo motor will be
the servo motor will be performed. successful.

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Takım
Logosu Avionics Prototype Test
Table 23.2. Avionics Prototype Test.
Test Name Test Location Test Method Test Rigs Data from the Test Interpretation of Test Data
Tests to be Performed After the Critical Design Report
It will be observed how healthy the data
The data sent to the ground station will displayed on the serial screen at the
Ground Station Interface Altinbas University 2 Arduino Nano, LoRa SX1278,
be sent to the application prepared by In-app data made for telemetry. ground station appear in the application
Test Mahmutbey Campus. DRF7020D27, Laptop
the EVA X Team. made by the EVA X team, and how
accurate and fast the application works.
Batteries to be used separately in
avionic computers will remain
2 GP GP1604AU Alkaline Data on battery operation on the serial It will be observed how long the batteries
Altinbas University connected to the avionic computers
Battery Duration Test Batteries, main avionics, screen of the main avionics and backup connected to the avionic computers work
Mahmutbey Campus. and in working condition and will
backup avionics avionics computers. differently.
output to the serial screen as long as it
remains on.
2 GP GP1604AU Alkaline With the value read from the
The temperature of avionic computers
Altinbas University Batteries, main avionics thermometer, it will be observed how hot
Avionic Temperature Test connected with batteries with different Thermometer data
Mahmutbey Campus. computer, backup avionics the avionic computers are and what
wiring will be measured.
computer, thermometer precautions should be taken.

Table 24. Avionics Prototype Test Schedule. In the shared test calendar, green boxes indicate
the tests completed during the CDR phase, and
the red-colored boxes indicate the tests to be
performed after the CDR.
Avonics Prototype Video Test: [Avionics Prototype
Test YouTube link will be placed here]
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Team
Logo Budget
Table 25. Total Budget Approximation.
Feature Material Amount Price
Feature Material Amount Price
E-Glass Fiber/Epoxy and
222 TL Nose Cone 1 600 TL
Lora module SX 1278 - 2 Aluminum
Primary Frame E-Glass Fiber/Epoxy 1 3500 TL
ATmega2560 - 2 333 TL
Body Main Frame E-Glass Fiber/Epoxy 1 3500 TL
MPU6050 IMU Sensor - 1 43 TL
Fins E-Glass Fiber 3 1000 TL
BMP180 Barometer - 1 57 TL
Coupler E-Glass Fiber/Epoxy 1 900 TL
DRF7020D27 Telemetry
- 2 683 TL
Avonic System
Module Boat-Tail and Retainer Aluminum 1 800 TL
GY-NEO 8M GPS - 1 426 TL (Provided by
M2020 Motor - 1
BME280 Sensor - 2 201 TL teknofest)
Engine
Grove - GPS (Air530) - 1 263 TL System Inner Motor Tube E-Glass Fiber/Epoxy 1 1500 TL

Buzzer - 2 6 TL Engine Block Aluminum 1 200 TL

TX433-JKD-20P 433 MHz - 4 106 TL Lora module SX 1278 - 2 222 TL

GP GP1604AU Alkaline Battery - 2 47 TL ATmega328PU - 1 193 TL

Ripstop TX433-JKD-20P 433 MHz - 2 106 TL
Parachutes 3 1570 TL
Recovery Nylon PAYLOAD GP GP1604AU Alkaline
System - 1 47 TL
CO2/Piston System Aluminum 2 900 TL Battery
BME280 Sensor - 1 201 TL
Total Price - - - Around 2600 TL Grove - GPS (Air530) - 1 263 TL

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Checklist
EVA X Checklist Rockets must release the payload at the
Requirement Recompense apogee point and deploy the drogue
No Requirement PDR Slide Number Explanation 9 3.2.1.4 Slide 5,33.
Item No Status parachute (yellow drag
Mixed teams comprising members from parachute in Figure 1).
1 3.1.6. different education/training institutions Slide 2. Main parachute will be deployed at a
can participate in the competition. 10 3.2.1.5 maximum of 600 m and a minimum 400 m Slide 5.
from the ground.
Teams shall comprise a minimum of six (6)
and a maximum of ten (10) people. A The payload will be recovered separately
2 3.1.9 Slide 2. from the rocket, whereas the rocket parts
maximum of 6 members can be present in
the area. will all be recovered together. There shall be
11 3.2.1.20 Slide 37.
a system (GPS, radio transmitter) pinpointing
Each team must participate in the the locations of both the payload and the
Advisor requirements are
competition with one (1) advisor. The parts in question.
3 3.1.11. Slide 2. attached in the zip file in
requirements related to the team advisor
PDF format. Teams are required to make flight
are given in the relevant article.
simulations in accordance with the “Open
A flight simulation report shall be prepared An ork. file has also been
FSR is attached in the zip Rocket Simulation” menu (Figure 3). Teams
4 3.1.17. and delivered in both the PDR and CDR Slide 9. 12 3.2.1.21. Slide 5. attached in the zip file with
file in PDF format. that have not included the simulation
stages. figure 3 simulation applied.
described in Figure 3 in their Open Rocket file
The teams are responsible for listing all shall not be evaluated.
team members that will participate in the Teams shall not enter their Payload as
5 3.1.22. competition and the team advisor in all the Slide 2. "Unspecified Mass". The payload shall be
reports (PDR, CDR, LRR, PLER) they named "PAYLOAD", and its mass shall be
prepare. entered as 4000 grams (4 kg) minimum as a
The faculty member/academic advisors to 13 3.2.1.23. single piece. The values on the "Launch Slides 3,38.
university teams must be an academician Simulation" screen seen in Figure 3 should be
(research assistant, lecturer) in any faculty entered into the simulation. Teams that fail
6 3.1.24.7. in the field of Engineering and Science, or Slide 2. to carry out the simulation using these values
an academician of any field who has shall be disqualified.
previously participated in rocket
competitions in the country or abroad. The system of parachute must be used for
14 3.2.3.1. Slide 35,36 .
the recovery system.
7 3.1.25. The team must have a team captain. Slide 2 .
The rockets in the Medium- and High- In order to prevent damage to the rocket and
Operation concept shown
Altitude Categories must carry out the its parts, the velocity of the loads carried by
8 3.2.1.3. Slide 3 to 5. in slide 5 with all the 15 3.2.2.2. Slide 36.
operation concept given in Figure 1 as an the main parachute must be 9 m/s maximum
competition rules in mind.
example. and 5 m/s minimum.

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Checklist
The drogue parachute must be able to prevent the rocket Nose cone shoulder must have a diameter of at least one and a half (1.5)
16 3.2.2.3. from tumbling. This parachute must reduce the descent rate Slide 35. times the outer diameter of the body tube. Couplers are expected to have
of the rocket to a rate not be less than 20 m/s. a diameter of at least 0.75 times each of the outer diameter of the body
25 3.2.5.5. Slide 12 .
The Payload must be landed “independently” with its own tubes into which they will be integrated. Failure to comply is grounds for
17 3.2.2.5 parachute, without any connection to the rocket parts (no Slide 33. disqualification. A sample nose cone shoulder is provided in Figure 4 and
equipment such as shock cord connecting to any point). sample coupler is provided in Figure 5.
Each parachute will be distinctly colored and easily The rail buttons must be attached to the structurally reinforced parts of
distinguished by the naked eye from a distance (it is of the body tube. Each rocket must have a minimum of two (2) rail buttons.
18 3.2.2.13. Slide 35.
crucial importance that the parachutes not be white, blue or 26 3.2.5.7. One should be located on the engine area, between the engine centre of Slide 20.
any shades of these colors). gravity and the end of the body tube. The centre of gravity of the rocket
19 3.2.3.1. The payload must have a mass of at least four (4) kilograms. Slide 38. must be between the two rail buttons.
The payload, which is separated from the rocket at the The flight computer and all switches on the payload must be located at
27 3.2.5.10. Slide 17,20 .
apogee in the Medium-Altitude category, must transmit the most 2500 mm ahead of the rocket nozzle (Figure 6).
20 3.2.3.4. pressure, temperature, and humidity data of the Slide 37. The deployment and recovery systems found on the rocket are managed
28 3.2.6.1. Slide 33.
atmosphere to the ground station at a frequency of 5 Hz (5 by the flight control computer.
units of data every second for each data group). The communication computer that ensures the transmission of telemetry
Rockets that will compete in the High School, Medium- 29 3.2.6.2. data to the ground station can operate either standalone or integrated Slide 60.
21 3.2.4.1 Altitude and Challenging Task categories must fly at subsonic Slide 4. with the Flight Control Computer.
(below Mach 1) speeds. In the Medium-Altitude category, the use of at least two (2) flight control
The maximum outer diameters of all parts of the rocket must computers is mandated. At least one (1) of these flight control computers
be of the same value (Stages of different diameters and 30 3.2.6.7. must be an authentic flight-control computer. At least one (1) of the flight Slide 46.
22 3.2.4.3. Slide 4.
diameter changes between stages are not allowed. Boat-Tail control computers used must provide the utility of a communication
use is allowed in line with rail positioning restrictions.) computer.
The minimum rail exit velocities are as follows: 15 m/s in the No electrical or wireless connection is permitted between the flight
High School Category, 25 m/s in the Medium-Altitude 31 3.2.6.9. Slide 47.
23 3.2.4.7. Slide 5. control computers used in the system.
Category, 30 m/s in the High-Altitude Category and 20 m/s in The flight control computers must be completely independent of each
the Challenging Task Category. 32 3.2.6.10. other. Each computer must have its own processor, sensors, power source Slide 46,47.
The internal and external pressure of the rocket must be in and cabling.
balance. To ensure pressure balance, a minimum of three (3) The flight control computers used are connected to the deployment
holes with diameters of 3.0–4.5 mm must be located 33 3.2.6.11. system actuator via electric lines, cables etc. (each line should be Slide 37.
Slide
24 3.2.5.1. between the nose cone and the frontal part of the body independent).
17,20 .
tube, in the body tube part housing the avionics systems,
In the event of the partial or complete failure of one of the flight control
and in the body tube section between the rear part of the
computers and/or one of the systems to which they are connected, the
body tube and the engine. 34 3.2.6.12. Slide 52,58.
others must be able to perform the rocket's recovery functions without
interruption.

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Checklist
The flight control computers must have at least two (2) The link bandwidth must be budgeted by assessing the power of the RF
35 3.2.6.13. sensors, and data from these sensors must be Slide 46. 46 3.2.6.23. Slide 60.
module, and this must be presented in the relevant design reports.
used in the flight control algorithm.
In the design and production of the rocket, it must be ensured that power can
There must be at least one (1) barometric pressure sensor in
36 3.2.6.14. Slide 46. be supplied to the flight control computers from outside the body tube (for
all flight control computers.
47 3.2.6.26. example, there should be an accessible switch on the body tube). The starting Slide 20.
In the event of two (2) barometric pressure sensors being
of systems by using tools with ropes, shunts or screwdrivers etc. will not be
used in the flight control computers, the sensors must be
37 3.2.6.15. Slide 46. permitted.
different from each other (Sensors used in different flight
control computers may be the same as each other). Design and production must be done in such a way that power can be supplied
In the flight control algorithm, the deployment system must 48 3.2.6.28 to the electronic circuits on the Payload from switches on the body tube of the Slide 38.
38 3.2.6.16. Slide 47,49,55. rocket.
not be triggered by data from GPS.
All teams must have a ground station to receive real-time At least two criteria that will trigger split sequences in the flight algorithms
39 3.2.6.20. Slide 60. 49 3.2.6.33. Slide 52,58.
data from their rockets and payloads. must be determined.
To launch the recovery of the rockets, the location data of 50 3.2.6.34. Decision-making parameters must be based on the data read from the sensors. Slide 52,58.
40 3.2.6.21.1 the rocket must have been transmitted to the Ground Station Slide 60.
in real time. The data read from the sensors must not be used directly, and any incorrect
The fact that rocket parts will land far away from the ground reading or sensor error must be taken into account. The measures to be taken
51 3.2.6.35. Slide 53,59.
station should be considered, and the range of the in such situations (such as filtering) must be explained in detail in the relevant
41 3.2.6.22. Slide 60.
transceiver antennae should be chosen taking the flight design reports.
trajectory of the rocket into account.
The link bandwidth must be budgeted by assessing the power The teams are responsible for carrying out and providing the results of all the
42 3.2.6.23. of the RF module, and this must be presented in the relevant Slide 60-. necessary analyses and tests in the Critical Design Report (CDR), demonstrating
52 4.3.1 Slide 42 to 45.
design reports. that their designs are ready to proceed to the final production, integration and
In the design and production of the rocket, it must be testing phases.
ensured that power can be supplied to the flight control
computers from outside the body tube (for example, there The system should be explained with an integration scheme (i.e. assembly
43 3.2.6.26. Slide 20.
should be an accessible switch on the body tube). The details of the systems must be presented with supporting visuals from the CAD
starting of systems by using tools with ropes, shunts or program, answering such questions as “How the stages are connected to each
53 4.3.6 Slide 28.
screwdrivers etc. will not be permitted. other, in the Challenging Task category”, “How the nose cone is connected to
To launch the recovery of the rockets, the location data of the body tube", “How the parachute is connected to the body tube”, “How the
44 3.2.6.21.1 the rocket must have been transmitted to the Ground Station Slide 60. motor is fixed inside the body tube in such a way that it can be removed”).
in real time.
The fact that rocket parts will land far away from the ground Open Rocket files with an “.ork” extension supporting the report must be
54 4.3.12. Slide 3 to 5.
station should be considered, and the range of the submitted with the report.
45 3.2.6.22. Slide 60.
transceiver antennae should be chosen taking the flight All electronic components on the system powered by batteries shall be
trajectory of the rocket into account. 55 4.3.17. Slide 50,56.
specified in the CDR, which should include switching circuit schematics.

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Team FMEA
Logo
Error Types and Effects analysis
A Failure Modes and Effects Analysis (FMEA) is located in a zip file in excel format.

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Team
Logo References
[1] Benson, T. (n.d.). Velocity during recovery. NASA. Retrieved May 5, 2022, from https://www.grc.nasa.gov/www/k-
12/VirtualAero/BottleRocket/airplane/rktvrecv.html#:~:text=Velocity%20During%20Recovery,recovery%20portion%20of%20t
he%20flight.
[2] Engineering ToolBox, (2003). U.S. Standard Atmosphere vs. Altitude. Retrieved February 19, 2022, [online] Available at:
https://www.engineeringtoolbox.com/standard atmosphere d_604.html .
[3] Crowell Sr., G. A. (1996). The Descriptive Geometry of Nose Cone .
[4] ÇAYIROĞLU, İ. (2012). Kalman Filtresi ve Programlama. http://www.ibrahimcayiroglu.com/.
[5] Roi YozevitchRoi Yozevitch 13733 silver badges99 bronze badges, & AntonAnton 4. (1967, August 1). Kalman filter
convergence. Stack Overflow. Retrieved May 5, 2022, from https://stackoverflow.com/questions/59046355/kalman-filter-
convergence .
[6] Kalman filter velocity estimation example. KF Velocity Estimation Example. (n.d.). Retrieved May 5, 2022, from
https://www.cs.cmu.edu/~cga/dynopt/kalman/kalman.html
[7] Pozar, D. M. (2012). Microwave engineering. Joh Wiley & Sons, Inc.
[8] T P, Sathishkumar & Satheeshkumar, S & Jesuarockiam, Naveen. (2014). Glass fiber-reinforced polymer composites - A
review. Journal of Reinforced Plastics and Composites. 33. 1258–1275. 10.1177/0731684414530790.
[9] Pardini, L.C., & Gregori, M.L. (2010). Modeling elastic and thermal properties of 2.5D carbon fiber and carbon/SiC hybrid
matrix composites by homogenization method. Journal of Aerospace Technology and Management, 2, 183-194.

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Team
Logo References
[10] Papastathis, T. & Bakker, Otto Jan & Ratchev, Svetan & Popov, A.. (2012). Design Methodology for Mechatronic Active
Fixtures with Movable Clamps. Procedia CIRP. 3. 323–328. 10.1016/j.procir.2012.07.056.
[11] Alam, Ashraful & Yadama, Vikram & Cofer, William & Englund, Karl. (2012). Analysis and evaluation of a fruit bin for
apples. Journal of Food Science and Technology -Mysore-. 51. 10.1007/s13197-012-0889-3.
[12] Tuset-Peiro, Pere & Angles, Albert & Lopez Vicario, Jose & Vilajosana, Xavier. (2014). On the suitability of the 433 MHz
band for M2M low-power wireless communications: Propagation aspects. European Transactions on Telecommunications. 25.
10.1002/ett.2672.

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