Preparation of Project Technical Reports for the LASC
Team 61B Project Technical Report to the 2023 LASC
Tuana İNCEİŞÇİ1 and Zeynep Melek ZEYBEK2
Şehit Ümit Çoban Gençlik Merkezi, Ankara, Ümitköy, 06810, Türkiye
Aslı ÖZYURT, Aybüke ÖZMEN, Eda MERT, Mehmet Emin AYDEMİR, Halil
Deniz KUSERLİ, Mustafa Barın BAKIR
Şehit Ümit Çoban Gençlik Merkezi, Ankara, Ümitköy, 06810, Türkiye
Signum’22-B is a 3P Pocketqube model satellite that is 50*50*178mm, created by RedCarbon for
Latin American Space Challenge 2023. Our satellite's main mission is collecting atmospheric data
such as: humidity, temperature, atmospheric pressure, UVA/UVB ray. Signum’22-B is also capable
of recording the journey with its build in camera module through the take off and landing.
I. Nomenclature
m = meter
mm = millimeter
Cm = centimeter
CAD = Computer Aided Design
GCS = Ground Control System
CNC = Computer Numerical Control
1
Team Leader, Youth Center, 06810
2
Co-Team Leader, Youth Center, 06810
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I.Introduction
RedCarbon is a team first formed in 2021 and has been working under Ümitköy Youth Centre since 2022. Our
team aims to build model satellite series such as “Signum” which is named after the word “signal” in Latin. The first
model satellite/element of this series is Signum’22. We added new adjustments and features according to the
experiences we gained through the year and put together Signum’22-B.
II. System Architecture Review
(1)Body
You can see Signum’22-B’s design in the Fig. 1 and 2 analysis. Satellite consists of two body parts body and a
frame. The body’s outer measurements are 47*47*175mm, frame’s outer measurements are 50*50*178mm. The
thickness of the aluminum walls are 3mm.
Fig. 1 Signum’22-B Satellite Fig. 2 Signum’22-B Frame
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A. Structure Subsystem
Signum’22-B features a 3P (50*50*178mm) PocketQube structure. We designed our satellites body with
trianglular and rectangular holes on it for electronics to be unaffected by the frame while collecting atmospheric data.
We prefer to use CNC machine to produce the satellite’s body. The parts of the body will produce separately and the
parts will join with the help of welding. We added an openable door to satellites body and frame which makes it easier
for us to move the avionics inside out and place them without causing any damage. Before take-off, we will securely
seal the openable door to ensure it remains closed throughout the mission. This will protect the electronics inside and
keep them safe during the entire operation.
Fig.3 Body Part Model
A.1 Material Choice
We needed a light, durable, resistant material that is also easily accessible to use on our model satellite. To find
this material, we did a lot of research. You can find some of the materials we considered and the material we decided
to use in the table below
Table 1: Body Material Choice
Options Selected material Motive to prefer
Aluminium 7075 Aluminium 7075 Lightness
Aluminium 2024 Durability
Carbon fiber Accessibility
Epoxy fiber High strength
Fatigue resistance
A.2 Interior Design
The payload contains four sensors which are UVA/UVB, GPS humidity-atmospheric pressure-temperature and
camera module. To record the journey without interference, we positioned the camera facing outward. Additionally,
we strategically placed holes for the antennas to ensure effective communication throughout the mission. Since the
connection points of the sensors provided by our sponsor were not suitable for vertical connections on the pertinax,
we added an additional piece of pertinax perpendicular to the remaining connection points to secure them in the air
Fig.4 Interior Design of Signum’22-B
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(2) Frame
Frame is a 50*50*178 mm structure that protects the satellite’s body. It is designed for maximum efficiency and
lightness while being protective. Sometimes thick aluminum layers can cause sensors to read incorrect data, to prevent
this we placed triangular holes all over the frame. Wall thickness is 3mm.
Fig.5 Different Axes of the Frame
B. Avionics Subsystem
Control Card:
We will be using Deneyap Kart in order to gather the necessary data from the sensors and as our controller unit. It is
developed with the original ESP32-WROVER-E module. It has a rich connection interface such as UART, SPI, I2C,
I2S, Ethernet, SDIO, Capacitive Detector.
The microcontroller is being fed by 3.4 volt 1800 mAh battery, the on/off is provided by a push button.
Camera:
Since one of the missions of the satellite is to record the the recovery of the satellite, we use "Deneyap Kamera"
camera module. Deneyap Kamera has a 2-Megapixel OV2640 sensor and a lens with an infrared filter. It is capable
of shooting video with a resolution of 1600 x 1200 pixels and a transfer rate of 15 fps, and take photos with a resolution
of 1600 x 1200 pixels. The direct connection to the control card provides us ease of use.
GPS Module:
“Deneyap GPS ve GLONASS Konum Belirleyici” GPS module is employed ,along with a buzzer sound module, to
be able to track the satellite during and after the recovery. The module has STM8S003F3 microcontroller and GNSS
locator module with L86-M33 internal antenna.
UVA/UVA Ray Sensor:
"Deneyap Ultraviyole Işık Algılayıcı" gives index information in UV-A and UV-B wavelengths and detects light
intensity in the range of 1-128000 lux with it's LTR-390UV-01 sensor.
Temperature, Humidity and Barometric Pressure Sensor:
"Deneyap Sıcaklık, Nem ve Basınç Ölçer" is a sensor that is capable of measuring humidity, temperature, and
atmospheric pressure. It is also compatible with the i2c protocol, which is supported by the microcontroller. It is able
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to measure temperature with ±0.1 °C, humidity with ±%1.5 RH and pressure with ±0.4kPa sensibility. It has MS5637-
02BA03 barometer and SHT40-AD1B sensor.
Communication Module:
For the communication between GCS (Ground Control System) and the satellite, NRF24L01 is employed. It operates
in the 2.4GHz frequency band, and is an energy-efficient choise. The module will be used with a LNA SMA antenna,
2.4-2.5GHz frequency range.
Micro SD Card Module:
Micro SD Card Module can read and write on micro-SD cards with the SPI protocol. It can work with 3.3V and 5V.
We will be using this module to store the data obtained by the sensors without any loss and to compare it with the data
in the ground control system when we receive the satellite.
C. Software Subsystem
The Software Subsystem in the Signum'22-B satellite plays a crucial role in the mission's success. It is responsible
for acquiring, processing, and transmitting data from various sensors, including UVA/UVB radiation, temperature,
barometric pressure, and humidity. The subsystem ensures seamless telemetry transmission to the Ground Control
System (GCS) using the NRF24L01 module, enabling real-time access to vital data such as UVA/UVB levels, GPS
coordinates, MARG data (Magnetic, Angular Rate, and Gravity), altitude, and barometric pressure. To enhance data
integrity, the Software Subsystem incorporates robust error handling and data storage redundancy, storing important
information on a microSD card in case of communication interruptions. Notably, the Software Subsystem handles
video data from the onboard camera differently, securely storing it on the microSD card rather than transmitting it via
telecommunication. This approach optimizes communication bandwidth and ensures valuable footage can be accessed
and analyzed post-recovery.
Fig.6 Satellite Software State Diagram
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Table 2: The link budget for the satellite a) Since the isn't any cable used there isn't any transmit loss b) the
polarisation loss and the atmospheric loss are estimated as a 3dbi loss for easier calculation
Free Transmit Atmospheric Polarisation Output Antenna Receiver Calculated
Space Loss Loss Loss Loss Power Gain Sens. Receiver
Sens.
100.0542 0 3 3 7 20 -82 -79.0542
D. Recovery Subsystem
The Signum'22B will land by a parachute; which has an overall diameter of 100 cm, consists of 6 slices, with a hole
in the middle that is 10 cm in diameter, or 10% of the total diameter. The ropes are made of 4 mm 10 thread paracord
rope which has a length of 1.5 times of chute diameter that equals to 150 cm. Parachutes have a Cd of 0.8 and weigh
approximate 150 grams. The material of the shock cordon was chosen as Kevlar as it is non-flammable and has high
strength. And the parachute material is undercoated polyester which is waterproof.
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IV. Mission Concept of Operations Overview
Fig.7 Mission Concept of Operations Overview
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Table 3: Mission Concept of Operations Overview
Step Time/ Altitude/ Description
Velocity
Assembly - Installation of all the rocket parts except the engine and
Before Flight
the gunpowder.
Calibration - The adjustment of the communication system, sensorts,
etc.
Arming - The installation of the engine and the gunpowder,
placement of the rocket on the launch rail
Final Checks - Energization of the electronics and the preparation of
the fuse.
Igniting Time: 0 s Going to the designated distance and triggering the fuse.
While Flight
Altitude: 0 m
Velocity: 0 m/s
Launch Rod Time: 0,44 s The complete rise of the rocket from the launch rail with
Clearance Altitude: 6 m the motor reaching a specific thrust.
Velocity: 30 m/s
Motor Burnout Time: 2,2 s Complete burning of the fuel and the thrust cuts off.
Altitude: 164,7 m
Velocity: 147,5 m/s
Apogee Time:15,5 s Travelling of the rocket with the total thrust and the
Altitude: 1090 m reaching of the apogee.
Velocity: 0,9 m/s
Deployment Time: 15,5 s The triggering of the gunpowder explosion and the
Altitude: 1090 m ejection of the satellite and the parachutes.
Velocity: 0,9 m/s
After the Main - The rocket and the nose cone are gliding in the sky with
Parachute the parachute.
Deployment
After the Ejection - The payload is gliding in the sky with the parachute.
of Satellite
Rocket Ground Hit Time: 136,8 s The landing of the sufficiently slowed down rocket.
Altitude: 0 m
Velocity: -8,24 m/s
Satellite Ground Hit Time: 158.9 s The landing of the sufficiently slowed down satellite.
Altitude: 0
Velocity: -6,9 m/s
Rescue - The detection of the touchdown point and the recovery
Flight
After
of the parts of the rocket.
V. Conclusion and Lessons Learned
Great teamwork, effective communication, and learning the value of time management and task distribution were
key experiences for our group.We are excited to continue our successful journey of being productive and actively
engaged in the aviation industry.
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Appendixes
A. Project Test Reports
Planned Tests
Control Card Tests: The control card of the satellite, Deneyap Kart, is going to be subjected to tests that assessed
its functionality with basic systems, such as servo motors, LEDs, and LDRs
Mechanical tests: We are going to attach the satellite to a rope that will represent the parachute and we will apply
a shake test to the satellite to see if the cover opens up and the assembly is enough.
Parachute durability tests: We are going to release the parachutes from the desired altitude with the proper weights.
Electrical Power System (EPS) Tests: To determine the battery life, we will fully charge the battery, and the circuit
will leave running to monitor its performance.
Sensor Tests: To evaluate the performance of the humidity and temperature sensor, the environmental conditions
will be varied separately to observe changes in the sensor output. For the pressure and altitude sensor, the circuit will
be placed in a vacuum container, and the output of the sensor will be analyzed as the pressure decreases. It is expected
that the output values will be proportional to the variables under observation.
GPS Tracking System Tests: The satellite will be relocated to a distance of three kilometers from its current
location, and its position will be tracked in real-time using the ground control system.
Communication Tests: The functionality of the data transmission system will be assessed by relocating the satellite
to a distance of three kilometers from its current location and testing for possible signal interruption.
B. Hazard Analysis
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Table 4: Hazard Analysis
Hazard Hazardous Failure Cause of the Effect of the Precautions Risk
No material description Hazard Hazard Severity
1. Recovery The rescue Algorithm The payload crushes Using the 8/10
system system not failure to the ground backup flight
working computer and
calibrating the
sensors
2. Parachute Parachute The parachute Due to the parachute Using a 5/10
ripping apart getting damaged being torn, it is backup
while being unable to carry the parachute and
stored payload choosing a
durable
parachute
3. Parachute The The parachute The Choosing a 10/10
parachute cord not being parachute durable and
cord able to support opening flexible
snapping the weight of the asymmetrically material when
rocket. selecting the
parachute cord
4. Ground station The inability System failures The ground station Communicatio 7/10
system to that may occur cannot receive the n is checked
communication process/read in the ground incoming data, so again before
stages the compute the data cannot be rocket
information processed avionics are
received by installe
the ground
station
5. Screws Screws being Failure to Inability to make the Inability to 4/10
loosening up complete satellite can’t make the
assemblies separate from rocket satellite can’t
and not to start the separate from
operation rocket and not
to start the
operation
7. Electronics Cables Satellite jolting Cables get damaged Satelitte will 6/10
getting during the or broken be subjected to
damaged takeoff and shake tests and
flight cables will be
secured
8. Data corruption This occurs Data corruption Data corruption can Using unique 6/10
when data can be caused by lead to the loss or radio
stored on the various factors, distortion of frequencies,
satellite's such as software essential checking the
memory or bugs, hardware information and code and make
communicati malfunctions, inaccurate data sure it works
on systems electromagnetic being transmitted. fine
becomes interference
unreadable
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C. Risk Assessment
Table 5: Risk Assesment
Failure Mode Failure Mishap Critically Team’s Comments
Probability Severity Ranking
Parachutes 3 7 6 Parachutes are crucial for our satellite's safe landing.
getting damaged If they get damaged, it could affect the recovery
process. We'll make sure to check and maintain them
properly to avoid any issues. Safety is a priority, so
we'll take necessary precautions and keep the
parachutes in good condition for a successful mission.
Ground station 1 4 4 We acknowledge the risk of frequency corruption in
system our communication system. To address this, we have
communication implemented error-checking and validation
procedures to maintain reliable communication
Recovery 2 7 6 If the recovery system doesn't work, the satellite may
system not fall to the ground quickly. This could lead to other
working dangers besides the satellite breaking apart. To keep
things safe and reduce risks, it's vital to test the
recovery system thoroughly.
Screws/nuts 2 2 3 To prevent damage to the electronics, it is essential to
moving during ensure proper clamping and fixing processes for
or before the certain parts of the satellite that have holes
flight.
Data Losses 2 2 4 A small amount of data loss is not highly dangerous.
Cables getting 4 5 4 Some data loss can can happen, the tests and controls
damaged must be done.
Damaging of the 1 2 4 To avoid losing data, we've securely placed the SD
SD Card Card Module in a safe location. This way, we can
ensure that important information is protected during
the satellite's mission
Battery Defects 2 2 2 Our mission relies on power, and without it, we can't
proceed. Before the operation, we thoroughly check
the power systems to ensure they are working
correctly. Additionally, we always have an extra
power reserve as a backup to safeguard against any
power-related issues during the mission
Wiring Error 1 3 3 We must exercise caution during the procedure to
prevent wiring errors that could lead to a fire. Such
incidents could render the operation impossible.
Prioritizing safety measures and double-checking the
wiring will help ensure a smooth and successful
mission
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D. Assembly, Preflight, Launch and Recovery Checklists
Assembly Checklist
▫ Ensure all required sensors are available and up-to-date
▫ Verify software compatibility with hardware and sensors
▫ Check the batteries to make sure they are fully charged
▫ Connect antennas to communication modules
▫ Check the screws are tight
▫ Screw all the hinge’s together
Preflight Checklist
▫ Check GPS data is being received to the ground control system
▫ Check telemetry is being received to the ground control system
▫ calibrate altitude
▫ Check UVA/UVB data and save the data
▫ Verify telemetry transmission to GCS using the NRF24L01 module
▫ Test error handling and data storage redundancy on the microSD card
▫ Connect batteries to the system
Launch Checklist
▫ Verify sensors' data acquisition and GCS telemetry transmission
▫ Test secure video storage on the microSD card
▫ Check the software state of satelitte
▫ Verify telemetry is being received from ground control system
· GPS
· UVA/UVB
· Temperature
· Barometric pressure
· Humidity data
Recovery Checklist
▫ Verify telemetry transmission and data integrity
▫ Collect successful video recording on the microSD card
▫ Analyze post-recovery data for mission assessment
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▫ Remove SD-Card from Arduino UNO
▫ Copy sensor data from SD kart to Computer
▫ Compare the data collected preflight with data collected during the flight
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E. Engineering Drawings
Fig.8 Engineering Drawings
Acknowledgments
The team is grateful to Sehit Ümit Çoban Gençlik Merkezi for their generous and constant support. We owe
much of our growth and project success to them.
We would also like to acknowledge and thank to our supporter from the beginning, Doğuş YİĞİT
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