Outline Post Flight Review (PFR) Version 1.0 CanSat 2019...Team Logo Here CanSat 2019 PFR: Team...

Team LogoHere

CanSat 2019 PFR: Team #3193 AGH Space Systems 1

CanSat 2019 Post Flight Review (PFR)

OutlineVersion 1.0

#3193AGH Space Systems

Team LogoHere

(If You Want)


Presentation Outline

Section Slide number

Team Organization 3

System Overview 4

Concept of Operation and Sequence of Events 7

Flight Data Analysis 11

Failure Analysis 32

Lessons Learned 36

Team LogoHere

(If You Want)


Team Organization

Team LogoHere


System Overview

Team LogoHere

(If You Want)


Design Description

mm Parachute

Auto-Gyro mechanism

Spin stabilisation mechanism

Camera

EPS

Payload release mechanism

Electronics + Radio

Container

Team LogoHere

(If You Want)


Ground Station Design

Antenna

Xbee Laptop

Team LogoHere


Concept of Operations and Sequence of Events

Team LogoHere

(If You Want)


System Concept of Operations

Operations

1

Launch and start GS operation

Start sending data

2Deploy Cansat from the rocket

3 Deploy parachute

4Release the SP from container,SP unfolds rotors

5 Landing

6

Recovery and Post-processing of data in the GS

Team LogoHere

(If You Want)


System Concept of Operations

CanSat operations Recovery

Turn on the CanSat and calibrate calibrate MPU. Track the probe using GPS.

Test radio communication and place CanSat in rocket payload section.

Container recovery

Deploy container from the rocket and open the parachute.

SP recovery

Make measurements and transmit data packets. Retrieve and extract data from the probe.

Collect data packets with antenna. Analyse the data correctness.

Release SP and unfold rotors. Filter data if needed.

Localize CanSat by GPS coordinates. Create the report for the PFR

Team LogoHere

(If You Want)


Sequence of Events

CanSat preparation

andassembly

Preflight

Mission

Recovery

Analysis

- Initial checklist:- Communication test- CanSat structure has no

mechanical damages- Unfolding and folding rotor blades- Checking if Science Payload

moves freely in container guides- CanSat assembly- Final Check

- Power CanSat on- Integrate CanSat into rocket payload- Confirmation of telemetry data reception

by line judge

- After powering on the CanSat, telemetry is constantly transmitted to the ground station and monitored

- Container deployment from the rocket and parachute release

- Separation mechanism is triggered when altitude drops below 450m

- Separation is followed by activation of auto-gyro mechanism

- Buzzer is turned on upon landing- After landing, telemetry is no longer

transmitted to the ground station and GPS is turned off

- After all launches for 1 hour period, recovery crew can enter the field to search for CanSat parts

- Obtaining permission to recover CanSat parts

- Retrieval of the Container from the pond- Retrieval of the Scientific Payload- Delivery of the telemetry data file to a line

judge for inspection

- Collection of data acquired by the camera

- If communication failed - telemetry recovery via USB connection

- Analysis of obtained data- Mission assessment and preparation of

the presentation

Legend

Worked as planned / Worked but was missing in planned SOE

No information / partially complete

Did not worked as planned

Team LogoHere


Flight Data Analysis

Team LogoHere

(If You Want)


Container separation altitude

Separation altitude: 446 m

Team LogoHere

(If You Want) Payload pressure sensor data plot


Team LogoHere

(If You Want) Payload altitude plot


Team LogoHere

(If You Want) Descent velocity


Team LogoHere

(If You Want) Payload temperature sensor plot


Team LogoHere

(If You Want) Payload GPS plot


Team LogoHere

(If You Want) Payload battery power plot


Team LogoHere

(If You Want) Tilt Sensor plot


Team LogoHere

(If You Want) Auto-gyro blade spin rate plot


Team LogoHere

(If You Want) Bonus Direction


Team LogoHere

(If You Want) Camera Video


Team LogoHere

(If You Want)


Mass Budget• Table(s) providing the following:

– Mass of each component of payload and container– Mass of each structural element– Sources/uncertainties – whether the masses are

estimates, from data sheets, measured values, etc.– Total mass of all components and structural elements– Margin : The amount of mass (in grams) in which the

mass budget meets, exceeds, or falls short of the mass requirement

• Method of correction to meet mass requirement (based on the margin listed above)

• Must clearly distinguish between Container and Payload masses

CanSatPart Mass [g] Determination

Container with parachute 87 Measured

Science Payload 417 MeasuredTotal 504Total allowed mass range 490 - 510

Team LogoHere

(If You Want)


CanSat Budget

Part Description Quantity Price per unit [USD]

Total [USD] Determination

Sensors subsystem

SS411P Hall sensor 2 0.54 1.08 Actual

MPU-9250 Tilt sensor 1 7.82 7.82 Actual

MS5607 Pressure and air temperature sensor 1 2.68 2.68 Actual

SQ9 Camera 1 10.00 10.00 Actual

UBLOX NEO-M8 GPS 1 7.72 7.72 Actual

Camera holder 3D printed 0.02kg 20.54 0.40 Estimated

Voltage divider + CPU’s ADC Payload Power Voltage Sensor 1 0.10 0.10 Estimated

PKM22EPPH2001 Buzzer 1 0.99 0.99 Actual

Recovery subsystem

Rotors and holders Auto-gyro mechanism 8 1.50 12.00 Estimated

Tube Auto-gyro mechanism 0.5m 1.78 0.89 Estimated

Bearings Auto-gyro mechanism 2 3.60 7.20 Actual

Spring SP deployment mechanism 1 3.62 3.62 Actual

Nichrome wire Hotwire 0.1m 0.91 0.09 Estimated

Rip-stop nylon Parachute material 0.5m2 10.40 5.20 Estimated

Other parts Parachute strings, thread etc. - 2.80 2.80 Estimated

Swivel Parachute detangling system 1 0.97 0.97 Actual

Ailerons Stability control system 4 0.65 2.60 Estimated

Team LogoHere

(If You Want)


CanSat Budget

Part Description Quantity Price per unit [USD]

Total [USD] Determination

CDH subsystem

PCB Main on-board computer 3 6.00 18.00 Actual

STM32F103RCT Microcontroller with real-time unit 1 25.91 25.91 Actual

Cypress S25FL512S Flash memory 1 13.23 13.23 Actual

XB9X-DMUS-001 Radio module 1 34.35 34.35 Actual

Other parts Electrical components - 10.00 10.00 Estimated

Electrical Power Subsystem

sg92r servo Servos 1 3.64 3.64 Actual

9V Lithium Battery Power Supply 2 8.99 17.98 Actual

Total USD 189.27

Team LogoHere

(If You Want) Requirements Compliance 1/5


ID Requirement Comments

1 Total mass of the CanSat (science payload and container) shall be 500 grams +/- 10 grams.

2 CanSat shall fit in a cylindrical envelope of 125 mm diameter x 310 mm length. Tolerances are to be included to facilitate container deployment from the rocket fairing.

3 The container shall not have any sharp edges to cause it to get stuck in the rocket payload section which is made of cardboard.

4 The container shall be a fluorescent color; pink, red or orange.

5 The rocket airframe shall not be used to restrain any deployable parts of the CanSat.

6 The rocket airframe shall not be used as part of the CanSat operations

7 The CanSat shall deploy from the rocket payload section and immediately deploy the container parachute. Container got stuck in rocket

8 The descent rate of the CanSat (container and science payload) shall be 20 meters/second +/- 5m/s. Container got stuck in rocket

9 The container shall release the payload at 450 meters +/- 10 meters

10 The science payload shall descend using an auto-gyro descent control system.

11 The descent rate of the science payload after being released from the container shall be 10 to 15 meters/second.

12 All descent control device attachment components shall survive 30 Gs of shock.

13 All electronic components shall be enclosed and shielded from the environment with the exception of sensors.

Team LogoHere




14 All structures shall be built to survive 15 Gs of launch acceleration.

15 All structures shall be built to survive 30 Gs of shock.

16 All electronics shall be hard mounted using proper mounts such as standoffs, screws, or high performance adhesives.

17 All mechanisms shall be capable of maintaining their configuration or states under all forces.

18 Mechanisms shall not use pyrotechnics or chemicals.

19 Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to the outside environment to reduce potential risk of setting vegetation on fire.

20 The science payload shall measure altitude using an air pressure sensor.

21 The science payload shall provide position using GPS.

22 The science payload shall measure its battery voltage.

23 The science payload shall measure outside temperature.

24 The science payload shall measure the spin rate of the auto-gyro blades relative to the science vehicle. Hall sensor did not registered the magnet

25 The science payload shall measure pitch and roll.

26 The probe shall transmit all sensor data in the telemetry

Team LogoHere




27 The Parachute shall be fluorescent Pink or Orange

28 The ground station shall be able to command the science vehicle to calibrate barometric altitude, and roll and pitch angles to zero as the payload sits on the launch pad.

29 The ground station shall generate a csv file of all sensor data as specified in the telemetry section.

30 Telemetry shall include mission time with one second or better resolution. Mission time shall be maintained in the event of a processor reset during the launch and mission.

31 XBEE radios shall be used for telemetry. 2.4 GHz Series radios are allowed. 900 MHz XBEE Pro radios are also allowed.

32 XBEE radios shall have their NETID/PANID set to their team number.

33 XBEE radios shall not use broadcast mode.

34 Cost of the CanSat shall be under $1000. Ground support and analysis tools are not included in the cost.

35 Each team shall develop their own ground station.

36 All telemetry shall be displayed in real time during descent.

37 All telemetry shall be displayed in engineering units (meters, meters/sec, Celsius, etc.)

38 Teams shall plot each telemetry data field in real time during flight.

39 The ground station shall include one laptop computer with a minimum of two hours of battery operation, XBEE radio and a hand-held antenna.

Team LogoHere




40The ground station must be portable so the team can be positioned at the ground station operation site along the flight line. AC power will not be available at the ground station operation site.

41 Both the container and probe shall be labeled with team contact information including email address.

42The flight software shall maintain a count of packets transmitted, which shall increment with each packet transmission throughout the mission. The value shall be maintained through processor resets.

44 No lasers allowed.

45 The probe must include an easily accessible power switch that can be accessed without disassembling the cansat and in the stowed configuration.

46 The probe must include a power indicator such as an LED or sound generating device that can be easily seen without disassembling the cansat and in the stowed state.

47 An audio beacon is required for the probe. It may be powered after landing or operate continuously.

48 The audio beacon must have a minimum sound pressure level of 92 dB, unobstructed.

49 Battery source may be alkaline, Ni-Cad, Ni-MH or Lithium. Lithium polymer batteries are not allowed. Lithium cells must be manufactured with a metal package similar to 18650 cells.

50 An easily accessible battery compartment must be included allowing batteries to be installed or removed in less than a minute and not require a total disassembly of the CanSat.

51 Spring contacts shall not be used for making electrical connections to batteries. Shock forces can cause momentary disconnects.

52 The auto-gyro descent control shall not be motorized. It must passively rotate during descent.

Team LogoHere




53 The GPS receiver must use the NMEA 0183 GGA message format.

54 The CANSAT must operate during the environmental tests laid out in Section 3.5.

55 Payload/Container shall operate for a minimum of two hours when integrated into rocket.

- A video camera shall be integrated into the science payload to record the descent. It shall be stabilised with 10deg accuracy

Camera was integrated into the SP. Stabilization unknown due to SP loss.

Team LogoHere


Failure Analysis

Team LogoHere

(If You Want) Identification of failure


Container stuck in the rocket.

Rocket with Container landed in the pond.

SP was lost in the pond - it sank.

Hall sensor did not work properly.

Team LogoHere

(If You Want) Root causes


Team LogoHere

(If You Want) Corrective actions


Checking if inside of the rocket is plain and has no scratches.

Launch during good weather conditions - either adding and subtracting 0.5m/s to the wind speed would save container and rocket from sinking.

Adding extra anti-drowning protection or recovery crew equipped with fishing rod or any other long item able to catch SP from water reservoir.

Hall sensor should have been checked more carefully before the mission.

Team LogoHere


Lessons Learned

Team LogoHere

(If You Want) What worked, what didn’t


What worked What partially worked / no information What didn’t work

Auto-gyro release mechanism Camera Container deployment from the rocket

Data transmission Buzzer Hall sensor

Scientific Payload release mechanism CanSat proceeding to recovery mode

Almost all sensors

Ground station apps, received

Maintaining auto-gyro descent rate in given range

Team LogoHere

(If You Want) Conclusions


Great majority of assumptions was fulfilled.

Rotor was tested multiple times and its descent rate was confirmed during competition.

Ailerons had no chance to do their job, although during conducted tests worked properly and stabilized camera vision - camera record from competition was not received as SP drowned in the pond.

Ground Station works properly and antenna angle simplifies transmitting data process.

Rocket should have been checked by Mission Operation Officer in search of scratches that could have prevent correct mission conduction.

Outline Post Flight Review (PFR) Version 1.0 CanSat 2019...Team Logo Here CanSat 2019 PFR: Team...

Documents

Transcript of Outline Post Flight Review (PFR) Version 1.0 CanSat 2019...Team Logo Here CanSat 2019 PFR: Team...