CanSat 2017 Post Flight Review (PFR) - CanSat · PDF fileCanSat 2017 PFR: Team 2848 JELLY 1...

CanSat 2017 PFR: Team 2848 JELLY 1

CanSat 2017 Post Flight Review (PFR)

Team 2848JELLY


Presentation Outline

1. Introduction:..………..……………………………………………………………………...…...1

2. Systems Overview:..………...………………………………………………………………….4

3. Concept of Operations and Sequence of Events:……………………………………….20

4. Flight Data Analysis:.…………….………………...………………………….……………...26

5. Failure Analysis:.………………...…………………………………………………………….38

6. Lessons Learned: …....……………………………………………………………………….43


Team Organization

CanSat 2017 PFR: Team 2848 JELLY

System Overview

Brandon Dawson Yisha Ng

4


System Overview - Mission

Mission Objectives:● Science glider shall be released from re-entry container at an altitude of 400 m.● Glider shall descend in 2 minutes following a circular pattern of no more than 1

km in diameter● Glider shall sample air pressure and temperature● Glider shall be powered by solar power without on-board batteries● Glider shall transmit the following measurements to a ground station at rate of 1

Hz: Air pressure, Temperature, Mission time, Speed (Pitot tube-generated), Direction (Manometer)

● Glider shall send telemetry information that shall indicate time (or times) command was received.

● After landing, transmission shall end and audio beacon shall start automatically.


System Overview - Mission

Selected Bonus Objectives: No bonus objectives were selected.


System Overview - CanSat overview

• Container

– Height: 285 mm

– Diameter: 110 mm

– Weight: 293 g

– Construction Materials: Fiberglass,

steel hinge, eye-bolts, epoxy,

ABS plastic

• Payload

– Height: 95.5 mm

– Width: 61.7 mm

– Weight: 209 g

– Construction Materials: 3D printed ABS plastic, carbon fiber rods, 90 degree torsion springs,

Monokote polyester, hot glue

• Total Integration

– Total Weight: 502 g

– Integration system: Fishing line to tie up CanSat inside container


System Overview - CanSat Costs

# Subsystem Component Cost QTY Type

1 CONT Fiber Glass sheet 2 oz $35.90 1 Actual

2 CONT Fiber Glass sheet 4oz $12.05 1 Actual

3 CONT Epoxy Hardener $15.35 1 Actual

4 CONT Epoxy $31.65 1 Actual

5 CONT Epoxy Pump Set & Mixer $19.15 1 Actual

6 CONT Monofilament 60 lb Fishing line (RSD) $8.88 1 Actual

7 CONT Nichrome Wire Spool (50 ft) (RSD) 4.99 1 Actual

8 CONT 18" low power chute (RSD) $28.00 1 Actual

9 CONT Ball Bearing Swivel $7.35 1 Actual

10 CONT Rustoleum orange paint $8.48 1 Actual

11 CONT Eye bolt and hook assortment $12.10 1 Actual




12 STRCT 3D Printing Filament $22.99 1 Actual

13 STRCT Carbon Fiber Rod $30.00 1 Actual

14 STRCT Ripstop Nylon Fabric Sheet $8.99 1 Actual

15 ELECT DC/DC Step down Converter 5V $5.68 2 Actual

16 ELECT MP7.2-75F PowerFilm Solar Panel $35.90 2 Actual

17 ELECT XBee-PRO 900HP Radio $39.00 4 Actual

18 ELECT DC/DC Step down linear regulator 5V $0.44 5 Actual

19 ELECT DC/DC Step down linear regulator 3.3V $0.56 5 Actual

20 ELECT Antenna $7.63 3 Actual

21 ELECT Adafruit 10-DOF IMU Breakout $17.76 2 Actual

22 ELECT DC/DC Step down switching converter 3.3V $7.60 2 Actual


10


23 STRCT Torsion Springs $15.24 1 Actual

24 ELECT Altitude Sensor MPL3115A2 (I2C) $3.29 1 Actual

25 ELECT Pressure Transducer 4515DO $37.07 1 Actual

26 ELECT Spektrum Pitot Tube w/ Tubing $13.91 1 Actual

27 ELECT 4PCS 10440 TrustFire w/ PCB Protected

$14.00 1 Actual

28 ELECT Piezo Speaker - PC Mount 2.048kHz $1.95 1 Actual

29 ELECT Adafruit Ultimate GPS Module $29.95 1 Actual

30 ELECT Coin Cell Batteries $5.00 1 Actual

31 CONT 18" low power chute (RSD) $28.00 1 Actual

32 ELECT Magnetometer $30 1 Actual

33 STRCT Resin for High-Quality 3D Printing $120 1 Actual




34 TEST Cesaroni I303 Blue Streak $47.85 2 Actual

35 TEST Rocket (RSD) $0.00 1 Re-use

36 TEST Quadcopter (RSD) $0.00 1 Re-use

37 OTHER Competition fee $100.00 1 Actual

38 OTHER Hotel Night $99.00 8 Actual

39 OTHER Car rental $400.00 1 Actual

40 OTHER Gasoline $200.00 1 Actual

41 OTHER Polos $20.00 10 Actual

FUNDING University Funding $2,000.00 1 Actual

FUNDING Lockheed Martin Sponsorship $1,850.00 1 Actual


CanSat Budget – Hardware

Total Hardware$ 957.76

Total Other$1,692.00

Total Income$3,850.00

Net Total$2,649.76



System Overview - Physical Layout

Physical layout of container Hinged container opens with tension from the parachute and the glider wings. Electronics are housed in on the hinge side of the container. Extra space is left in radius and length of the container to ensure fit.

Left: CAD model of hinged containerRight: Dimensions of container in comparison to mission limitations



Physical model of container utilized in competition

Above: Open view of containerRight: Top view of closed container



Physical layout of glider descent mechanismStructure deploys after exiting container via the force of tensioned springs in the wings. Structure is folded inside container until Nichrome hot-wire mechanism melts fishing line connecting glider and container.

Left: side view of glider as it flew in competitionRight: top view Below: front view



Physical model of glider utilized in competition

Left: Top view of glider with solar panels attachedBelow: Forward view of glider with solar panels


During preflight preparations on launch day, the glider tail and connecting carbon fiber rods were removed to make weight after an extra battery pack had to be added to the container. The glider that flew in the payload had the tail removed.




Physical layout of container electronics

Left: Container electronics with battery pack, uncoveredRIght: Container electronics with battery pack, covered by plastic casing



Physical layout of glider electronics

Left: Model of component placement (previous version)RIght: Component placement utilized in competition


Concept of Operations and Sequence of Events

Michael Campbell

20

Planned vs Actual CON-OPS

Planned CON-OPS1. Establishment of communication between CanSat and Ground Station

2. Systems check and rocket mounting

3. Rocket launch (Apogee at 600m)

4. Container release

5. Velocity reduction via parachute descent

6. Glider release at 400 m altitude

7. Glider wings deployment

8. Circular path glide descent

9. Data acquisition (telemetry and images)

10. Landing after 120 seconds of gliding

11. Audio beacon activation

12. Recovery


Planned vs Actual CONOPS

1. Establishment of communication2. Systems check and rocket mounting3. Rocket launch (Apogee at 600m)4. Container release (400m)5. Velocity reduction via parachute descent 6. Glider release at 400 m altitude7. Glider wings deployment8. Circular path glide descent9. Data acquisition

10. Landing after 120 seconds of gliding 11. Audio beacon activation12. Recovery

Actual CONOPS


AchievedPartialUnsuccessful

Release Mechanism

Nichrome Wire Release Mechanism:• Nichrome wire cuts fishing line holding the glider and

container in place.

Automatic release: • The payload must be in descent mode with an

altitude less than 410 meters.• The early deployment allows time for the nichrome

wire to completely cut the fishing line.

Manual release:• Override command to container to activate the

release mechanism.


Planned vs Actual SOE

Planned SOE:• Upon arrival

– Setup ground station, perform connection tests– Make any necessary changes to CanSat

• Pre-launch– Power on CanSat and Container– Confirm wireless connectivity

• Launch– Watch telemetry, override container if necessary

• Recovery– Recover CanSat


Planned vs Actual SOE

Actual SOE:• Upon arrival

– Setup ground station, perform connection tests– Make any necessary changes to CanSat

• Pre-launch– Power on CanSat and Container– Confirm wireless connectivity

• Launch– Watch telemetry

• Recovery– Search for CanSat (unsuccessful)


Flight Data Analysis

Mecah Levy Stephen Flores


Payload separation altitude

• Separation determined by altitude• Nichrome cutting circuit triggers

below 410m• Container ‘Deployed’ state

entered at 408m, thus activating nichrome

• 10m distance from target of 400m is allowed for cut and separation

• First Glider packet received has altitude 343.9m


Release

400m

Glide Duration

• Duration of glide calculated to be 83.62s

• First altitude point received: 343.87m

• Last altitude point received: 125.92m with dt = 53s

• Duration extrapolated linearly to 0m using 400m target

• Average descent speed 5.17m/s


Payload Altitude Data


Release: ~400mFirst received packet: 343.87mLast received packet: 125.92m343.87

125.87

(metres)

Payload Temperature Data


Avg: 31.76°CTemperature ( °C )

Payload Speed Data


Speed (m/s) Avg: 4.338m/s

Payload Minimap

• Sensor fusion: speed and heading

• Derived from Ground Station map

• Scaling


Payload Power Data


Voltage (V)

No power to voltage dividerNoise data on pin 14

Payload Pressure Data


Pressure (hPa)

Container Altitude Data


Altitude (m)

Launch: 0m

Apogee: 739.43m

Deployment: 408.09m

Loss of sight: 39.07m

[Pressure noise]

Container Temperature


Container Power Data


Failure Analysis

Kevin Julius Brendan Scobie


Overview

Mechanical Failures:• Mass initially over-budget• Container drop test damages

Electrical Failure:• Inconsistent Transmissions


40

Mass Over-Budget

Identification of Failure: 531g total mass during preliminary weighing.Root Cause: Unanticipated addition of battery pack caused mass increase of 28g.Corrective Action: Removed tail of glider to compensate for additional weight.Consequences: CanSat mass meets requirements, but lower glider stability during descent. However, glider did achieve stable circular flight without tail wing.


41

Drop-Test Damage

Identification of Failure: Container was damaged twice during drop test. An eye screw was disconnected during the failure of the first drop test. A second, passed, drop test resulted in the tearing of the container body.Root Cause: The first damage was caused by an unsecure eye-screw. The second resulted from fatigue to the container material, caused by extensive stress tests.Corrective Action:The eyescrews were replaced, and both damages were corrected using JB Weld to repair the affected parts.


42

Inconsistent Transmissions

Identification of Failure: Lack of steady power to glider resulting in missing packets of dataRoot Cause: Components of the design system could not be integrated due to design errors that resulted in the removal of a supercapacitor to smooth solar input power. The circuit was reconfigured to bypass the defective parts of the power system.Corrective Action: Plots were used to extrapolate missing data transmission from the glider.


Lessons Learned

Anthony McCourt


44

Lessons Learned


● Glider lessons learned

- Build and have several back-up pieces for glider in case of breaking so that

broken peices can quickly be replaced and the glider repaired.

- Center of mass location must be designed to be “nose-heavy” for stable

circular flight.

- A simple, mechanical wing deployment mechanism made of sturdy

material is most effective for glider deployment.

● Container lessons learned

- Fiberglass material is ideal for strength, shape, and ease of communication

with ground station.

- Epoxy mounts for eye bolts and hinges provide the strongest and lightest

bonds to container

45

Lessons Learned


● Container lessons learned (cont.)

- Electronic cover should enclose the nichrome wire cutting circuit but should

also not take up too much space as to restrict the glider release

- Fishing line for keeping the glider in place and container closed should be

looped directly on nichrome cutting circuit and should be pre-loaded so that

the glider will not slide down below the open end of the container.

46

Lessons Learned

• Electrical power system lessons learned

– Correctly incorporate solar voltage regulator and supercapacitor system to

provide continuous power.

– Avoid needless complication and account for unreported error in

component specifications: test components individually.

Software lessons learned

– Strong unit testing is important for data parsing logic

– Filter data used in calculations to reduce noisy output

– Allow mission parameters to be modifiable during runtime for smoother

testing


47

Lessons Learned

• Payload electrical system lessons learned

– Use through-hole components, avoid SMD’s when possible to allow easier

modification.

– When using PCB design software, double-check errors in auto-routed

traces.

– Ensure that components mounted on a PCB are located close to one

another to allow simpler routing of traces.

– Incorporate a ground pour into PCB designs to reduce electrical noise.

• Communications lessons learned

- Constant movement of the Yagi antenna in the direction of the payload

provides the best communication with the ground station


48

Thank You


Thank you!

CanSat 2017 Post Flight Review (PFR) - CanSat · PDF fileCanSat 2017 PFR: Team 2848 JELLY 1...

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Transcript of CanSat 2017 Post Flight Review (PFR) - CanSat · PDF fileCanSat 2017 PFR: Team 2848 JELLY 1...