CanSat 2017 PFR: Team 2848 JELLY 1
CanSat 2017 Post Flight Review (PFR)
Team 2848JELLY
CanSat 2017 PFR: Team 2848 JELLY 2
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
CanSat 2017 PFR: Team 2848 JELLY 3
Team Organization
CanSat 2017 PFR: Team 2848 JELLY
System Overview
Brandon Dawson Yisha Ng
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CanSat 2017 PFR: Team 2848 JELLY 5
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.
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System Overview - Mission
Selected Bonus Objectives: No bonus objectives were selected.
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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
CanSat 2017 PFR: Team 2848 JELLY 8
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
System Overview - CanSat Costs
CanSat 2017 PFR: Team 2848 JELLY 9
# Subsystem Component Cost QTY Type
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
System Overview - CanSat Costs
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# Subsystem Component Cost QTY Type
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
CanSat 2017 PFR: Team 2848 JELLY
System Overview - CanSat Costs
# Subsystem Component Cost QTY Type
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 $1,850.00 1 Actual
CanSat 2017 PFR: Team 2848 JELLY
CanSat Budget – Hardware
Total Hardware$ 957.76
Total Other$1,692.00
Total Income$3,850.00
Net Total$2,649.76
CanSat 2017 PFR: Team 2848 JELLY
CanSat 2017 PFR: Team 2848 JELLY 13
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
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System Overview - Physical Layout
Physical model of container utilized in competition
Above: Open view of containerRight: Top view of closed container
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System Overview - Physical Layout
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
CanSat 2017 PFR: Team 2848 JELLY 16
System Overview - Physical Layout
Physical model of glider utilized in competition
Left: Top view of glider with solar panels attachedBelow: Forward view of glider with solar panels
System Overview - Physical Layout
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.
CanSat 2017 PFR: Team 2848 JELLY 17
CanSat 2017 PFR: Team 2848 JELLY 18
System Overview - Physical Layout
Physical layout of container electronics
Left: Container electronics with battery pack, uncoveredRIght: Container electronics with battery pack, covered by plastic casing
CanSat 2017 PFR: Team 2848 JELLY 19
System Overview - Physical Layout
Physical layout of glider electronics
Left: Model of component placement (previous version)RIght: Component placement utilized in competition
CanSat 2017 PFR: Team 2848 JELLY
Concept of Operations and Sequence of Events
Michael Campbell
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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
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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
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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.
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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
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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)
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Flight Data Analysis
Mecah Levy Stephen Flores
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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
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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
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Payload Altitude Data
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Release: ~400mFirst received packet: 343.87mLast received packet: 125.92m343.87
125.87
(metres)
Payload Temperature Data
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Avg: 31.76°CTemperature ( °C )
Payload Speed Data
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Speed (m/s) Avg: 4.338m/s
Payload Minimap
• Sensor fusion: speed and heading
• Derived from Ground Station map
• Scaling
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Payload Power Data
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Voltage (V)
No power to voltage dividerNoise data on pin 14
Payload Pressure Data
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Pressure (hPa)
Container Altitude Data
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Altitude (m)
Launch: 0m
Apogee: 739.43m
Deployment: 408.09m
Loss of sight: 39.07m
[Pressure noise]
Container Temperature
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Container Power Data
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Failure Analysis
Kevin Julius Brendan Scobie
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Overview
Mechanical Failures:• Mass initially over-budget• Container drop test damages
Electrical Failure:• Inconsistent Transmissions
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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.
CanSat 2017 PFR: Team 2848 JELLY
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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.
CanSat 2017 PFR: Team 2848 JELLY
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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.
CanSat 2017 PFR: Team 2848 JELLY
Lessons Learned
Anthony McCourt
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Lessons Learned
CanSat 2017 PFR: Team 2848 JELLY
● 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
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Lessons Learned
CanSat 2017 PFR: Team 2848 JELLY
● 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.
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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
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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
CanSat 2017 PFR: Team 2848 JELLY
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Thank You
CanSat 2017 PFR: Team 2848 JELLY
Thank you!
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