NASA University Student Launch Initiative (Sensor Payload) · Current Progress We have finished ......
Transcript of NASA University Student Launch Initiative (Sensor Payload) · Current Progress We have finished ......
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NASA University Student
Launch Initiative
(Sensor Payload)Jason G Renner
Patrick R Williamson
Tin T Tran
Michael A Bizanis
Payload Name: G.A.M.B.L.S
CPE496-01 Computer Engineering Design II
Electrical and Computer Engineering The University of Alabama in Huntsville
2CPE495/496 Project Proposal, G.A.M.B.L.S.
GAMBLS Members
■ Jason G Renner - Project Manager■ Patrick R Williamson - Software development■ Michael A Bizanis – Software development■ Tin T Tran – Hardware development
3CPE495/496 Project Proposal, G.A.M.B.L.S.
The Need■ Gather, store, and transmit data about flight
characteristics from an accelerometer,
magnetometer, gyroscope, barometer, and pitot
probe pressure sensors.
■ Data sampling rate shall be 500 Hz
■ Lightweight payload shall fit into a 3.5”x4.5”
space
■ Who is affected and who will benefit?
■ Charger Rocket Works will fly this payload on their
USLI rocket
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Finished Package Sample
■ Current Transmitter/Power
Board
■ GAMBLS payload will be
used by future CRW design
teams
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Marketing Requirements
■ Shall operate under the under the rigors of flight
■ Shall operate effectively for multiple launches
■ Shall be able to idle on the launch pad for up to
■ forty-five minutes and still be able to operate during
flight
■ Shall take data from an accelerometer, gyroscope,
magnetometer, barometer, pitot probe pressure sensors
and have the capability to add more sensors
■ Shall store data on the rocket and transmit data to a
ground station
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Engineering Requirements
The payload must contain the following instruments:
■ 3-axis accelerometer (3 channels)
■ 3-axis gyroscope (3 channels)
■ 3-axis magnetometer (3 channels)
■ One pressure sensor for ambient pressure (up to 15
psia)
■ Develop a way to synchronize data between multiple
copies of this payload in order to compare events
between payloads.
■ Five additional channels of data which may be used for
sensors chosen by the USLI team
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Engineering Requirements cont.The payload must also meet the following requirements:
■ Minimum 500 Hz sampling rate
■ Sensors and five additional channels must have a 12-bit
minimum resolution
■Capable of making 5 voltage measurements (0 - 5 V) at up to
four feet from the payload. These are the five additional
channels.
■Noise tolerant digital or differential analog signaling required
for the five additional channels and any other signals traveling
more than five inches.
■ System shall provide a minimum of 1W power to sensors and
associated support components (e.g. ADCs, bus transceivers)
for remote sensors
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Engineering Requirements cont.
■ Capable of operating under a 50g acceleration loading
■ Capable of operating under vibration experienced during a rocket flight.
■ Have a means of confirming operational state when the rocket is on the
launch pad
■ Have a means of powering on and off via an external switch when the
payload is in the assembled rocket
■ Must be capable of being integrated with the rest of the rocket, powered up,
and operational within 45 minutes
■ Must be ready for re-flight (new batteries installed, data transferred to
ground station, and empty memory) within 45 minutes
■ Capable of operating for up to one hour in the powered up (standby) state
on the rocket pad
■ Capable of fitting inside of a 3.5-inch cylinder with a 4 inch height
■ Weigh under 1 kg
■ Contain an independent power source (i.e. not require power from other
systems in the rocket)
9CPE495/496 Preliminary Design Review Team Acronym
Survey: Market & Competition■ Raspberry Pi and Arduino supply breakout boards
with the needed sensors
■ These boards are too large for the USLI rocket
■ Arduino and Raspberry Pi systems cannot meet the
500 Hz minimum sampling requirements
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Design Strategy■ Previous senior design teams have attempted
this project with partial success
■ Rather than start from scratch, we will build on
the design from last year
■ We will reuse the transmitter board but redesign
the sensor board and pitot probe board
CPE495/496 Project Proposal, G.A.M.B.L.S.
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Survey: Existing Projects
■ The hardware design last year was completed
but had problems with flash memory and
reading the inertial measurement unit
■ Embedded software was begun but never
finished
■ Ground station code is reusable
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Alternative Approaches■ We initially planned to use an Arduino board to
utilize the breakout board sensors, but the board
did not have the amount of storage space
required to hold the sampled data.
■ We next looked at the Raspberry Pi board,
which had the option for a micro SD card,
which solved the storage space problem, but the
operating system that was on the board was not
fast enough to support the sampling frequency
we are aiming for.
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Project SummaryGAMBLS will measure rotation, acceleration, direction,
and atmospheric pressure while ascending through the
atmosphere, beginning at launch and ending at
approximately 5280 feet (1 mile). The payload will
sample sensor data at a minimum of 500 samples per
second and store this data on board. After apogee, the
rocket will begin transmitting all data to a ground station
so that there will be two copies of acquired data, one on
the rocket and one at ground station. GAMBLS will
synchronize data sampling by use of a GPS time stamp,
and transmit data to ground using an RF transmitter.
CPE495/496 Project Proposal, G.A.M.B.L.S.
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System Design Description
CPE495/496 Preliminary Design Review Team Acronym
Off StateStandby
State
Flight
State
Power On Launch
detected
Landing
State
Apogee
detected
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System Design Description
Sensor Board
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System Design Description
RF-Power board
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Current Progress■ We have finished schematics and CAD layout
design for sensor board
■ Currently creating parts order list
■ Labor hours spent:
■During CPE496 35hrs/week
■During CPE495 10hrs/week
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Current Progress - Pitot
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Current Progress - Power/RF
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Current Progress - Sensor
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Current Progress
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Current Progress
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Current Progress
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Response to Feedback■ After project proposal, we had a lot of feedback from our
professor, students, and guests. All feedback was very helpful
■ Feedback from our professor and our mentor revealed we
would not be able to use a Raspberry Pi or Arduino with our
sensors. Therefore we chose to modify last year’s project instead
of starting from scratch
■ Since beginning the modification of last year’s project, we have
been receiving help from the previous design team regarding
problems and accomplishments of the design
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Testing Plan Requirement Number Verification Requirement Success Criteria Verification Method
P1 Pitot Probe Measurement Sample atmospheric pressure at 500
Hz up to 15 psi
Test Launch
P2 Acceleration Measurement Sample rocket acceleration at 500 Hz
up to 50g
Ground Test
P3 Rotation Measurement Sample rocket rotation at 500Hz up
to 2000 dps
Ground Test
P4 Magnetism Measurement Sample magnetism around rocket at
500 Hz up to 12 gauss
Ground Test
P5 Data Stored to Flash Memory Flight data can be recovered through
USB download
Ground Test
P6 Data Transmitted to Ground Flight data is transmitted to ground
after apogee
Test Launch
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Testing Plan ▪ Unit Tests
▪ Verify Embedded System correctly for each sensor
▪ Retrieve data from flash memory
▪ Test wireless communication via subscale rocket launch or alternative scenario
▪ Integration Tests
▪ Test the wireless state controls from Ground Station
▪ Verify packet retrieval at ground station and process data
▪ Acceptance Tests
▪ Dedicated MAE Team decides acceptance testing.
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The Project Timeline ■ January 6-15
■ Design Sensor Board
■ Critical Design Review
■ January 20-29
■ Order parts
■ Begin ARM embedded Code
■ January 30-February 11
■ Solder circuit boards
■ Finish Software
■ February 12-14
■ Payload Test Flight
■ February 15-March 10
■ Correct Software Problems
■ Acceptance Tests
■ March 11-14
■ Flight Readiness Review
■ March 15
■ Final launch
Safety Analysis■ Soldering can create hot surface, fire and smoke which can
damage your eyes and skin.
■ Battery also creates fire risks during flight because of high speeds
and temperature changes fast which can be problems for the
LiPo battery.
■ The battery also requires a precise charging profile to avoid
damage which is accomplished with a LIPO charging circuit.
■ The payload itself poses very little danger as the boards operate
at 3.3 volts.
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Individual Responsibility ■ The team now is split into two sub-teams
■ Hardware development
■ Jason G Renner
■Tin T Tran
■ Software development
■Patrick R Williamson
■Michael A Bizanis
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Cost Estimation■ Type Item Cost ea.
Qty required Total Cost
■ Microcontroller Atmel ATSAM-4S 6.17
2 12.34
■ Accelerometer, 3-axis, ± 100G
STMicroelectronics H3LIS331DL 10.96
2 21.92
■ Accelerometer, 3-axis, ± 12G
STMicroelectronics LIS331HH 5.37
2 10.74
■ Barometric Pressure / Altimeter Measurement
Specialties MS5607-02BA03 5.42
2 10.84
■ Flash Memory IC Spansion S25FL256S 3.44
4 13.76
■ Gyroscope, 3-axis Bosch BMG160 6.25
2 12.50
■ Magnetometer, 3-axis
STMicroelectronics LIS3MDL 1.79
2 3.58
■ ADC, 4-channel Maxim Integrated MAX11060 6.48 2
12.96
■ GPS Module GlobalTop Technology
FGPMMOPA6H 29.95
1 29.95
■ Radio Module Xbee Pro S3B 900HP 39.00
Cost Estimation Continued
■ 30 PSI Pressure Sensor Honeywell NBPDLNN015 12.32 1
12.32
■ 150 PSI Pressure Sensor TruStability NSCDANN100 29.91 1
29.91
■ Passive components (R, C, L, etc.) Various 30.00
1 30.00
■ Wires, Cables, Connectors Various 25.00
1 25.00
■ Solder Paste Zephyrtronics SPE-0012 24.75
1 24.75
■ PCBs, 2-layer, 1 oz copper Various, 2"x3" 30.00
6 180.00
■ Antenna, 900 MHz omnidirectional Abracon APAMS-104 6.00
1 6.00
■ Antenna, 900 MHz, directional Data Alliance AYA-9012 21.99 1
21.99
■ Shielded Cable
0.42 15 6.30
■ Structual Components Hardware
300.0
■ Ground Component FTDI Serial to USB 25.00
1 25
■ TOTAL 951.7231
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Updated CPE 496 Deliverables■ At the end of CPE 496, the team will able to deliverable three
finished GAMBLS packages with working embedded software
and provide a specific schematics, and software for ground
station.
■ The GAMBLS package will be included:
■ 3 x RF/POWER Boards
■ 3 x SENSOR Boards
■ 3 x PITOT PROBE Boards
■ Finished embedded code for the system.
■ Ground station Receiver
Questions?
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