Launch Initiative (Sensor Payload) Jason G Renner Patrick R - - PowerPoint PPT Presentation

email:jgr0007@uah.edu

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

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GAMBLS Members

■ Jason G Renner - Project Manager ■ Patrick R Williamson - Software development ■ Michael A Bizanis – Software development ■ Tin T Tran – Hardware development

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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

• n 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)

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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

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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

• perating system that was on the board was not

fast enough to support the sampling frequency we are aiming for.

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Project Summary

GAMBLS 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.

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System Design Description

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Off State Standby 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
• f 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 951.72

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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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