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

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 email: jgr0007@uah.edu

GAMBLS Members ■ Jason G Renner - Project Manager ■ Patrick R Williamson - Software development ■ Michael A Bizanis – Software development ■ Tin T Tran – Hardware development CPE495/496 Project Proposal, G.A.M.B.L.S. 2

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 CPE495/496 Project Proposal, G.A.M.B.L.S. 3

Finished Package Sample ■ Current Transmitter/Power Board ■ GAMBLS payload will be used by future CRW design teams CPE495/496 Preliminary Design Review Team Acronym 4

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 CPE495/496 Project Proposal, G.A.M.B.L.S. 5

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 CPE495/496 Project Proposal, G.A.M.B.L.S. 6

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 CPE495/496 Project Proposal, G.A.M.B.L.S. 7

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) CPE495/496 Project Proposal, G.A.M.B.L.S. 8

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 CPE495/496 Preliminary Design Review Team Acronym 9

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. 10

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 CPE495/496 Preliminary Design Review Team Acronym 11

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. CPE495/496 Preliminary Design Review Team Acronym 12

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. CPE495/496 Project Proposal, G.A.M.B.L.S. 13

System Design Description Power On Launch Standby Flight Off State detected State State Apogee detected Landing State CPE495/496 Preliminary Design Review Team Acronym 14

System Design Description Sensor Board CPE495/496 Preliminary Design Review Team Acronym 15

System Design Description RF-Power board CPE495/496 Preliminary Design Review Team Acronym 16

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 CPE495/496 Preliminary Design Review Team Acronym 17

Current Progress - Pitot CPE495/496 Preliminary Design Review Team Acronym 18

Current Progress - Power/RF CPE495/496 Preliminary Design Review Team Acronym 19

Current Progress - Sensor CPE495/496 Preliminary Design Review Team Acronym 20

Current Progress CPE495/496 Preliminary Design Review Team Acronym 21

Current Progress CPE495/496 Preliminary Design Review Team Acronym 22

Current Progress CPE495/496 Preliminary Design Review Team Acronym 23

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 CPE495/496 Preliminary Design Review Team Acronym 24

Testing Plan Requirement Number Verification Requirement Success Criteria Verification Method P1 Pitot Probe Measurement Sample atmospheric pressure at 500 Test Launch Hz up to 15 psi P2 Acceleration Measurement Sample rocket acceleration at 500 Hz Ground Test up to 50g P3 Rotation Measurement Sample rocket rotation at 500Hz up Ground Test to 2000 dps P4 Magnetism Measurement Sample magnetism around rocket at Ground Test 500 Hz up to 12 gauss P5 Data Stored to Flash Memory Flight data can be recovered through Ground Test USB download P6 Data Transmitted to Ground Flight data is transmitted to ground Test Launch after apogee CPE495/496 Preliminary Design Review Team Acronym 25

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. CPE495/496 Preliminary Design Review Team Acronym 26

The Project Timeline ■ January 6-15 ■ February 15-March 10 ■ Design Sensor Board ■ Correct Software Problems ■ Critical Design Review ■ Acceptance Tests ■ January 20-29 ■ March 11-14 ■ Order parts ■ Flight Readiness Review ■ Begin ARM embedded Code ■ March 15 ■ January 30-February 11 ■ Final launch ■ Solder circuit boards ■ Finish Software ■ February 12-14 ■ Payload Test Flight CPE495/496 Preliminary Design Review Team Acronym 27