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Drexel RockSAT

Drexel RockSAT. Full Mission System Testing Report. Kelly Collett • Christopher Elko • Danielle Jacobson April 24, 2012. FMSTR Presentation Contents. Section 1: Mission Overview Mission Statement Mission Objectives Expected Results System Modifications Functional Block Diagrams.

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Drexel RockSAT

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  1. Drexel RockSAT Full Mission System Testing Report • Kelly Collett • Christopher Elko • Danielle Jacobson • April 24, 2012

  2. FMSTR Presentation Contents • Section 1: Mission Overview • MissionStatement • Mission Objectives • Expected Results • System Modifications • Functional Block Diagrams

  3. FMSTR Presentation Contents • Section 2: Subsystem Test Reports • Subsystems Overview • Structural System (STR) • Piezoelectric Actuator System (PEA) • Electrical Power System (EPS) • Visual Verification System (VVS) • Section 3: Conclusions • Plans for Integration • Lessons Learned

  4. Mission Overview Drexel RockSat Team 2011-2012

  5. Mission Statement • Develop and test a system that will use piezoelectric materials to convert mechanical vibrational energy into electrical energy to trickle charge on-board power systems.

  6. Mission Overview • Demonstrate feasibility of power generation via piezoelectric effect under Terrier-Orion flight conditions • Determine optimal piezoelectric material for energy conversion in this application • Classify relationships between orientation of piezoelectric actuators and output voltage • Data will benefit future RockSAT and CubeSAT missions as a potential source of power • Data will be used for feasibility study

  7. Expected Results • Piezoelectric beam array will harness enough vibrational energy to generate and store voltage sufficient to power satellite systems • Anticipate output of 130 mV per piezo strip, based on preliminary testing. • Success dependent on following factors: • Permittivity of piezoelectric material • Mechanical stress, which is related to the amplitude of vibrations • Frequency of vibrations

  8. Changes Since ISTR • Implemented latching relay for g-switch • Added additional 9V battery to power camera

  9. Mechanical Subsystems Christopher Elko

  10. Integration full payload

  11. Integration PEA & STR • All PEA subsystem components fit successfully on lower flight deck • No interference with VVS components • Electronics fit successfully on upper flight deck

  12. Physical Specs full payload • Overall Height: 4.5 inches • Overall Weight (including electronics): 2.42 lb • CG: X = -0.01, Y = 0.27, Z = 0.10 in. • Canister Sharing with Temple • Method of Integration: standoffs • Min. Required Standoff Clearance: 1.0 inch • Combined Weight: 7.06 lb (based on designs) • Combined CG: pending final designs from Temple • CG to be adjusted with systematic ballast placement

  13. Prepare for Takeoff • Written integration procedure: in progress • Full parts list: compiled • Spare parts: procurement in progress • Action Items • More regular interface with Temple • Final construction of BETA

  14. EPS and Software Danielle Jacobson

  15. Electrical Design LED Array PEA I PEA II PEA III PEA IV Rectifier + Capacitor Rectifier + Capacitor Rectifier + Capacitor Rectifier + Capacitor Camera Internal Memory Arduino Microcontroller Accelerometer I SD Card Memory Accelerometer II 9V Battery Legend 9V Battery Wallops G-Switch New / updated part Power connection Data connection

  16. EPS test summary • All electronics performed favorably • Integration went smoothly • Activation system still in need of latching relay • Mechanical solution introduces a troubling single point of failure • Once activated, closes circuit until reset • Currently on order

  17. Data as collected Conclusion A bit messy…let’s take a closer look…

  18. Data piezoelectric output 5V Reference Input Pendulum beam generates highest voltage followed by diving board orientation; balance beam lowest (low G’s?) Observations

  19. Data accelerometers High-load vibration testing needed to fully characterize correlation between voltage output and acceleration (Wallops) Conclusion

  20. Data correlations Z-Axis Acceleration As acceleration in beam oriented direction increases, generated voltage also increases!!! It works!!! Observations

  21. Battery Power • Before full system test: ~ 9.3 V • Voltage after full system test: ~ 8.1 V • ΔV over 30-minute test: ~ 1.2 V • Estimated operation time until failure: 1.5+ hr

  22. Software • Software is running as planned • Data collection rates are solid • No inconsistencies

  23. VVS Updates Kelly Collett

  24. VVS status update

  25. VVS on a serious note… • Camera wired to 9V Battery • Originally running from Arduino 5 V output • Moved so Arduino can have its own power source

  26. VVS test summary • Camera will not function on auxiliary battery • Works when hooked up to the Li-Ion battery, but not the 9V • Odd, since it worked with the 9V power supply during ISTR testing

  27. VVS troubleshooting • Attempted changing resistors in the voltage regulator circuit • Resistor ratio (R2/R1) = 1.96 • 2.2/1.2, V = 3.7 V (It worked this time!) • 3.5/1.5, V = 4.5 V (It worked for a little while this time) • 7.35 / 3.7, NOTHING • Voltage going into circuit is too high? • 9 V, perhaps drop to 5 V? • Currently coming out of circuit at 4.5 V or higher

  28. Conclusions

  29. Action Items • STR & PEA • Finish any machining for BETA supports, mounts, etc. • Laser-cut BETA decks • Reconstruction – estimated completion date: 4/29/2012 • EPS • Vibe testing at Wallops to determine actual accelerations from test data • Latching relay to be integrated this week; clean up wiring • VVS • Don’t burn the camera…yet • Determine voltage issue • Integration • Communicate with Temple…

  30. Issues and Concerns • Camera • Latching relay • Spotty communication with Temple

  31. Final Thoughts

  32. Acknowledgements • Kyle Dooleyfor assistance with electronics and circuitry troubleshooting • Dan Lofaro for lending us his precision solder kit

  33. Thank you! Questions?

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