Drexel Rock SAT Full Mission System Testing Report

Drexel Rock. SAT 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 2

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 3

Mission Overview Drexel Rock. Sat Team 2011 -2012

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. 5

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 Rock. SAT and Cube. SAT missions as a potential source of power • Data will be used for feasibility study 6

Expected Results • Piezoelectric beam array will harness enough vibrational energy to generate and store voltage sufficient to power satellite systems • Anticipate output of 130 m. V 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 7

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

Mechanical Subsystems Christopher Elko

Integration full payload 10

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 11

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 12

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 13

EPS and Software Danielle Jacobson

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

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 16

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

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

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

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

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 21

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

VVS Updates Kelly Collett

VVS status update 24

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

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

VVS troubleshooting • Attempted changing resistors in the voltage regulator circuit • Resistor ratio (R 2/R 1) = 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 27

Conclusions

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… 29

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

Final Thoughts

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

Thank you! Questions?