2. Section 1: Mission Overview Mission Statement Mission Objectives Section 2: The Payload! User’s Guide Compliance Beta Prototype Testing Section 3: Check-In Readiness Plans for Integration Documentation 2

4. 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. 4

5. 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 5

7. 7 MicrocontrollerG-switch Accelerometer Array Piezo Arrays Camera Flight Decks Standoff Supports Batteries

8. 8 Beta payload with wiring connections ready for vibration testing Beta payload includes modifications to: Camera housing Organization of EPS components on top deck Transistors and relays used to control power for EPS and VVS Cantilever length: 3.0 in.

9. 9 RequirementUG SpecStatus Mass2.42 lb Volume½ can H: 4.3” D: 9.3” Payload CG1”x1”x1”x0.23” y0.21” z0.43” Activation Method1.SYS.2We think so… Structure Mounts Top, bottom bulkheads SharingFully Developed?Integration Successful

10. 10 PEA I Camera Rectifier + Capacitor PEA II Rectifier + Capacitor Accelerometer II Rectifier + Capacitor Rectifier + Capacitor Rectifier + Capacitor PEA III PEA IV 9V Battery G-Switch Wallops Internal Memory Internal Memory 3-AA Batteries SD Card Memory SD Card Memory Accelerometer I Arduino Microcontroller Power connection Data connection Legend Latching Relay 9V Battery Power (G-switch=1)

11. Beta prototype complete and tested VVS functioning Switched to AA batteries, no regulator Modified camera mounting bracket 11

12. 12 Increased length of cantilevers Lowered maximum output Alpha: over 1 V for “diving board” Beta: about 0.55 V

13. 13

14. 14 Primary ObjectivesComplete? Power generation via the piezoelectric effect under Terrier- Orion flight conditions Yes Classify the relationships between the orientation of piezoelectric actuators and output voltage Yes Ensure system activates upon launchYes Data is autonomously recorded to SD cardYes Secondary Objectives Visual data recorded to SD cardYes Data collection systems are self poweredYes Voltage generated purely from launch vehicleYes Accepted for flight with RockSAT-C programYes

16. Ready! Travel arrangements set Payload is assembled and ready to go Integration with Temple Almost Ready! Documentation For Drexel Payload and Canister Check-in Procedure 16

17. 17 Canister Sharing with Temple Method of Integration: standoffs Height: 9.07” Combined Weight: 6.74 lb Combined CG: x-1.32” y2.04” z2.10” NOTE: material properties discrepancies CG to be adjusted with systematic ballast placement Procedure: tighten standoffs

18. 18

19. 19 Temple Drexel

20. ø 20 9.07” overall height 9.30” overall diameter 6.73 lbs. overall weight standoffs means of integration

21. Finish up documentation Mostly drawings Parts accounting Tidying of documents Ballasting, staking, etc. To be completed after integration with Temple Mostly at Wallops 21

22. 22 Check-in procedure partially completed So far so good

24. None right now! :D 24