1. { Dynamo Careful Harry Glenda Alvarenga J.J. Busse Emily Eggers Adam Kemp Gabrielle Massone Dalton Smith Corey Wilson

2.  To Investigate High Altitude Power Generation from the motion of Dynamo using a Kinetic Energy Generator (K.E.G.)  Expected to prove Kinetic Energy Generation is a viable source of power in spacecraft Mission Overview

3.  Dimensions changed to fulfill weight requirement (23x23x9cm)  Rebuilt new structure with improved insulation Design Overview

4. Arduino configured with K.E.G

5. Design Overview Canon SD780 Camera HOBO Data Logger

6. Design Overview Heater and Batteries

7. Functional Block Diagram

8. { Following Launch, Nov 6, 2011 Results and Failure Analysis

9.  Operated and logged data successfully for 96.7 minutes (roughly 86 minutes of flight)  Stopped at 26,500 ft (entering troposphere)  Noticeable spike in acceleration the instant before  Power cord likely became dislodged upon parachute deployment in lower atmosphere  Altitude correlates, and power found disconnected upon recovery Analysis: Arduino

10.  Original AttoPilot Voltage Sensor failed before launch  Subsequent transformers, resistors, and circuits routed through Arduino failed to collect data during flight  Lack of appropriate resistors last-minute Analysis: Voltage Sensor

11. Analysis: Accelerometer

12.  Did not operate during Flight due to Sensor Failure  Mission Simulation  Emulated accelerations between 0 - 1 G  Successfully produced voltage! Analysis: K.E.G.

13. Analysis: Voltage Graph

14.  HOBO gathered data throughout flight  External temperature probe found disconnected upon recovery  Likely caused by movement of other dislodged objects  Recorded Internal Temperatures below -28° C  Did not meet RFP requirement (-10° C) Analysis: HOBO

15. HOBO Internal Temp Lowest Temperature

16.  Temperature dropped to -28° C  Heater disconnected from power  Cause: Additional, un-insulated hole added for camera upon camera switch failure  Extreme external temps, beyond tested values  Fix: Seal hole, reinforce heater to battery connections, add insulation  Testing: cold test indicates temperatures above -10° C  However, difficult to emulate -70° C External Analysis: Insulation & Heater

17.  Camera successfully ran for most of flight  Took images periodically and saved on SD card  Retained power through half of troposphere Analysis: Camera

18. Camera Image

19.  8:26:20 (approx.) camera failure  Altitude: about 15,225 ft  Correlated EOSS and photo time stamps  Dislodged upon recovery  Causes of Failure  Impact (disproved by drop/shake testing)  Cold (disproved by cold testing)  Power button hit when dislodged (Most Probable, and Repeatable)  Fix: Secure Better Within Box, Insulate Analysis: Camera

20.  Components dislodged  Batteries disconnected, loss of power  Only half of payload collected data  K.E.G. didn’t function during flight Failure Summary

21. Conclusion  Despite some failures, mission still successful  Accelerometer data and KEG ground testing suggests kinetic energy could be a viable source of energy  Would required more refined, sensitive generator  Biggest obstacle is lack of noticeable acceleration during majority of ascent

22. { Appendices

23.  Secure components better  More extensive testing, earlier  More research into appropriate parts  Receive components earlier to extend testing time  Add more insulation, or reorganize structure to improve thermal properties Lessons Learned

24. Ready For Flight  Secure all components more precisely with electrical tape, Velcro and hot glue  Connect camera to proper switch, and seal exposed hole  New batteries and securing of switches before flight  Hobo programmed to start at new flight time for data collection  Thicker copper wire (12 gauge) and more coils on K.E.G. for higher voltage generation  Refined voltage sensor compatible with Arduino Uno  Store Dynamo in cool, dry place with batteries disconnected until flight time  No perishable objects inside

25.  Final Mass: 830 g  Final Budget: $213.78 Mass and Weight Budget

27. { Compliance Matrix #RequirementFulfillment 1.01 Our experiment shall use the motion of the BalloonSat to generate electricity and charge a battery. Successful construction and testing of generator. 1.02 After the BalloonSat lands it shall still be in working order. Successful kick and drop tests. 1.03 The flight string interface shall be a PVC tube that runs through the BalloonSat and shall not pull through the BalloonSat or interfere with the string. We shall use washers on both sides of the tube and pins that dissipate the pressure onto the washer, preventing the string from being pulled through. Successful whip tests and integration of flight tube through center of structure. 1.04 The BalloonSat shall remain above -10° C internally during the entire flight. Successful cold tests and construction of heater. 1.05 The total weight shall remain less than or equal to 850 grams. Total weight was less than 850 grams. 1.06 We shall acquire the ascent and descent rates of the BalloonSat. Accelerometer measures changes in flight velocities. 1.07 Our design shall include a HOBO H08-004-02.Successful integration and data collection during cold test.

28. 1.08 Our design shall include an external temperature cable. External cable is connected to HOBO. 1.09 Our design shall allow for a Canon SD780.Successful integration of camera in the corner of Dynamo. 1.10 BalloonSat shall include an active heater system weighing 100 grams with batteries. Successful construction and test of heater. 1.11 BalloonSat shall be made of foam core.Successful construction of structure using foam core. 1.12 Our budget shall include a parts list, including spare parts. Budget is complete and maintains a surplus. 1.13 The design shall allow for and present on the outside of the satellite contact information for the Careful, Harry! team as well as an American flag. Successful placement of USA flag and contact information on exterior. 1.14 All units presented in the design, construction, and use of the satellite shall be expressed only in the metric system. Metric system was used for all calculations and dimensions 1.15 The satellite shall be fully constructed and prepared for launch and recovery no later than November 5, 2011, and at least one team member shall agree to participate in the retrieval of the satellite. Successful construction and test of entire satellite and components.

29. 1.16 Nobody, at any time, or in any phase of this project, shall be injured in any way. No one was injured during construction and testing. 1.17 All hardware and other materials used are a part of the Gateway to Space program, and shall return to Professor Koehler at the end of the semester in full working order and absolutely no damages. All material is in working order with no damages. 1.18 All purchases using Professor Koehler's CU Visa for parts shall be recorded in extreme detail on the budget, and all receipts from any purchase made shall be kept and turned in to Professor Koehler within 48 hours of the purchase. Furthermore, a copy of the Gateway order form, HW 04, shall be provided alongside every purchase that is made. These purchases shall only be made after an appointment with Professor Koehler. Successful recording of purchases, and submission of all receipts for payment and/or reimbursement. 1.19 The satellite design shall not allow for any living organism to be included on the payload. Payload does not include any living organisms. 1.20 The design of the satellite shall include a visual indicator on the outside of the craft that confirms the payload is fully functional and running. Switches, button, and flashing LED light indicate proper function.

30. Message To Next Semester  Choose a challenging yet feasible project  Meet early and often with team  Tim May and ITL staff are great resources  Secure internal components as best as you can  Extra weight, use it for insulation  Be friendly and work well with your teammates  Don’t give up and work hard