1. Colorado State University Paul Scholz, Tyler Faucett, Abby Wilbourn, Michael Somers June 14 2010 1

2. Mission Overview Objective: to study alternative energy collection at different altitudes Find the ideal altitude for alternative (wind & solar) energy collection. Is high altitude energy collection worthwhile? Can the added cost of high altitude energy collection be made up for with increases in efficiency? 2

3. Current Products “MARS” – Maggen Air Rotor System 3

4. CoolEarth Solar Balloon MARS turbine 4

5. How we can help Our test could provide useful data to someone wishing to put up a similar system on Earth or Mars An airborne solar/wind power farm could be very useful for remote area power generation Our test vehicle will provide data to give an altitude of maximum power generation. 5

6. Mission Requirements TOP LEVEL Measure & Record Wind Speed - as a function of altitude Measure & Record Solar Panel Power - as a function of altitude SECONDARY LEVEL Measure & Record External Temperature Measure & Record External Pressure Measure & Record Acceleration - perpendicular to gravity 6 Increases accuracy of wind speed calculations Yield altitude and air density

7. Subsystems Structural Thermal Data Storage Processing Electrical Sensing 7

8. Subsystem – Structural Must have cylindrical shape Allows for even and constant sun exposure to solar faces Must have center core flight string pass through Pass through design must comply with all DemoSAT-B regulations Pressure differences inside and outside the payload must not exceed 10 psid 8

9. Subsystem - Thermal The internals of the payload must remain above 0C to prevent failures of electrical components The internal electrical components must be placed as close to the center of the payload as possible Internal flexible heaters will be installed to maintain required internal temps. Flexible heaters allow for easy placement near critical components (battery) Temp. Distribution Flux 9

10. Subsystem - Data Processing All sensor data shall be processed on a PIC 16F884 microcontroller Storage The PIC shall send data from the sensors to the data storage unit every 5 seconds The data storage device shall be removable and portable and must allow for computer interface 10

11. Subsystem - Electrical All electrical components must be powered by a 5V source The power supply must be able to produce 4.8V to 6V for at least 2 hours Switches for electrical components must be mounted on the external of the payload 11

12. Subsystem – Sensing Wind Speed Sensing – Anemometer must be at least 2in from the flight cord – At least 2 axis of acceleration must be sensed to accurately measure wind speed Altitude Sensing – Payload must contain at least 1 pressure sensor and 1 temperature sensor Pressure and Temp must be measured externally for accurate data Solar Panels – Solar panels must cover at least 90% of the rounded faces of the payload All external sensors must be able to operate at temperatures ranging from -80C to 30C 12

13. Subsystems Block Diagram 13

14. Schematics/Drawings/Analysis 14

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19. 100mph winds at -80C 5W internal heat generation Steady state. 19

20. 100mph winds at -80C 5W internal heat generation Steady state. 20

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24. Commands and Sensors Sample Rate Sample Duration # of samples Bytes/ Sample (estimated) Min Required Memory For data storage Available Memory 1 sample every 5 seconds 2 hours 1440 (samples/ sensor) * 6(sensors) = 8640 samples 4 bytes34560 bytes2Gb SD – (less due to formatting, etc.) Data transferred serially from PIC microcontroller to SD card mounted in SD card reader. 24

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26. Sensor Specifications SensorOperational Voltage Operational Temperature Measurement Range Notes Temperature3.0 to 5.5V-55C to +125C Converts Temperature to 12-bit Digital Word in 750 ms Pressure5.0V0C to 85C0 psi to 1 psi through 0 psi to 100 psi Response time of 8 ms Accelerometer (2-axis) 2.4V to 5.25V-20C to 70C+/- 18g----- Cup Anemometer ----- 3 mph to 125+ mph 2.5 mph per Hz (1 Hz=1 pulse/sec) Solar Panels (3) ----- Voltage: 7.2 V Watts: 1.44 W Amperage: 200 mA 26

27. Test Plans Testing Types Structural Test Whip test Drop test Stair pitch test Environmental Test Cooler Test Functional Tests Bench Test 27

28. Structural Tests Whip Test Hardware Required: Test structure (full model minus electrical board, heaters, power supply) Possible Point of Failure: Carbon fiber tube could snap, top plate could bend Drop Test Possible Point of Failure: Carbon fiber tube breakage, exterior fracture/puncture, studs in foam pull out Stair Pitch Test Possible Point of Failure: Carbon fiber tube breakage, exterior fracture/ puncture, studs in foam pull out 28

29. Environmental Tests Cooler Test Must purchase Dry Ice and Cooler Will also test solar array independently of payload Potential Point of Failure: Payload: Insulation design may be flawed and low internal temps may cause freezing/condensation on electrical components. Solar Array: may find that we need to account for power change due specifically to temperature change. 29

30. Functional Test Bench Test Potential Points of Failure: Overheating of internal electrical components No data transmission to SD Card No data transmission from sensors Wiring failure 30

31. Parts List 31

32. Schedule 32

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34. Mass BudgetMonetary Budget 34

35. Questions? 35