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Helios Critical Design Review

Fall 2011 Rev A 8-2-11. Helios Critical Design Review. Calder Lane, Courtney Ballard, Ian Thom, Thomas Green, Matt Cirbo , Janelle Montoya 10-6-11. Mission Overview.

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Helios Critical Design Review

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  1. Fall 2011 Rev A 8-2-11 HeliosCritical Design Review Calder Lane, Courtney Ballard, Ian Thom, Thomas Green, Matt Cirbo, Janelle Montoya 10-6-11

  2. Mission Overview • Objective: To send a BalloonSat capable of wireless energy transmission to an altitude of 100,000 feet and record data on the efficiency of transmission. • Purpose: To evaluate the efficiency of wireless energy transfer at high altitudes for possible application on a larger scale. • Hypothesis: The BalloonSat will transmit energy at a moderate efficiency to another satellite and provide it with electricity. Wireless energy transfer would negate several of the problems with photovoltaic arrays today. Weather, atmosphere and other events that block electromagnetic radiation render solar panels on the ground totally useless. However, in space, in the correct orbit, a solar cell bearing satellite could provide and endless stream of energy to Earth through any condition. With several receiving stations, or a high power microwave generator, energy could be produced constantly and consistently.

  3. RequirementFlow Down

  4. Design (Proposal Requirements Met) • Testing efficiency of laser transfer of Energy • Solar panels (both structures) • Laser diode • Volt-ammeter • Satellite shall not exceed 850 grams • Lightweight, sturdy materials (i.e. carbon fiber) • Effective use of space in structures • Data collected during ascent and descent • HOBO, temperature cable • Canon SD780 (also lightweight) • Heater to maintain internal temp (make testing possible) • Satellite will remain intact • Durable materials • Foam for insulation and to avoid shock

  5. Design (Structure) • Helios will integrate two separate boxes • One box will be used for energy transmission (Sat 1) • Sat 1 will be a 15cm cube • One will be used to receive energy (Sat 2) • Sat 2 will be 9x9x5cm rectangle • Sat's 1 and 2 will be connected on the flight string and with two carbon fiber tubes to ensure energy transmission.

  6. Design (Power) • Power will be provided by 9 solar cells • Solar cells will feed a 3.7 volt 2600mah lithium battery • A 3-6 volt 650nm 50 mw red laser will transfer power, wirelessly between the two satellites. • Sat 2 will receive power using a 10th solar cell and route it through a Microprocessor and Volt/Ammeter PCV board • A red light filter will be incorporated into Sat 2 for ambient light filtration

  7. Design (Thermal) • Three 9 volt batteries in Sat 1 will power a heater • Internal Infrared insulation and ambient heat will be used to heat both satellites • Sat 2 will integrate extra internal infrared insulation and “waste” heat from the microprocessors. • Both satellites will use external insulation as well.

  8. Design (Data Storage) • Data will be stored on a 2 Gigabyte micro SD card. • Card will be contained within an Arduino card shield • Data will be measured by a PCB board with both volt and amp analog outputs. • Data will be processed using an Arduino Uno microprocessor. • These parts will all be contained within Sat 2

  9. Design Renderings

  10. Switch Box Diagram 3.7 Volt lithium battery 2600 mah Solar Cells 3x9V Batteries Switch Switch Rechargeable Battery HOBO Onboard Heater 50-100mw Laser Diode Thermometer Barometer  Hygrometer Rechargeable Battery  Switch Photovoltaic Panel Camera Arduino Uno and Micro SD card Volt/Ammeter PCB Board 2 Gigabyte SD card

  11. Parts Used • Arduino Uno: Arrived 10/3 • AttoPilot Sense Breakout 180: Arrived 10/3 • MircoSD Shield: Arrived 10/3 • 3.7 Volt 2600 mAh LG Li-Ion Battery with PCB and Wires Ordered and expected to arrive 10/6-10/7 • Solar Cells: Ordered and expected to arrive 10/5-10/7 • 50mW 650nm laser: Ordered and expected to arrive 10/12 • Carbon Tubing: Ordered and expected to arrive 10/5-10/7

  12. Testing • We will conduct the drop test, roll test, whip test, and cold test (roll, drop, and whip all on 10/13 and cold on 10/20) • We will test the efficiency of the solar cells (10/11) • We will test the filter by emitting it to the sun and testing to see how much energy is being produced by just the light from the sun (10/11) • We will test to make sure that the solar panel is able to generate energy using the laser (10/20) • We will test the alignment of the laser and the solar cell by using the vibration table in the ITLL (10/20)

  13. Team Organization Chart

  14. Schedule

  15. Budget

  16. Expected Results • We expect the satellite to receive low amounts of power in the form of laser radiation and convert it back into useable electricity. This will then be measured in real time and stored for later analysis.

  17. Biggest Worries • The laser doesn’t transfer the energy to the solar panel. • The carbon tubes are not stable enough to keep the laser pointed to the solar panel. • Making the programing compatible to all the components.

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