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The CANDEL Project

The CANDEL Project. CAN Sat DEL ivery Project Laura Lewis Jens Ramrath Cecil Strickland. Background. Idea originated at the 1998 University Space Systems Symposium Expected Launch Date - Fall 1999 Participating Universities Include: Stanford Univ. of Hawaii

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The CANDEL Project

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  1. The CANDEL Project CANSat DELivery Project Laura Lewis Jens Ramrath Cecil Strickland

  2. Background • Idea originated at the 1998 University Space Systems Symposium • Expected Launch Date - Fall 1999 • Participating Universities Include: Stanford Univ. of Hawaii Univ. of Tokyo Tokyo Inst. Of Tech.

  3. Objectives • Design a carrier to house 12 CanSats • Eject 12 CanSats from carrier • Use onboard camera to view activity during deployment • Transmit pictures to specified location on Earth • Reenter the Earth’s atmosphere • Burn up on reentry

  4. Our first design• Initial Designs • Brainstorm concept at conference

  5. 30° Final Deployment Design • Use rotational velocity, , as primary means of deployment • Assist deployment by light springs 

  6. 200mm 70mm 142mm 382mm CanSat 2-D Design

  7. Carrier Design • Cylindrical case with a 382mm diameter • Cylindrical burrows slightly larger than a “coke” can opening radially outward • Cylindrical area in middle for housing of camera, power, and tracking device • Thin wire covering CanSat openings

  8. Can Attachment • Attached to: • Carrier • Adjacent Cans • Tether Joint

  9. Subsystems Placement • Pressurized canister in the center of the carrier • Provides protection from the space environment • Reduces costs of subsystems

  10. Satellite Subsystems • Camera Suggestions • Tracking Device Suggestions • GPS • NORAD Tracking • Picture Transmittal • Requirements

  11. CameraCMOS Active Pixel Sensor • A single +3.3 V supply • 11 pixel size - 512 x 512 pixel array • Digital I/O • Low noise • Timing and control implemented in chip • Low power (10mW at 1M pixels/sec) • Radiation resistant compared to CCD’s

  12. CMOS Active Pixel Sensor http://csmt.jpl.nasa.gov/APS/features

  13. Dycam Modular Digital Camera • Camera consumes 5V-9V at peak current • Image organization 496 x 288 pixels • Transmits picture to host computer upon request • Camera has its own processor and memory (1 or 4 Megabyte) • In sleep mode camera draws 3.5mA, awake mode 125mA, image capture 650 mA for 15ms • Operated with Dycam’s Picture Viewer Software

  14. Dycam Digital Modular Camera Camera Size: 63 x 24 x 197 mm Weight = 495 grams

  15. Tracking Devices • GPS Options • Simple receiver • Contained in pressurized canister • Determines when pictures will be transmitted to receiver on Earth • Space-hardened • Expensive • NORAD tracking Picture from:www.sni.net

  16. Transmittal Process • GPS • Transmit signal from satellite to receivers on Earth • Transmitter on Earth sends command to send pictures at appropriate time • NORAD tracking • Orbital Elements from NORAD will determine carrier location • Transmitter from Earth sends signal to receiver

  17. Transmittal • Amateur band radio transmitter located on satellite • Device will be used to determine best transmit time to Earth • Various receivers will be placed all over the world to receive pictures

  18. Requirements • Camera Power • CMOS requires 10mW • Dycam requires 5-9 V at 500 mA peak current • Ground Clock for picture transmittal • GPS Power • Power requirements will determine number of batteries needed

  19. CanSat Deployment • CanSats move to final circular position using angular momentum and are restrained by tethers

  20. CanSat Deployment • Carrier is ejected from primary payload • Wire is heated and allows CanSats to eject • CanSats will receive initial acceleration from springs

  21. Manufacturing of Dispenser • Three proposed materials: • Carbon-Epoxy composites • Aluminum • Foam

  22. Advantages of Foam • Very light • Easy to build satellite ourselves • Can withstand vacuum • Possible Temperature and radiation problems • Several different kinds of foam available

  23. Foam • Expanded polystyrene • regular styrofoam • is permanently deformed by impacts • Extruded polystyrene • hard foam • Expanded polypropylene • rubber-like foam • can withstand impacts

  24. Tether There are several possible materials • vectran • UV radiation resistant • zero creep • parachute chord • cheap

  25. Testing the dispenser • Test model in 1-g environment • Test in zero-g onboard NASA KC-135A aircraft (Vomit Comet)

  26. Questions ?

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