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Drexel University  2010-2011 RockSat -C Conceptual Design Review

Drexel University  2010-2011 RockSat -C Conceptual Design Review. Joe Mozloom Eric Marz Linda McLaughlin Swati Maini Swapnil Mengawade Advisor: Jin Kang, PhD. Mission Overview. Objective 

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Drexel University  2010-2011 RockSat -C Conceptual Design Review

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  1. Drexel University 2010-2011 RockSat-CConceptual Design Review Joe Mozloom Eric Marz Linda McLaughlin Swati Maini Swapnil Mengawade Advisor: Jin Kang, PhD

  2. Mission Overview Objective  Drexel's RockSat payload will incorporate a platform rotating opposite the spin-stabilization of the Terrior-Orion sounding rocket during ascent, resulting in a rotationally static platform from an outside reference frame.

  3. Mission Overview Purpose Experimentally determine the feasibility of a despun platform under high acceleration and turbulence, driven by a low power system. Provide a stable platform with respect to the exterior environment to accommodate experiments requiring constant frame of reference in a traversing object.

  4. Mission Overview • Theory • A Microelectromechanical systems (MEMS) gyroscope is based on the physical principal that a vibrating object will continue to vibrate along the same plane as its support is rotated. • MEMS Gyroscopes utilize Coriolis Effect • The apparent defection of a moving object when viewed from a rotation reference frame.

  5. Mission Overview

  6. Mission Overview

  7. Mission Overview

  8. Mission Overview

  9. Success Criteria • Flight • Meet all NASA / WFF requirements • Counter-rotating platform engaged when canister is spinning • Platform able to rotate under harsh flight conditions •  Data is reliably collected and is usable Workbench • Meet all NASA / WFF requirements • Counter-rotating platform effective from 0.5 Hz - 10 Hz • Maximum platform spin-rate 10% of maximum canister spin-rate • Data is reliably collected and is usable

  10. Mission Expectations • Despun platform rotates against the rotation of rocket • System capable of surviving and functioning in launch environment

  11. Previous research Currently, minimal research has been completed regarding despun payloads during ascent. Most despun applications occur in orbit and utilize external thrust vectoring of entire rocket. • Leonard Blaisdell, Richard Rubin, Otto Mahr. "ATS Mechanically Despun Communications Satellite Antenna." IEEE Transactions on Antennas and Propagation 17 (1969): 416-28. • Successful mechanically despun internal payload (for • antenna use)

  12. Design Overview • Payload consists of a platform fixed to canister • Will spin at the same rate as the spin stabilized Terrior-Orion Rocket • Platform to be despun elevated above fixed platform • Able to freely rotate about the longitudinal axis of rocket • Attached to the fixed platform via slip ring •  Allows data transfer with unrestricted rotational movement. • Outside edge of despun platform geared to interface with motor • Geared platform will be rotated via electric motor(s) attached to the fixed platform • Motors spin geared platform equal and opposite the angular velocity of rocket • Gyroscope (possibly accelerometer) will be utilized on the fixed platform to calculate spin rate, and will be fed into the motor via a microcontroller • Despun platform will also have a gyroscope (or accelerometer) to calculate the platform spin rate for data collection and comparison

  13. Initial Design Despun Platform Gyroscope Motor(s) Gyroscope Data Handling, Storage, and Power Platform attached to Canister Despun platform post with bearings and slip-ring

  14. Block Diagram Microcontroller Motor Despun Platform Gyro Fixed Platform Gyro Memory

  15. Required Hardware • Low Voltage Electric Motor(s) • Slip-ring for data transfer • Low-Friction Bearings • Microcontroller • Memory • 9V Battery(s) • MEMS Gyroscopes

  16. Shared can logistics • Sharing 1/2 can with Temple University • Temple University will be measuring gamma and x-rays, up to 100keV, through the use of a scintillator and photomultiplier-tube. They will use visible solar light as a directional z-axis reference point to characterize the high energy particles as solar or cosmic rays. • No ports needed for experiment • Drexel and Temple have been communicating regularly thus far • Close geographic proximity allows for the teams to meet face to face and will aid in future collaboration.

  17. Team overview Advisor     Jin Kang, PhD. MEM Department Drexel University Team Leader     Joe Mozloom Senior Mechanical Engineering Members     Eric Marz   Senior   Electrical and Computer Engineering     Linda McLaughlin Senior Electrical and Computer Engineering     Swati Maini Senior Mechanical Engineering     Swapnil Mengawade Senior Mechanical Engineering

  18. budget

  19. timeline

  20. Conclusions • Experiment to be used as a feasibility study of stable, despun system under high acceleration • Challenges • Sourcing bearings to perform under high loads/vibration of flight environment • Sourcing motor(s) which are light, powerful, low voltage

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