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CRITICAL Design Review RockSat -C

Pegasis II. CRITICAL Design Review RockSat -C. December 3, 2012 Mitchell Community College MCC Aerospace Engineering and Technology. Pegasis II. Mission Overview Presented By: Patrick Mencias -Lewis. Mission Statement.

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CRITICAL Design Review RockSat -C

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  1. Pegasis II CRITICAL Design ReviewRockSat-C December 3, 2012 Mitchell Community College MCC Aerospace Engineering and Technology RockSat-C 2013

  2. RockSat-C 2013

  3. RockSat-C 2013

  4. PegasisII Mission Overview Presented By: Patrick Mencias-Lewis RockSat-C 2013

  5. Mission Statement Our goal is to power space-based instrumentation systems by passively generating energy from transducers of a proprietary design. Energy will be harvested from the rocket flight, solar rays, and other sources. This will be accomplished by building a more robust and simplistic payload using transducers with increased efficiency and improved design characteristics. Results may lower cost and power requirements for space science by reducing the weight of electrical components. RockSat-C 2013

  6. Organizational Chart RockSat-C 2013

  7. Theories and Concepts • Electromagnetic transducers will utilize Faraday’s Law. • Solar transducers will utilize Photoelectric effect. • Peltier coolers will use solar transducer to act as a heat sink for microprocessors • Piezoelectric effect RockSat-C 2013

  8. Concept of Operations Concept of Operations RockSat-C 2013

  9. Concept of Operations • Event A • Ignition, spike in data, collection begins • Event B • Orion burn ends, spike in data, collection continues • Event C • Apogee, little to no voltage measured, collection continues • Event D • Chute deploys, spike in data, collection continues • Event E • Splash down, spike in data, collection continues until retrieval RockSat-C 2013 RockSat-C 2013 9

  10. Expected Results CONTROL A sensing board will be powered by a fixed battery. It will record and save data of different environmental variables. EXPERIMENT A sensing board will be powered by energy gathering devices. The energy used from both sensing boards will be recorded and saved for comparison. Energy produced by transducers will also be recorded and saved. TRANSDUCERS Transducers are expected to produce from 2V to 15V peak. Currents will vary depending on transducer design and coil development. RockSat-C 2013

  11. PegasisII Mechanical Description Presented By: Joseph Edwards RockSat-C 2013

  12. De-Scopes & Off Ramps • All transducers are to be completed as designed. • May implement a fractal design coil to harvest the earth’s electromagnetic field. RockSat-C 2013

  13. Mechanical design Description Jerk RockSat-C 2013

  14. Mechanical design Description Bristol RockSat-C 2013

  15. Mechanical design Description EM Pendulum’s Pendulum RockSat-C 2013

  16. Mechanical design Description EM Pendulum’s Base RockSat-C 2013

  17. Mechanical design Description Diving Board RockSat-C 2013

  18. Mechanical design Description Aubade RockSat-C 2013

  19. PegasisII Electrical Description Presented By: Tony Briceno RockSat-C 2013

  20. Electrical Design Description RockSat-C 2013

  21. Electrical Design Description RockSat-C 2013

  22. Electrical Design Description To be Completed • Design and test a z-axis g-switch to latch power on after lift-off • Test battery configurations for longevity and current supply • Research availability of surface mount versions of components from 2012 mission Changes • Main processor and both sensing boards will contained on one circuit board • Low power processors were chosen for testing. No negative effects are indicated from datasheets on processor performance. The lower voltages will increase battery performance. RockSat-C 2013

  23. Electrical Design Description Activation • Our payload will use command line activation • A z-axis g-switch will latch the power supply after lift off. RockSat-C 2013

  24. Electrical Design Description Plan of attack deadlines • 12/14 - Test different processors to confirm final selection • 1/11 – Confirm components for power supply and basic processor operation • 1/18 – Basic coil design testing should be done to determine possible voltage maximums • 1/25 – Confirm components for USB operation to comply with USB 2.0 standards • 2/8 – Build proto-board to test revision 1 of software code on • 2/15 – Final coil designs should be determined for each transducer • 2/22 – Finalize revision 1 of board design and expand to include sensing boards • 2/29 – Finalize voltage regulation of transducers to keep from damaging processors during A/D conversion.

  25. Electrical Design Description To be considered • Voltage regulators need to be chosen for each processor, 2 in total • At least 3 revisions will be needed before a flight ready board will be available • 2 prototypes will be built in house for testing. Revisions 1 and 2. • Subsequent revisions will be designed for manufacture from a board house. • PCB to transducer wiring harness connectors and wiring still needs to be determined • Smaller more efficient solar cells need to be obtained to replace the current Aubade design

  26. PegasisII Software Description Presented By: Tony Briceno RockSat-C 2013

  27. Software Design Description Purpose • Control the measuring of power developed by transducers and used by sensing boards • Store the information in a readable form. I/O’s • Analog input for transducers and sensing boards (ADC) • Digital output for indicator LED RockSat-C 2013

  28. Software Design Description To be Completed • Processor settings need to be confirmed and tested for proper operation. • ADCloop – Settings need to be checked and code tested to check proper operation. • USB settings need to be confirmed. Preferably compliant with USB 2.0 standards. Interface and code needs to be checked for proper operation. RockSat-C 2013

  29. Software Design Description RockSat-C 2013

  30. Software Design Description RockSat-C 2013

  31. Software Design Description Pseudo Code Main { Start Infinite loop Initialize (); Setup the processor CntDwnWait (); Wait until < T-1min SBactivation (); Send signal to start ADC cycle for both Sensing Boards Start ADC infinite loop ADCloop (); } RockSat-C 2013

  32. Software Design Description Pseudo Code Initialize { Select clock settings Select Communication ports and settings Select analog ins and digital outs Set interrupts } CtnDownWait { Loop for Aprox 2 min } RockSat-C 2013

  33. Software Design Description Pseudo Code SBactivation { Set two outputs to low -this signals the SBs to start the ADC cycle } ADCloop { Select AD channel Transmit AD channel to SDcard Capture AD voltage Transmit AD voltage to SDcard If all channels have not been sampled repeat loop If all channels have been sampled, send newline command to SDcard Repeat loop } RockSat-C 2013

  34. Software Design Description Plan of attack deadlines • 12/14 - Test different processors to confirm final selection • 12/21 – Confirm working code for processor initialization is working • Holiday break – use to time research USB 2.0 standards • 1/11 – Confirm A/D settings and ADCloop code functions properly • 1/18 – Finalize and test activation sequence for sensing boards • 1/25– Confirm USB settings and basic interface with computer • 2/1– Improve interface with computer to allow streaming data when connected • 2/8 – Test all portions of code working as one • 2/15 – Finalize revision 1 of software code RockSat-C 2013

  35. PegasisII Prototyping/Analysis Presented By: Colin Robinson RockSat-C 2013

  36. Prototyping/Analysis We have yet to begin testing. We have been designing and building our own equipment to test our components for each subsystem. We have also begun breaking down PEGASIS l parts to test against new components. RockSat-C 2013

  37. Prototyping/Analysis We are in the entry stages of prototyping and will have it complete by the beginning of next semester. RockSat-C 2013

  38. Mass Budget

  39. Electrical Design Description • Preliminary battery pack designs have us at approximately 7.5V and 9000mAh • Maximum current draw of the processors combined is approximately 400mA. Even if the batteries drain twice as fast as rated, there will still be sufficient current/voltage to power the devices for longer than planned.

  40. PegasisII Manufacturing Plan Presented By: Mason Young RockSat-C 2013

  41. ManufacturingPlan Need to be manufactured: • Makrolon Plates • Mounting Board for Electronics • Mounting device to hold battery RockSat-C 2013

  42. ManufacturingPlan Still need to be procured: • All items will be manufactured in house • Research on new magnets and possible procurement RockSat-C 2013

  43. ManufacturingPlan RockSat-C 2013

  44. ManufacturingPlan Electrical elements Need to be manufactured: • 2 prototypes • Proto-board RockSat-C 2013

  45. PegasisII Testing Plan Presented By: Nathan Keller RockSat-C 2013

  46. TestingPlan • Tests will verify payload meets user guide requirements and functionality under high G-forces, strong vibrational forces, and heat • Similar to last year a mock up payload will undergo test flights and shake table testing • Additional tests have been included to test performance under heat and magnetic interference RockSat-C 2013

  47. Testing Plan • Functionality of the payload and individual components shall be tested through test flights and shake table testing • Measurement of G-forces and vibrational forces, inspection of components, and results from collected data will be used to verify functionality RockSat-C 2013

  48. Mechanical Testing Plan • Measurements of mass and volume will verify payload remains within user guide requirements • Individual components will be tested on fabrication is completed, full canister tests will begin once all individual components have been tested RockSat-C 2013

  49. Electrical Testing Plan • Electrical system will be tested to minimize effects from magnetic interference, ensure heat durability, and verify connections between components can withstand flight conditions • Placement tests of components will be used to minimize magnetic interference RockSat-C 2013

  50. Electrical Testing Plan • Connections will be tested during test flights and shake table testing • Payload will be tested for functionality under heated conditions to verify durability. • Electrical tests will begin once electrical components are acquired RockSat-C 2013

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