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University of Wyoming Dorin Blodgett, Kevin Brown, Heather Choi, Ben Lampe

University of Wyoming Dorin Blodgett, Kevin Brown, Heather Choi, Ben Lampe Eric Robinson, Michael Stephens, Patrick Weber October 7, 2010. Mission Overview. 3. 4. 5. 2. 1. 6. Scientific Objectives. Capture optical images of the earth. Collect space dust.

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University of Wyoming Dorin Blodgett, Kevin Brown, Heather Choi, Ben Lampe

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  1. University of Wyoming Dorin Blodgett, Kevin Brown, Heather Choi, Ben Lampe Eric Robinson, Michael Stephens, Patrick Weber October 7, 2010

  2. Mission Overview 3 4 5 2 1 6

  3. Scientific Objectives • Capture optical images of the earth. • Collect space dust. • Provide perspective of what is in our atmosphere. • Measure thermal, seismic and pressure effects throughout duration of launch. • Collect data for future projects

  4. Engineering Objectives • Engineer electronics systems for capturing and storing images from optical devices. • Create extendable booms to mount imaging equipment and dust collector. • Use AeroGelto collect space dust. • Create protective water shield for housing data storage devices and encasing AeroGel collector during reentry and splashdown. • Record thermal, seismic and pressure data in real time throughout launch using electronic sensors and transmit recorded data via provided Wallops telemetry.

  5. Mission Requirements The payload shall conform to the requirements set forth in the 2011 RockSat-X User Guide

  6. Specifications: Physical Constraints

  7. Specifications: Performance Parameters (Source: RockSat Payload Canister User’s Guide 2010)

  8. Success Criteria • At minimum, the payload shall gather data during launch, at apogee, and during reentry through the use of: • Thermocouples • 3-axis Accelerometers • Gyroscopes • Absolute Pressure Sensors • Ideally, the payload should also extend telescopic booms outside of the payload and: • Gather optical images of the Earth • Store photographs to on-board SD cards • Capture space dust using AeroGel

  9. Expected Results • Space Dust Composition (10^-6) • Rocket Fuel • Meteor/ Metal Fragments • Gases • Earth/Payload Images • Detailed Data through Flight Duration • Thermal Data • Seismic Data • Pressure Data

  10. Concept of Operations Rocket skins are shed, pressure within canister drops, boom is extended and begins to collect samples/take photographs. 3 4 T = 2.8 min. Samples/photographs continue to be collected/taken during descent. 5 2 Payload hits atmosphere, pressure within canister rises, boom is retracted and AeroGel is sealed within shield. Data is still being collected and transmitted over telemetry. Data continues to be transmitted. T = 4.5 min. T = 1.3 min. 1 6 T = 5.5 min. T = 0 min. T = 15 min. Circuits initialize and begin collecting and transmitting data. Power and telemetry is shut down and data collection and transmission ceases. Splashdown.

  11. Design Overview

  12. RockSat 2010 Payload Structure Aerogel Camera Electronics Factor of Safety = 1.5

  13. Payload Functional Block Diagram To Wallops Telemetry (10x 0-5V A/D 16-Bit, and Asynchronous) Power (NASA) G-Switch RBF (Wallops) X/Y Accelerometer Pressure Sensor Z Accelerometer Boom Actuator ADC Pressure Sensor Microcontroller Thermocouple 1 Solid State Storage Device Thermocouple 2 Solid State Storage Device Microcontroller … Solid State Storage Device Thermocouple n Solid State Storage Device Microcontroller Optical Camera 2 Optical Camera 1 ADC

  14. Design Specifications, Mechanical • Water Shield • Material (weight, thermal conductivity, impact and vibration resistance) • Sealing around data connections • Dynamic sealing around AeroGel following successful data collection • Structure • Able to withstand 25G with 50G+ impulse loads • Harmonic Oscillations • Boom • Telescopic Mechanical Arm • Surviving launch and vibration loads • AeroGelretrieval

  15. Design Specifications, Electrical • Automation • Booms, Control Motors • Timed Exposures – Gyroscope and Light sensors • Data Acquisition • Thermal (Thermocouples) • Seismic (Multi-Axis Accelerometers) • Pressure Measurements (Piezoelectric Strain Gage, Absolute) • Send Measurements through 10x 0-5V 16-bit A/D lines • Photo Capture • Optical Camera (~390 – 750nm) • Implementation • Photos stored on redundant SD cards (Multi-GB) • Data sent through NASA telemetry • Payload powered by NASA

  16. AstroX Team

  17. Management

  18. Management • Schedule • See Attachment • Budget • Mass (15-30lbs) • Boom (7 lbs) • Circuits (1 lb) • Water Shield (2 lbs) • Camera (4 lbs) • Other Sensors (1 lb) • Monetary Budget • $850

  19. Conclusions • Mission Recap • Capture optical images of the earth. • Collect space dust via aerogel. • Measure thermal, seismic and pressure effects throughout duration of launch. • Issues • Sufficient funds • Engineering success • Waterproofing payload • Extreme vibrations

  20. Questions?

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