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NMSU SHOT II WORKSHOP

NMSU SHOT II WORKSHOP. Klipsch School of Electrical and Computer Engineering & Mechanical Engineering Department Jeremy Bruggemann Michelle Chavez Trevenor Evans George Kuchera. Mission Overview.

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NMSU SHOT II WORKSHOP

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  1. NMSU SHOT II WORKSHOP Klipsch School of Electrical and Computer Engineering & Mechanical Engineering Department Jeremy Bruggemann Michelle Chavez Trevenor Evans George Kuchera

  2. Mission Overview Our SHOT II mission is to test sensors, code, and components from our UN-4 nanosat project in order to get preliminary characterizations.

  3. Relationship to UN-4 Mission • Test computer code for UN-4 nanosat, as well as run ADC and test data • Prove that that the science sensors and flight computer function in a cold environment • Familiarize NMSU UN-4 team with nanosat hardware so they may communicate with, control, and obtain viable data

  4. SHOT II Design • Data Logging • DOS 6.2 operating system • Quick Basic control program that starts on power-up • Diamond Systems Prometheus CPU with integrated 16-channel ADC • Data recorded every 10 seconds to a 32 MB flash disk

  5. Payload Design All values stored as ASCII

  6. Payload Structure Design • Shell is formed from 1/8-inch aluminum honeycomb plates • Insulation added to internal surfaces • On/Off switch to exterior

  7. Drop Test Test Design: Drop payload from a 15-foot height to a concrete patio Use actual structure materials, battery, non-functional CPU, mass simulators for sensors Results Structure suffered a dent where it landed but did not break open No visible damage to internal components Testing

  8. Cold Test Test Design: Place payload into a chest with dry ice for three hours Run the payload as if it were a flight (use charged batteries, collect data) Results – Sensors operated normally with the following temperature and pressure readings: Temperature 50.4 degrees C flight computer 22.3 degrees ambient air Pressure Voltage 3.46 (normal for testing altitude) Testing

  9. Expected Results • Should be able to see magnetometer reacting to orientation • Determine how much vibration the payload was under and ensure that pressure, altitude and acceleration characterize test environment • See GPS drop out (ITAR altitude limit) • Collect 2-hours minimum of data • Gain better understanding of satellite orientation with earth sensors

  10. Demonstration

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