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NMSU SHOT II WORKSHOP. Klipsch School of Electrical and Computer Engineering & Mechanical Engineering Department Jeremy Bruggemann Michelle Chavez Trevenor Evans George Kuchera. Mission Overview. - PowerPoint PPT Presentation
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NMSU SHOT II WORKSHOP
Klipsch School of Electrical and Computer Engineering & Mechanical Engineering Department
Jeremy Bruggemann
Michelle Chavez
Trevenor Evans
George Kuchera
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.
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
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
Prometheus CPU
GPS
Ma
gn
eto
me
ter
COM1
COM2
DC/DC Converter
7 VX Y,Z P
T1 T2
Analog In
ES1 ES2
Payload Design
Datum ValueTime Seconds since midnight
Channel 1 (z acceleration) #, lsb, msb
Channel 2 (x acceleration) #, lsb, msb
Channel 3 (y acceleration) #, lsb, msb
Channel 4 (pressure) #, lsb, msb
Channel 5 – 8 (Earth sensor array 1) #, lsb, msb
Channel 9 – 12 (Earth sensor array 2) #, lsb, msb
Channel 13 (temperature 1) #, lsb, msb
Channel 14 (temperature 2) #, lsb, msb
GPS fix GGA navigation message
All values stored as ASCII
Payload Structure Design
– Shell is formed from 1/8-inch aluminum honeycomb plates
– Insulation added to internal surfaces
– On/Off switch to exterior
Testing
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
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)
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
Demonstration