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

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