APPENDAGE DEPLOYMENT VERIFICATION FOR THE 2001 MARS ODYSSEY SPACECRAFT USING SPACECRAFT ATTITUDE TELEMETRY

摘要

The 2001 Mars Odyssey Spacecraft was required to execute several mission critical appendage deployments and articulations along the way to its final Mars-mapping configuration. These events included Solar Array, High Gain Antenna, and Gamma Ray Spectrometer Instrument Boom deployments and positioning of the Solar Array for aero-braking passes. Verification of these events was necessary in order to proceed with nominal mission plans. This verification was accomplished through use of high sample rate (200 samples per second) spacecraft attitude telemetry data compared to analytic model predictions. The use of attitude data eliminated the need for any position monitoring sensors (limit switches, potentiometers, accelerometers etc.) other than the spacecraft Inertial Measurement Unit (IMU) itself, yet provided high-fidelity information regarding the mechanical performance of the spacecraft deployments and articulations. This paper summarizes the flight and simulation results from Mars Odyssey, demonstrating the ability to thoroughly verify spacecraft deployment and articulation activities without the need of additional sensors given the availability of IMU data acquired at sufficiently high sample rates.