Computer Science – Performance
Scientific paper
Mar 1978
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1978guco.conf...70m&link_type=abstract
In: Guidance and Control Conference, Palo Alto, Calif., August 7-9, 1978, Technical Papers. (A78-50159 22-01) New York, American
Computer Science
Performance
Airborne/Spaceborne Computers, Attitude Indicators, Kalman Filters, Multimission Modular Spacecraft, Star Trackers, Strapdown Inertial Guidance, Algorithms, Attitude Gyros, Instrument Errors, Maximum Likelihood Estimates, Pointing Control Systems, Signal Processing
Scientific paper
Attitude determination algorithms for a multimission spacecraft are derived and their performance analyzed. The attitude determination system is composed of a strapdown Inertial Reference Unit (IRU), two fixed head star trackers, and an onboard computer. IRU data is processed to maintain real-time knowledge of spacecraft attitude relative to an inertial reference frame. Star tracker data is processed using Kalman filtering techniques to estimate and correct the attitude determination errors and the gyro drift compensation errors. The results of a star availability analysis for stellar, solar and earth pointing missions are presented. Linear covariance analysis techniques are used to evaluate nominal attitude determination performance, the effects of sensor measurement accuracy variations, the effects of errors in knowledge of sensor measurement accuracy, and the effects of star tracker misalignment errors. Results of a nonlinear simulation analysis of attitude determination performance are also presented. These analyses show that precision attitude determination for stellar, solar and earth pointing missions is achieved.
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