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An analysis of the Kalman filter in the Gamma Ray Observatory (GRO) onboard attitude determination subsystem

Author
Garrick, Joseph
Published
Sep 1, 1988.
Physical Description
1 electronic document
Additional Creators
Harman, Richard and Snow, Frank
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
The Gamma Ray Observatory (GRO) spacecraft needs a highly accurate attitude knowledge to achieve its mission objectives. Utilizing the fixed-head star trackers (FHSTs) for observations and gyroscopes for attitude propagation, the discrete Kalman Filter processes the attitude data to obtain an onboard accuracy of 86 arc seconds (3 sigma). A combination of linear analysis and simulations using the GRO Software Simulator (GROSS) are employed to investigate the Kalman filter for stability and the effects of corrupted observations (misalignment, noise), incomplete dynamic modeling, and nonlinear errors on Kalman filter. In the simulations, on-board attitude is compared with true attitude, the sensitivity of attitude error to model errors is graphed, and a statistical analysis is performed on the residuals of the Kalman Filter. In this paper, the modeling and sensor errors that degrade the Kalman filter solution beyond mission requirements are studied, and methods are offered to identify the source of these errors.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19890006578.
Accession ID: 89N15949.
Flight Mechanics(Estimation Theory Symposium 1988; p 289-325.
Terms of Use and Reproduction
No Copyright.
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