Improvements in ERBS attitude determination without gyrosPrevious papers have described the modification of the Earth Radiation Budget Satellite (ERBS) Attitude Determination System (ADS) to overcome the impact of on board gyro degradation and failure on attitude ground support of the mission. Two approaches were taken: implementing a Kalman filter in place of the batch-least-squares attitude estimator to account for the propagation error produced by high-noise gyro data, and modeling the ERBS attitude dynamics to restore rate information in the case of gyro failure. Both of these methods had shortcomings. In practice, the filter attitude diverged without complete sensor observability, and accurate dynamics modeling required knowledge of disturbance torque parameters that had to be determined manually. These difficulties have been overcome by improved tuning of the filter and by incorporating dynamics parameter estimation into the ERBS ADS.
Document ID
19930015521
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chu, D. (Computer Sciences Corp. Lanham, MD, United States)
Glickman, J. (Computer Sciences Corp. Lanham, MD, United States)
Harvie, E. (Computer Sciences Corp. Lanham, MD, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1993
Publication Information
Publication: NASA. Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium, 1992