The Far Ultraviolet Spectroscopic Explorer (FUSE) is equipped with two ring laser gyros on each of the spacecraft body axes. In May 2001 one gyro failed. It is anticipated that all of the remaining gyros will fail, based on intensity warnings. In addition to the gyro failure, two of four reaction wheels failed in late 2001. The spacecraft control now relies heavily on magnetic torque to perform the necessary science maneuvers and hold on target. The only sensor consistently available during slews is a magnetometer. This paper documents the testing and development of magnetometer-based gyroless attitude and rate estimation algorithms for FUSE. The results of two approaches are presented, one relies on a kinematic model for propagation, a method used in aircraft tracking. The other is a pseudo-linear Kalman filter that utilizes Euler's equations in the propagation of the estimated rate. Both algorithms are tested using flight data collected over a few months after the reaction wheel failure. Finally, the question of closed-loop stability is addressed. The ability of the controller to meet the science slew requirements, without the gyros, is analyzed.
Testing of Gyroless Estimation Algorithms for the FUSE Spacecraft
2003 AAS/AIAA Astrodynamics Specialist Conference Meeting ; 2003 ; Big Sky, MT, United States
2003-01-01
Preprint
No indication
English
Testing of Gyroless Estimation Algorithms for the FUSE Spacecraft (AAS 03-605)
British Library Conference Proceedings | 2004
|Gyroless fine pointing on Small Explorer Spacecraft
NTRS | 1993
|Gyroless Fine Pointing on Small Explorer Spacecraft
British Library Conference Proceedings | 1993
|