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Testing of Gyroless Estimation Algorithms for the FUSE SpacecraftThe 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 also 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. The only sensor available during slews is a magnetometer. This paper documents the testing and development of gyroless attitude and rate estimation algorithms for FUSE. The results of two approaches are presented, one relies on a kinematics model for propagation, a method used in aircraft tracking, and the other is a traditional Extended Kalman filter that utilizes Euler's equations in the propagation of the estimated rate. Finally, the question of closed-loop stability is addressed. The ability of the controller to meet the science slew requirements, without the gyros, is tested through simulations.
Document ID
20030054392
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Thienel, Julie
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Harman, Rick
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Oshman, Yaakov
(Technion - Israel Inst. of Tech. Haifa, Israel)
Date Acquired
August 21, 2013
Publication Date
January 1, 2003
Subject Category
Spacecraft Instrumentation And Astrionics
Meeting Information
Meeting: AAs Guidance and Control Conference
Location: Breckenridge, CO
Country: United States
Start Date: February 5, 2003
End Date: February 9, 2003
Distribution Limits
Public
Copyright
Other

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