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Zero-gyro control of the International Ultraviolet ExplorerThe IUE was built for an anticipated lifespan of three years with a goal of five. It has been operating for over 15 years, even though it has had only two working gyros since August 17, 1985, through the use of a two-gyro attitude control system that uses information from IUE's fine sun sensor (FSS) and the two remaining gyros to provide three-axis control. A one-gyro control system that uses an additional axis of information from the FSS has been developed and tested on-orbit. The purpose of this paper is to discuss the work in progress towards the development of a zero-gyro control law for IUE. Motion about the sunline, which cannot be measured by the FSS, is measured and controlled in the zero-gyro system by applying a momentum bias perpendicular to the sunline and measuring the transfer of this momentum between the spacecraft reaction wheels, while the spacecraft is held in the other two axes using position and derived-rate information from the FSS.
Document ID
19930067358
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
O'Donnell, James R., Jr.
(Universities Space Research Association; NASA, Goddard Space Flight Center Greenbelt, MD, United States)
Hoffman, Henry C.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Guidance, Navigation and Control Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-51301 22-63)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 93-3760
Accession Number
93A51355
Funding Number(s)
CONTRACT_GRANT: NAS5-30442
Distribution Limits
Public
Copyright
Other

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