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Closed loop navigation and guidance for gravity probe B orbit insertionThis paper addresses the problem of guiding the Gravity Probe B (GP-B) spacecraft from its location after initial insertion to a very precise low earth orbit. Specifically, the satellite orbit is required to be circular to within 0.001 eccentricity, polar to within 0.001 deg inclination, and aligned with the direction of the star Rigel to within 0.001 deg. Navigation data supplied by an on-board GPS receiver is used as feedback to a control algorithm designed to minimize the time to achieve the desired orbit. Translational control is provided by the proportional helium thrusters, which are used for drag-free and attitude control during the remainder of the science mission. Simulations of the guidance system are presented which give an indication of performance characteristics for several types of orbit injection errors. This research is the first reported effort to use GPS as a sensor for a closed loop space guidance system.
Document ID
19890048424
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Axelrad, P.
(Stanford Univ. CA, United States)
Parkinson, B. W.
(Stanford University CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Publication Information
Publication: Navigation
Volume: 36
ISSN: 0028-1522
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking
Accession Number
89A35795
Funding Number(s)
CONTRACT_GRANT: NAS8-36125
Distribution Limits
Public
Copyright
Other

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