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Simultaneous calibrations of Voyager celestial and inertial attitude control systems in flightA mathematical description of the data reduction technique used to simultaneously calibrate the Voyager celestial and inertial attitude control subsystems is given. It is shown that knowledge of the spacecraft limit cycle motion, as measured by the celestial and the inertial sensors, is adequate to result in the estimates of a selected number of errors which adversely affect the spacecraft attitude knowledge.
Document ID
19820039493
Document Type
Reprint (Version printed in journal)
Authors
Jahanshahi, M. H.
(California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Publication Information
Publication: IEEE Transactions on Aerospace and Electronic Systems
Volume: 18
Subject Category
Spacecraft Instrumentation
Accession Number
82A23028
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other

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