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Orbit-averaged behavior of magnetic control laws for momentum unloadingAnalytical formulas are derived for orbit-averaged behavior of magnetic control laws for unloading the excess angular momentum of a spacecraft reaction wheel control system in the presence of secular environmental torques. The specific example of an axially symmetric spacecraft with an inertially fixed attitude for which the dominant environmental torque is the gravity-gradient torque is treated in detail, but extensions of the general approach to other inertially fixed and earth-pointing spacecraft are discussed. The analytical formulas are compared to detailed simulations performed for the Solar Maximum Mission spacecraft, and agreement to within 10% is found. The analytical formulas can be used in place of detailed simulations for preliminary studies, and can be used to find selected cases giving the most stringent tests of momentum unloading capability for which detailed simulations may be performed.
Document ID
19810034177
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Camillo, P. J.
(Computer Sciences Corp. Silver Spring, MD, United States)
Markley, F. L.
(Computer Sciences Corp. System Sciences Div., Silver Spring, Md., United States)
Date Acquired
August 11, 2013
Publication Date
December 1, 1980
Publication Information
Publication: Journal of Guidance and Control
Volume: 3
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
81A18581
Funding Number(s)
CONTRACT_GRANT: NAS5-11999
Distribution Limits
Public
Copyright
Other

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