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Spacecraft attitude pointing performance during orbit adjust as a function of compensator orderA steady state compensator of specified order is proposed to estimate the required duty cycle needed to balance the distribution torque. The compensator was increased gradually to demonstrate the improvement in pointing accuracy. The basic mathematical model of the flexible spacecraft and sensor used to characterize the performance of the compensator are described.
Document ID
19820002203
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Basuthakur, S. (General Electric Co. Philadelphia, PA, United States)
Duelfer, R. (General Electric Co. Philadelphia, PA, United States)
Peckjian, A. (General Electric Co. Philadelphia, PA, United States)
Stick, T. (General Electric Co. Philadelphia, PA, United States)
Date Acquired
August 10, 2013
Publication Date
October 1, 1981
Publication Information
Publication: NASA. Goddard Space Flight Center Sixth Ann. Flight Mech.(Estimation Theory Symp.
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
82N10076
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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