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Equilibrium and stability of a satellite influenced by gravitational and aerodynamic torquesA circular orbit and constant atmospheric density was assumed. A computer program which determines equilibrium attitudes and the associated eigenvalues of these attitudes is presented. Demonstration of the use of this program was made using the former Skylab satellite as an example.
Document ID
19810009554
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Galaboff, Z. J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
NASA-TM-82401
Report Number: NASA-TM-82401
Accession Number
81N18078
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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