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A parametric study of the behavior of the angular momentum vector during spin rate changes of rigid body spacecraftDuring a spin-up or spin-down maneuver of a spinning spacecraft, it is usual to have not only a constant body-fixed torque about the desired spin axis, but also small undesired constant torques about the transverse axes. This causes the orientation of the angular momentum vector to change in inertial space. Since an analytic solution is available for the angular momentum vector as a function of time, this behavior can be studied for large variations of the dynamic parameters, such as the initial spin rate, the inertial properties and the torques. As an example, the spin-up and spin-down maneuvers of the Galileo spacecraft was studied and as a result, very simple heuristic solutions were discovered which provide very good approximations to the parametric behavior of the angular momentum vector orientation.
Document ID
19820056482
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Longuski, J. M.
(California Institute of Technology, Jet Propulsion Laboratory, Guidance and Control Section, Pasadena CA, United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1982
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 82-1467
Meeting Information
Meeting: Astrodynamics Conference
Location: San Diego, CA
Start Date: August 9, 1982
End Date: August 11, 1982
Sponsors: American Institute of Aeronautics and Astronautics and American Astronautical Society
Accession Number
82A40017
Distribution Limits
Public
Copyright
Other

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