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The dynamics of spin stabilized spacecraft with movable appendages, part 1The motion and stability of spin stabilized spacecraft with movable external appendages are treated both analytically and numerically. The two basic types of appendages considered are: (1) a telescoping type of varying length and (2) a hinged type of fixed length whose orientation with respect to the main part of the spacecraft can vary. Two classes of telescoping appendages are considered: (a) where an end mass is mounted at the end of an (assumed) massless boom; and (b) where the appendage is assumed to consist of a uniformly distributed homogeneous mass throughout its length. For the telescoping system Eulerian equations of motion are developed. During all deployment sequences it is assumed that the transverse component of angular momentum is much smaller than the component along the major spin axis. Closed form analytical solutions for the time response of the transverse components of angular velocities are obtained when the spacecraft hub has a nearly spherical mass distribution.
Document ID
19750014295
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bainum, P. M. (Howard Univ. Washington, DC, United States)
Sellappan, R. (Howard Univ. Washington, DC, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1975
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-142703
Accession Number
75N22367
Funding Number(s)
CONTRACT_GRANT: NGR-09-011-053
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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