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Preliminary design method for deployable spacecraft beamsThere is currently considerable interest in low-cost, lightweight, compactly packageable deployable elements for various future missions involving small spacecraft. These elements must also have a simple and reliable deployment scheme and possess zero or very small free-play. Although most small spacecraft do not experience large disturbances, very low stiffness appendages or free-play can couple with even small disturbances and lead to unacceptably large attitude errors which may involve the introduction of a flexible-body control system. A class of structures referred to as 'rigidized structures' offers significant promise in providing deployable elements that will meet these needs for small spacecraft. The purpose of this paper is to introduce several rigidizable concepts and to develop a design methodology which permits a rational comparison of these elements to be made with alternate concepts.
Document ID
19960000759
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mikulas, Martin M., Jr. (Colorado Univ. Boulder, CO, United States)
Cassapakis, Costas (Colorado Univ. Boulder, CO, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1995
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-CR-199240
NAS 1.26:199240
Accession Number
96N10759
Funding Number(s)
CONTRACT_GRANT: NAG1-1642
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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