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A deployable structure and solar array controls experiment for STEPA candidate configuration for a controls experiment on the Space Technology Experiments Platform (STEP) is described. The elements of the experiment are the mast, the solar array, and an articulation module between the two. The characteristic dimensions are very compatible for integration on a pallet such a STEP's proposed configuration. The controls' objective would be the measurement of orbiter interaction as well as the system identification of the appendages. The flight experiment configuration would also provide a test bed for various active vibration controls concepts. The instrumentation being considered would measure accelerations, strains, displacements, and temperatures. The deployable mast has eight elements defining a structural bay. Uniaxial measurements would be required to define loads at a cross section of the structure. Displacements due to thermal distortion of the mast and the local state of the solar concentrator may be measured by an optical ranging technique from the orbiter aft flight deck.
Document ID
19840009159
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nishimoto, T. S.
(Rockwell International Corp. Downey, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Publication Information
Publication: NASA. Langley Research Center STEP Expt. Requirements
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
84N17227
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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