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Analysis, design, and test of a graphite/polyimide Shuttle orbiter body flap segmentFor future missions, increases in Space Shuttle orbiter deliverable and recoverable payload weight capability may be needed. Such increases could be obtained by reducing the inert weight of the Shuttle. The application of advanced composites in orbiter structural components would make it possible to achieve such reductions. In 1975, NASA selected the orbiter body flap as a demonstration component for the Composite for Advanced Space Transportation Systems (CASTS) program. The progress made in 1977 through 1980 was integrated into a design of a graphite/polyimide (Gr/Pi) body flap technology demonstration segment (TDS). Aspects of composite body flap design and analysis are discussed, taking into account the direct-bond fibrous refractory composite insulation (FRCI) tile on Gr/Pi structure, Gr/Pi body flap weight savings, the body flap design concept, and composite body flap analysis. Details regarding the Gr/Pi technology demonstration segment are also examined.
Document ID
19830042419
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Graves, S. R.
(Rockwell International Corp. Downey, CA, United States)
Morita, W. H.
(Rockwell International Corp. Shuttle Orbiter Div., Downey, CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1982
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: Material and process advances ''82; Fourteenth National SAMPE Technical Conference
Location: Atlanta, GA
Start Date: October 12, 1982
End Date: October 14, 1982
Sponsors: Ciba Geigy Corp.
Accession Number
83A23637
Distribution Limits
Public
Copyright
Other

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