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Heat sink structural design concepts for a hypersonic research airplaneHypersonic research aircraft design requires careful consideration of thermal stresses. This paper relates some of the problems in a heat sink structural design that can be avoided by appropriate selection of design options including material selection, design concepts, and load paths. Data on several thermal loading conditions are presented on various conventional designs including bulkheads, longerons, fittings, and frames. Results indicate that conventional designs are inadequate and that acceptable designs are possible by incorporating innovative design practices. These include nonintegral pressure compartments, ball-jointed links to distribute applied loads without restraining the thermal expansion, and material selections based on thermal compatibility.
Document ID
19770042892
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Taylor, A. H.
(Vought Hampton Technical Center Hampton, Va., United States)
Jackson, L. R.
(NASA Langley Research Center Hypersonic Aerodynamics Branch, Hampton, Va., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1977
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 77-392
Meeting Information
Meeting: Conference on Structures, Structural Dynamics and Materials
Location: San Diego, CA
Country: US
Start Date: March 21, 1977
End Date: March 23, 1977
Accession Number
77A25744
Distribution Limits
Public
Copyright
Other

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