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A structural design for a hypersonic research aircraftA research aircraft is being studied that has potential for large-scale demonstration of advanced propulsive, structural, and aerodynamic technologies for hypersonic application. Versatility is achieved through a large removable payload bay with removable thermal protection, by removable wings, and by the configuration, which considers engine-airframe integration. Design criteria have been applied to an effective heat-sink structure of Lockalloy (Be-38Al), wherein thermal stress alleviation is a prime consideration in the design. Structural analyses are being performed with the SPAR computer program. Results indicate that no critical problems exist and the resulting structural weight is within initial estimates.
Document ID
19760062425
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jackson, L. R.
(NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)
Taylor, A. H.
(Vought Technical Center Hampton, Va., United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1976
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 76-906
Accession Number
76A45391
Distribution Limits
Public
Copyright
Other

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