Box beam simulating dry wing structure of high L/D hypersonic flight vehicle was fabricated and tested under simulated flight conditions; design techniques used to minimize thermal stresses are presented together with experimental results demonstrating structural integrity; structure used brazed honeycomb sandwich skin panels and corrugated plate webs of D-43 columbium and Haynes-25 superalloy; deleterious temperature differences were reduced by combining use of insulation with detail design arrangements; conclusions and review of test results.
Design and testing of hot redundant structure concept for hypersonic flight vehicle
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 5 ; p 685-692
1966
8 pages
Article (Journal)
English
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