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
1966
8 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
NTIS | 1987
|NTIS | 1994
|AIAA | 1992
|