NDLI: Loading tests of a wing structure for a hypersonic aircraft

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Loading tests of a wing structure for a hypersonic aircraft

Content Provider	NASA Technical Reports Server (NTRS)
Author	Reardon, L. F. Siegel, W. H. Fields, R. A.
Copyright Year	1980
Description	Room-temperature loading tests were conducted on a wing structure designed with a beaded panel concept for a Mach 8 hypersonic research airplane. Strain, stress, and deflection data were compared with the results of three finite-element structural analysis computer programs and with design data. The test program data were used to evaluate the structural concept and the methods of analysis used in the design. A force stiffness technique was utilized in conjunction with load conditions which produced various combinations of panel shear and compression loading to determine the failure envelope of the buckling critical beaded panels The force-stiffness data did not result in any predictions of buckling failure. It was, therefore, concluded that the panels were conservatively designed as a result of design constraints and assumptions of panel eccentricities. The analysis programs calculated strains and stresses competently. Comparisons between calculated and measured structural deflections showed good agreement. The test program offered a positive demonstration of the beaded panel concept subjected to room-temperature load conditions.
File Size	2541537
Page Count	73
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19800006809
Archival Resource Key	ark:/13960/t7kq2t85x
Language	English
Publisher Date	1980-01-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Finite Element Method Spot Welds Hypersonic Aircraft Wing Panels Computer Programs Stress-strain Diagrams Load Tests Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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