Buckling Behavior of Rene 41 Tubular Panels for a Hypersonic Aircraft Wing

Ko, William L. and Shideler, John L. and Fields, Roger A. (1986) Buckling Behavior of Rene 41 Tubular Panels for a Hypersonic Aircraft Wing. Technical Report NASA TM-86798, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

The buckling characteristics of Rene 41 tubular panels for a hypersonic aircraft wing were investigated. The panels were repeatedly tested for buckling characteristics using a hypersonic wing test structure and a universal tension/compression testing machine. The nondestructive buckling tests were carried out under different combined load conditions and in different temperature environments. The force/stiffness technique was used to determine the buckling loads of the panels. In spite of some data scattering, resulting from large extrapolations of the data-fitting curve (because of the termination of applied loads at relatively low percentages of the buckling loads), the overall test data correlate fairly well with theoretically predicted buckling interaction curves. Also, the structural efficiency of the tubular panels was found to be slightly higher than that of beaded panels.

EPrint Type:	NASA Technical Memorandum
Keywords:	Buckling interaction curves, Force/stiffness method, Hypersonic aircraft wing, Nondestructive buckling tests, Rene 41 tubular panels
Subjects:	(31 - 39) Engineering: (39) Structural Mechanics
ID Code:	535
Deposited On:	25 January 2006
Additional Information:	31 pages. Prepared as AIAA-86-0978 for presentation at the AIAA/ASME/ASCE/AHS 27th Structures, Structural Dynamics and Materials Conference, San Antonio, Texas, May 19-21, 1986.