Thermal-Structural Panel Buckling Tests

Thompson, Randolph C. and Richards, W. Lance (1991) Thermal-Structural Panel Buckling Tests. Technical Report NASA TM-104243, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

The buckling characteristics of a titanium matrix composite hat-stiffened panel were experimentally examined for various combinations of thermal and mechanical loads. Panel failure was prevented by maintaining the applied loads below real-time critical buckling predictions. The test techniques used to apply the loads, minimize boundary effects, and predict the panel response at high temperatures are presented. Experimentally predicted buckling loads have been shown to compare well with a finite-element buckling analysis for previous panels. Comparisons between test predictions and analysis for this panel are ongoing.

EPrint Type:	NASA Technical Memorandum
Keywords:	Buckling, Composite structures, Elevated temperatures, Finite element method, Force/stiffness, Hat-stiffened panel, Hypersonic vehicle, Load tests, Metal matrix composite, Panels, Prediction analysis techniques, Spacecraft construction materials, Strain gages, Test techniques, Titanium
Subjects:	(31 - 39) Engineering: (39) Structural Mechanics
ID Code:	335
Deposited On:	01 September 2004
Additional Information:	22 pages. Prepared for presentation at the Society for Experimental Mechanics 1991 Fall Conference on "Structural Testing Technology at High Temperature," Dayton, Ohio, November 4–6, 1991.