Predictions of Thermal Buckling Strengths of Hypersonic Aircraft Sandwich Panels Using Minimum Potential Energy and Finite Element Methods

Ko, William L. (1995) Predictions of Thermal Buckling Strengths of Hypersonic Aircraft Sandwich Panels Using Minimum Potential Energy and Finite Element Methods. Technical Report NASA TM-4643, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

Thermal buckling characteristics of hypersonic aircraft sandwich panels of various aspect ratios were investigated. The panel is fastened at its four edges to the substructures under four different edge conditions and is subjected to uniform temperature loading. Minimum potential energy theory and finite element methods were used to calculate the panel buckling temperatures. The two methods gave fairly close buckling temperatures. However, the finite element method gave slightly lower buckling temperatures than those given by the minimum potential energy theory. The reasons for this slight discrepancy in eigensolutions are discussed in detail. In addition, the effect of eigenshifting on the eigenvalue convergence rate is discussed.

EPrint Type:	NASA Technical Memorandum
Keywords:	Different edge conditions, Finite element method, Hypersonics, Minimum potential energy theory, Sandwich panels, Thermal bucklings
Subjects:	Aircraft/Project: Miscellaneous (31 - 39) Engineering: (39) Structural Mechanics
ID Code:	216
Deposited On:	16 July 2004
Additional Information:	54 pages.