An Application of Finite Element Methods to Panel Flutter Optimization

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Report Number: AFFDL TR 71-160 p. 537-556
Author(s): Weisshaar, Terry A.
Corporate Author(s): University of Maryland
Date of Publication: 1973-12
Pages: 20
DoD Task:
Identifier: This paper is part of a conference proceedings. See AD0785968

This paper presents the results of an aeroelastic optimization study. The weight of a panel in high Mach number supersonic flow is minimized subject to the requirement that the critical aerodynamic parameter for flutter be held within prescribed limits. Panel equilibrium is described with finite element techniques. The study shows that finite element techniques, when used together with standard optimization methods, yield accurate results to this difficult problem. The numerical results of the investigation are compared to other converged numerical results to illustrate accuracy. The optimization mechanism itself is studied and discussed to provide qualitative results which may be applied to other aeroelastic optimization problems. The results of the paper show that, with an effective finite element model, weight savings and mass distributions found with finite element methods are comparable to those found by more complicated methods.

Provenance: Bombardier/Aero

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