Abstract
A method for calculating the sensitivities for transonic unsteady aeroelastic constraints with respect to structural design variables (skin thickness, spar thickness, spar cap cross-sectional areas, etc.) is presented. The method requires that the transonic unsteady aerodynamics be represented in the frequency or Laplace domain. This Indicial Response Technique was used to transform time domain aerodynamics found by solving the TSD equations into the Laplace domain. The indicial responses are performed about a static aeroelastic equilibrium found using the TSD equations for the steady aerodynamics. Once in the Laplace domain the unsteady aerodynamics are used to develop semianalytic equations for the constraint sensitivities. These sensitivity equations include a nonlinear term that must be calculated by finite differences at a considerable computational cost. If a static rigid equilibrium is used, this term vanishes producing fully analytic sensitivities. This method of sensitivity calculation will allow formal unsteady aeroelastic optimization in the transonic flight regime. (Author)
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