Aeroelastic model design using parameter identification
摘要
Wind-tunnel model design can be very involved, so an approach has been developed that uses optimization methods to automate it. The model design process has been divided into separate stiffness design and mass design stages. Then, a sample structure was manufactured and subjected to static and modal testing using laser holographic techniques. The predicted flutter response of the model matches the predicted flutter response of the full-scale wing very closely. Nomenclature c = element of calculated flexibility matrix F = objective function g = constraint K = stiffness matrix k = proportionality constant M = mass matrix m = total mass x = element of eigenvector matrix 8 = element of target flexibility matrix a) = natural frequency
引用本文（GB/T 7714）
Mark French, F. Eastep. Aeroelastic model design using parameter identification[J]. Journal of Aircraft, 1996.
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