INTEGRATED AEROSERVOELASTIC WING SYNTHESIS BY NONLINEAR-PROGRAMMING APPROXIMATION CONCEPTS

Nonlinear programming/approximation concepts optimization techniques developed for structural synthesis are adapted to the integrated aeroservoelastic wing synthesis problem, in which constraints from several disciplines are taken into account simultaneously and the design space includes structural and control system design variables. Structural, aerodynamic, and control system mathematical models that are suitable for the preliminary design of airplanes are used in an integrated synthesis of wings and their active control systems. The effectiveness and efficiency of the new capability are studied using mathematical models of a remotely piloted vehicle as well as a more complex YF16-type airplane model. Simplified handling quality constraints are added to the set of design requirements. The performance of several complex eigenvalue approximations is examined. Effects of control law structure on the weight and robustness of the resulting aeroservoelastic designs provide new insights into the complex multidisciplinary interactions involved.