抄録
This paper investigates the structural optimization of plate wing for supersonic flutter. The analytical sensitivity of the critical dynamic pressure on supersonic flutter is formulated by the theoretical sensitivity analysis. The sensitivity is implemented in the steepest descent method to investigated the performance of the optimization. A delta wing model is considered for a numerical example. The numerical results indicate that the computational cost is reduced and the critical dynamic pressure is improved with respect to the results with the evolutionary structural optimization.
