A coupled-adjoint aerostructural wing optimization tool has been modified to include the optimization of high-lift devices from the start of the optimization process. The aerostructural tool couples a quasi-three-dimensional method with a finite beam element model. In this paper, the quasi-three-dimensional method is modified using the a method of Van Dam to enable high-lift aerodynamic analysis. In order to estimate the maximum wing lift coefficient of an elastic wing, the Pressure Difference Rule is coupled with the aerostructural tool. The proposed method is able to compute wing drag and maximum wing lift coefficient with reasonable accuracy compared to high-fidelity CFD tools that require much higher computational cost. The coupled systems are solved using the Newton method for iteration. The sensitivities of the outputs of the tool with respect to the input variables are computed through combined use of the chain rule of differentiation, automatic differentiation and coupled-adjoint method. Using the presented tool, a sequential and combined gradient based optimization is performed in order to minimize the fuel weight of a Fokker 100 class aircraft. The combined optimization results in a fuel weight reduction of 4.1% while achieving a maximum wing lift coefficient in both takeoff and landing configuration equal to that of the initial wing.
展开▼
