Abstract: To overcome the shortcomings of the multidisciplinary feasible method, approximate models based on the response surface method are used in system analysis so as to reduce the amount of computation. This scheme is applied to the multiple objective optimization for a tailless unmanned aerial vehicle with multiple flaps to derive the integral optimal design of the control effectors’geometry parameters and the fullenvelope flight control law. The design of experiment method and radial basis function neural network response surface method are used to set up approximate models for the control effectors’aerodynamic effect and the control discipline. A set of Pareto solvers are obtained by applying the multiple objective genetic algorithm. One solver among them is chosen by applying fuzzy decision technique, which is the start point for further optimization with the mathematical programming method. The simulation result shows that the proposed method is feasible and effective.

Key words: multidisciplinary design optimization, control effector, flight control system, response surface, fuzzy decision, multi-objective optimization