Robust design optimization method for aircraft

The robustness problem in the aircraft design optimization is discussed in reference to the undulation of aircraft performance derived from uncertainty factors. A new robust design optimization (RDO) model, the constrained condition method (CCM), is expounded perspicuously. By dint of genetic algorithm (GA) joining with Back Propagation neural networks response surface (BP-NNRS), two optimal schemes, so called RDO scheme and non robust design optimization (NRDO) scheme, different in the fact whether or not robustness is taken into account, are respectively obtained for three dimension wing in aerodynamic. The cruising speed is regarded as the interference factor in RDO. It is suggested in the results that the maximum lift-drag ratios at cruising speed of both two schemes are higher than that of the original scheme. Though the maximum lift-drag ratio of the RDO scheme is 0.0231 lower than that of the NRDO scheme, the variation of it of the RDO scheme is 0.02559 less than that of the NRDO scheme within the range of the Mach number. The lift coefficient and the drag coefficient of the RDO scheme also vary much less sharply than that of the NRDO scheme. Therefore the RDO method in this paper is verified useful and efficient.