钻石背弹翼制导炸弹气动外形的多目标优化方法OA

To meet the demand for long-range standoff precision strikes by guided bombs,the diamondback wing guided bomb has become a research hotspot due to its excellent gliding range extension capability.To address the issues of numerous configuration parameters and strong aerodynamic coupling between the front and rear wings of the diamondback wing,an efficient multi-objective aerodynamic shape optimization method is proposed.A parametric geometry model of the bomb body,front and rear folding wings,and tail rudders is established.The front wing sweep angle,the distance between the front and rear wing roots,the wing half-span,and the tail rudder half-span are selected as design variables.With the lift-to-drag ratio and static stability margin as optimization objectives,the non-dominated sorting genetic algorithm-II(NSGA-II)is employed to obtain the Pareto solution set,and a decision function is utilized to determine the overall optimal configuration.During the optimization process,aerodynamic calculations are performed using Missile DATCOM and Fluent to construct design samples.On this basis,the multivariate adaptive regression splines(MARS)method is utilized to establish a low-fidelity global trend model,and the Kriging method is applied to correct local errors using high-fidelity data,thereby forming a multi-fidelity surrogate model.Numerical simulation results demonstrate that under the design conditions of Ma=0.9 and α=4°,compared to the baseline configuration,the lift-to-drag ratio of the optimized shape increases from 4.448 to 7.278,achieving an improvement of approximately 63.6%.The static stability margin increases from 2.5%to 5.3%,and the maximum gliding range extends from 55.72 km to 91.13 km,an increase of about 67%.The optimization method and framework proposed in this paper provide theoretical and methodological references for the configuration design of diamondback wing extended-range munitions.