Hybrid optimization approach research for low sonic boom supersonic aircraft configuration

High fidelity sonic boom prediction and low sonic boom design methods are key technologies of next generation supersonic aircraft. By coupling a modified SGD (Seebass-George-Darden) method, a high fidelity sonic boom prediction method and a Pareto genetic algorithm, a hybrid optimizing approach is developed. The parameters of the SGD method are optimized and an equivalent area distribution with a lower sonic boom overpressure and large available volume can be obtained. By using the optimized equivalent area distribution, a low boom layout can be designed. A low sonic boom configuration mixed optimizing environment is developed, which integrates sonic boom analysis, perceived loudness analysis, available volume calculation and equivalent area distribution generation. The low sonic boom configuration mixed optimizing environment can be used in the conceptual design phase. The optimized layout is a joint wing configuration with a blunt nose. The sonic boom overpressure decreases by 14.51% and the available volume increases nearly 15.08%. Due to the different strengths of the after shock wave, the relationship between the PLdB and roll angle is complex. The after shock of the sonic boom should be optimized in future work for mitigating PLdB.