超声速飞行器低声爆气动布局优化设计研究

Optimization design research on low sonic boom configuration for supersonic transport

降低声爆噪声水平是未来超声速运输机取得商业成功所必须解决的关键问题之一。针对超声速飞行器声爆噪声预测与控制,建立了基于超声速线化理论及波形参数法的声爆噪声计算方法,与标模lm1021试验结果符合较好,验证了预测方法的可靠性。开展了低声爆气动布局优化设计研究。首先计算了某公务机基本布局的声爆水平并分析了声爆形成原因,在此基础上采用遗传算法分别对机身和机翼平面形状进行了低声爆优化。经过优化后的飞行器布局声爆水平大大降低,地面声爆过压降低了41%,声爆A计权声级降低了7.55dB。同时,采用CFD对优化布局气动力特性进行了计算分析,结果表明在巡航状态下阻力明显降低,而力矩特性基本没有变化。

The reduction of sonic boom noise level is one of the most important problems that must be resolved to get the commercial success in the future.For the sonic boom noise prediction and control of supersonic flight vehicle,the sonic boom noise level prediction methods based on supersonic linear theory and waveform parameter method were developed.The prediction results agreed well with the experiment results of the lm1021,thus the reliability of the prediction methods were validated.The low sonic boom configuration optimizations were researched.The sonic boom level of a basic configuration of supersonic business jet was computed,and the cause of sonic boom formation was analyzed.Based on the results and the analysis,the fuselage and wing planform were optimized separately to decrease the noise level of sonic boom.Compared with the basic configuration,the sonic boom level of optimized configuration decreased distinctively.The overpressure decreased 41%,and the A-weighted noise level decreased 7.55 dB.The aerodynamic characteristics of optimized configuration were computed by computational fluid dynamics(CFD).Compared with the basic configuration,the drag decreased significantly at the cruise condition,while the moment almost unchanged.