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声爆精确预测及低声爆设计方法已成为新一代军民用超声速飞机研制过程中必须解决的关键难题之一。将改进后的SGD(Seebass-George-Darden)反设计方法、声爆预测算法与遗传算法相结合,形成低声爆布局混合优化方法,利用遗传算法对SGD参数进行优化,得到具有较低声爆超压值和较大有效容积的等效截面积分布,进而得到低声爆布局方案。构建了低声爆混合优化设计环境,可以对方案的声爆水平、感觉噪声级、机体有效容积以及等效截面积分布等进行计算分析,在总体设计阶段具有较高的工程实用价值。优化后的方案采用连翼布局,钝形机头设计,优化后方案的声爆超压值降低了14.51%,机体有效容积增加了15.08%。由于尾部激波强度的不同,地面声爆感觉噪声级随滚转角的变化呈现先变小、后变大、再变小的趋势,对于尾部声爆波形还需进一步优化研究,以降低感觉噪声级。
The precise prediction of sound explosion and the design method of low sound explosion have become one of the key problems that must be solved in the development of a new generation of military and civilian supersonic aircraft. The modified SGD (Seebass-George-Darden) inverse design method, sound explosion prediction algorithm and genetic algorithm are combined to form a hybrid method of low sound explosion layout. The SGD parameters are optimized by using genetic algorithm, Overpressure value and the effective cross-sectional area of larger effective volume distribution, and then get a low sound burst layout scheme. The optimal design environment of low-sound-explosion mixing is constructed, which can be used to calculate and analyze the sound explosion level, the perceived noise level, the effective volume of the airframe and the distribution of the equivalent cross-sectional area. It has high engineering practical value in the overall design stage. The optimized scheme adopts the wing layout, blunt head design, the sound pressure explosion overpressure value of the optimized scheme is reduced by 14.51%, and the effective body volume is increased by 15.08%. Due to the different intensities of the tail shocks, the sensory noise level of the ground sound explosions decreases first, then becomes larger and then decreases with the change of the roll angle. For the tail sonic waveforms, further optimization is needed to reduce the perceived noise level .