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考虑到全尺寸吸气式高超声速飞行器的机体弹性弯曲振动极易被激发,提出了一种包含机体弹性弯曲影响的外喷管建模和分析方法。该方法首先用虚拟激波膨胀波法确定剪切层的位置,然后用影响系数法求解外喷管中的准一维流,并用活塞理论修正后体下表面的压力。用该方法对一个全尺寸吸气式高超声速飞行器的后体/外喷管进行了仿真分析,结果表明,仅考虑低频、小振幅的后体弹性弯曲运动对外喷管性能的影响并不显著。
Considering that the body flexural vibration of a full-size aspirated hypersonic vehicle can be easily excited, a method of modeling and analyzing the outer nozzle including the elastic bending of the body is proposed. In this method, the position of the shear layer is determined by the virtual shock swell wave method. Then the quasi-one-dimensional flow in the outer nozzle is solved by the influence coefficient method, and the pressure on the lower body surface is corrected by the piston theory. The simulation analysis of the rear body / outer nozzle of a full-size aspirated hypersonic vehicle by this method shows that the influence of the low-frequency and small-amplitude rear body flexural bending on the performance of the outer nozzle is not significant.