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针对固体火箭发动机前封头人工脱粘缝隙,设计了二维实验装置,用来模拟发动机点火过程中前封头人工脱粘位置受到点火冲击后的应力-应变情况。同时,采用流固耦合的数值方法,对比计算了实验工况,计算得到人工脱粘根部的应力-应变与实验吻合很好。通过数值研究发现,点火初期燃气对人工脱粘部位的冲击,会引起缝隙内部的压强振荡及装药表面的振动,其幅值取决于脱粘缝隙内的压强传播情况,点火后期振荡趋于消失。人工脱粘的装药表面应力与燃烧室压强基本一致,在尖端出现应力集中,且对于固定形式的人工脱粘,其增大幅值基本固定,与燃烧室压强无关。人工脱粘向壳体圆柱段的延伸,可能会减小应力集中的幅值。人工脱粘的缝隙宽度对脱粘部位的影响很小。
Aiming at the artificial debonding gap of the front head of solid rocket motor, a two-dimensional experimental device was designed to simulate the stress-strain situation after the artificial debonding position of the front head was ignited by ignition in the ignition process of the engine. At the same time, the numerical method of fluid-solid coupling was used to calculate the experimental conditions, and the calculated stress-strain of the artificial debonding root was in good agreement with the experiment. Through numerical research, it is found that the impact of the gas ignited on the artificial debonding site in the initial stage of ignition can cause the pressure oscillation inside the gap and the vibration on the loading surface. The amplitude depends on the pressure propagation in the gap and the oscillation in the late ignition tends to disappear . The artificial surface of the debonded charge is basically the same as the pressure of the combustion chamber, and the stress concentration occurs at the tip. For the artificial form of artificial debonding, the increase amplitude is basically constant, which is independent of the pressure of the combustion chamber. The extension of the artificial debonding to the cylindrical section of the shell may reduce the magnitude of stress concentration. The width of the artificial debonding gap has little effect on the debonding site.