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常用来作为促进爆震形成的Shchelkin螺旋由于流阻较大,对发动机的比冲会造成一定的损失,因此缩短缓燃向爆震转变(Deflagration to Detonation Transition,DDT)增强装置长度,对脉冲爆震火箭发动机性能的提高有着重要的意义。通过分析DDT增强段的壁温来判断爆震波的形成位置,并通过压力信号来验证。实验结果表明,DDT增强段的壁温沿轴向分布为先增加,然后保持不变,轴向温度会有一个明显的转折点;经过实验验证,壁温的转折点即为爆震波的形成位置。
The Shchelkin spiral, which is commonly used to promote detonation, has a certain loss of specific impulse to the engine because of its large flow resistance. Therefore, the length of the device is shortened to increase the length of the Deflagration to Detonation Transition (DDT) Shock rocket engine performance improvement is of great significance. The location of the detonation wave is determined by analyzing the wall temperature of the DDT enhancement section and verified by the pressure signal. The experimental results show that the axial temperature of the DDT reinforcement increases first and then remains unchanged, and there is a significant turning point in the axial temperature. The experimental results show that the turning point of the wall temperature is the formation position of the detonation wave.