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为了改善采用液态燃料的脉冲爆震火箭发动机内部燃料的雾化以及燃料混合物的掺混状况,采用了一种中心锥体结构.该结构发动机不采用Shchelkin螺旋增爆装置,而采用中心锥体结构、二级供应方式.采用航空煤油为燃料、压缩氧气为氧化剂、压缩氮气为隔离气体,在该结构脉冲爆震火箭发动机上获得了充分发展的爆震波并且能够在多循环条件下稳定工作.实验结果表明,该结构可以大大缩短DDT(deflagra-tion to detonation transition)距离,在实验条件下爆燃向爆震转变距离约为管径的5倍.较之同一管径采用Shchelkin螺旋增爆装置的脉冲爆震火箭发动机,该结构发动机的爆燃向爆震转变距离缩短了57.5%.
In order to improve the atomization of the fuel in the pulse detonation rocket engine with liquid fuel and the blending of the fuel mixture, a central cone structure is adopted, which adopts the Shchelkin spiral explosion device instead of the central cone structure , Secondary supply.Using aviation kerosene as fuel, compressed oxygen as oxidant and compressed nitrogen as isolation gas, a fully developed detonation wave was obtained on the pulse detonation rocket engine and was able to work stably under multi-cycle conditions. The results show that the structure can greatly shorten the distance from the deflagration to detonation transition (DDT), and the transition distance from detonation to detonation under the experimental conditions is about 5 times of the diameter of the tube.Compared with the same diameter, the pulse of the Shchelkin spiral explosion device Detonation rocket engine, the structure of the engine detonation knock to shorten the conversion distance of 57.5%.