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为了研究高室压脉冲火箭发动机的工作特性,在分析其工作原理的基础上建立了数学模型,其中燃烧室和挤压腔采用零维模型,喷管采用一维准稳态模型,采用四阶Runge-Kutta法进行了求解.结果表明,燃烧室的最大压强和平均压强都高于推进剂供给压强,而挤压过程中进出燃烧室的质量不守恒是压强升高的原因.与常规液体火箭发动机相比较表明,脉冲火箭发动机的真空比冲提高了7.5%,而喉部面积仅为其10.2%.
In order to study the operating characteristics of high pressure pulse rocket engine, based on the analysis of its working principle, a mathematical model was established, in which the zero-dimensional model was adopted in the combustion chamber and the extrusion chamber, the one-dimensional quasi-steady state model was adopted for the nozzle, Runge-Kutta method.The results show that the maximum pressure and the average pressure of the combustion chamber are higher than the pressure of the propellant, and the non-conservation of mass entering and exiting the combustion chamber is the reason of the pressure increase.Compared with the conventional liquid rockets The engine comparison shows that the pulse rocket engine vacuum ratio increased by 7.5%, while the throat area was only 10.2%.