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目前空天飞行器用的火箭冲压组合发动机尚有很多技术问题没有解决。其中之一是吸入发动机的空气密度随飞行高度有很大变化,为此必须改变推进剂的燃气发生量,即必须有控制空气与燃烧气体混合比的技术。为此探讨了利用推进剂的化学反应特性控制火箭冲压组合发动机燃烧的新原理。根据这一原理提出了变流量型火箭冲压组合发动机,它采用一种能使空气与燃气保持最佳比的机构,从而保证发动机在较宽的高度范围内有效工作。
At present, there are still many technical problems that the rocket-propelled combination engine used in the space vehicle has not been solved. One of them is that the density of the air drawn into the engine varies greatly with the altitude of the flight. Therefore, it is necessary to change the amount of gas generated by the propellant, that is, the technology of controlling the mixing ratio of air to combustion gas. Therefore, a new principle of controlling the combustion of a rocket ramjet engine by using the chemical reaction characteristics of propellants is discussed. Based on this principle, a variable flow rocket ramjet engine is proposed, which uses a mechanism that keeps the air and gas at an optimum ratio to ensure that the engine works efficiently over a wide range of heights.