提出了压气机进口预注冷质的空气涡轮火箭（MIPCCATR）循环，拓展了ATR在高飞行马赫数下的工作能力。给出了基于工质组分的变比热ATR循环热力学建模方法和工质物性改变时对部件特性的修正方法，基于所推导的准无量纲关系式讨论了循环参数之间的相互作用及其对性能的影响。研究结果表明预注冷质不仅能有效拓宽ATR的工作包线，而且可以提高单位推力，所需付出的代价是比冲会有一定程度的降低。
This paper presents the air turbo rocket （ATR） engines using water and oxygen injection and precompressor cooling to enhance performance by increasing flying Ma（h number capability. The engine cycle is simulated and the method to correct compressor characteristics is given, both of which take into account the changing of thermal properties of working fluid due to injected mass. Parametric cycle analysis was performed to obtain interactions of cycle parameters and engine performance based on derived quasi-dimensionless relations. The results demonstrate that preeompressor cooling allows ATR engines to fly to higher Maeh numbers and altitudes with improved specific thrust, however, at the cost of reduced specific impulse.
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