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建立了用于控制规律研究的单变量控制和双变量控制的固体推进剂吸气式涡轮火箭发动机(SPATR)特性计算模型,并编制了相应的计算程序。计算模型中采用了以试验数据为基础的燃烧室出口总温计算方法。利用程序分别计算了燃气流量不可调、燃气流量可调、尾喷管喉部面积可调以及燃气流量和尾喷管均可调的不同控制规律的SPATR发动机速度特性,并分析了其特点。对SPATR发动机进行了双变量控制规律设计,得到了相应的燃气流量调节比和尾喷管喉部面积调节比。计算结果表明,按照所设计的双变量控制规律进行控制,SPATR具有很宽的飞行包线和更好的推力特性和比冲特性。
The calculation model of solid propellant aspirated turbo rocket engine (SPATR) with single variable control and bivariate control was established and the corresponding calculation program was established. The calculation model uses the calculation method of the total temperature of the combustion chamber outlet based on the experimental data. The SPATR engine speed characteristics with non-adjustable gas flow rate, adjustable gas flow rate, adjustable throat area of tail nozzle, and adjustable control of gas flow rate and tail nozzle were calculated respectively by using the program. The characteristics of SPATR engine were analyzed. The design of SPATR engine with double-variable control was carried out, and the corresponding adjustment ratio of gas flow rate and throat area of tail nozzle was obtained. The calculation results show that SPATR has a wide flight envelope and better thrust characteristics and specific impulse characteristics according to the designed bivariate control law.