固体推进剂吸气式涡轮发动机控制规律与特性

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。

Control law and characteristics of solid propellant air-turbo-rocket

Mathematical model was set to study the control law and characteristics of solid propellant air-turbo-rocket(SPATR) with single and two control parameters,and the computational program based on the model was developed.In the mathematical model the total temperature of combustor exit is calculated based on interpolation of the experimental data.The velocity characteristics of SPATR with different control laws were computed in four cases which are the gas flow mass in turbine inlet is constant,the gas flow mass in turbine inlet is adjustable,the throat area of nozzle is adjustable and both the gas flow mass in turbine inlet and the throat area of nozzle are adjustable,respectively.The bivariate control law of SPATR was designed,and the adjusted ratio of gas flow mass in turbine inlet and the throat area of nozzle were obtained.Computational results show that SPATR has a wide flight envelope and better characteristics with the bivariate control law.