关键词: 固体推进剂吸气式涡轮火箭发动机;控制规律;特性计算;双变量控制

Abstract: 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.

Key words: Solid propellant air-turbo-rocket(SPATR);Control law;Characteristics computation;Bivariate control