复合调节固冲发动机控制方法研究（英文）  

Study on control method of compound adjustable ducted rocket

作　　者：邵明玉[1] 王志刚[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2016年第1期1-8,16,共9页Journal of Solid Rocket Technology

基　　金：National Natural Science Foundation of China(61104195)

摘　　要：基于复合调节固冲发动机非线性动力学模型,对发动机在气道/燃气发生器/喷管调节下的响应进行了分析。在此基础上,提出采用进气道调节提高其所保有的最佳性能,利用燃气发生器/喷管调节控制发动机推力和补燃室工作压力。控制系统设计中,采用INA方法削弱推力回路和补燃室工作压力回路间的耦合,采用频域信息融合方法构造没有非最小相位特性的反馈变量,并设计PI控制器。非线性仿真结果表明,文中所设计的控制器能对复合调节固冲发动机实现有效控制。The responses of compound-adjustable ducted-rocket to inlet / gas generator / nozzle adjustments were studied with nonlinear dynamic model. On this basis,the control strategy was proposed to improve critical total-pressure recovery by inlet adjustment and controlling thrust / afterburner pressure by gas-generator / nozzle adjustments. In design of control system,the coupling characteristic between thrust and afterburner pressure loops was weakened by INA method,while feedback variables without non-minimum phase characteristic were constructed by information fusion in frequency domain,then PI controllers were designed. The nonlinear simulation results of control system show that the controllers are effective in compound-adjustable control.

关 键 词：固冲发动机 复合调节 控制方法 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]