固体火箭冲压发动机燃气流量调节最优前馈控制  

Research on Optimum Feedforward Control of Gas Flow Regulation of Solid Rocket Ramjet

作　　者：赵泽敏[1] 陈雄[1] 周长省[1] 李宏文 

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]晋西工业集团有限责任公司,太原030027

出　　处：《弹箭与制导学报》2014年第3期109-112,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：总装备部预研基金资助

摘　　要：固体火箭冲压发动机燃气流量调节过程中存在负调节,对正常工作有很大影响。文中根据燃气流量调节小扰动数学模型分析了负调量与调节时间之间存在的矛盾,给出了负调受约束下最小调节时间。然后根据最优响应设计了可实现的最优前馈控制器,建立以内弹道方法为基础的仿真模型。结果表明,该前馈控制方法能够在燃气流量难以测量形成有效反馈控制的实际情况中,实现不同负调约束的最优调节。发动机设计时应根据综合状态折中选择负调量和调节时间。Negative regulation occurring to gas flow adjustment of solid rocket ramjet adversely affects normal operation. In this paper, the inverse relationship between the undershoot and time set was analyzed according to the gas regulating small perturbation dynamic model and the minimum settling time was given subject to undershoot constraint. Then, the optimum feedforward controller was synthesized based on i- deal response, the simulation model was established according to mathematic model of interior ballistic. Numerical simulation results illus- trate the optimum feedforward controller signals achieve minimize the settling time subject to undershoot constraint.

关 键 词：固体火箭冲压发动机 燃气流量调节 负调约束 前馈控制 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]