固体火箭冲压发动机燃气发生器及燃气流量调节阀建模及仿真  

Modeling and simulation on the gas generator and gas control valve of solid ducted rockets

作　　者：鲍文[1] 牛文玉[1] 陈林泉[2] 于达仁[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001 [2]中国航天科技集团公司四院四十一所,固体火箭发动机燃烧、热机构与内流场国防科技重点实验室,西安710025

出　　处：《固体火箭技术》2008年第6期569-574,共6页Journal of Solid Rocket Technology

摘　　要：研究了一种气动式的燃气流量调节阀,并建立了固体火箭冲压发动机燃气发生器和气动式燃气流量调节阀的数学模型及仿真模型,对燃气流量调节阀仿真模型进行了试验验证,动态误差和稳态误差都在5%以内。通过仿真获得了燃气发生器和燃气调节阀的动态响应特性。仿真结果表明,燃气调节系统开环响应速度较慢,并具有很强的非线性。A kind of pneumatic gas control valve was investigated. The mathematical model and simulation model for the gas generator and pneumatic gas control valve of solid ducted rockets were established. Moreover the model of gas control valve was verified in tests, with the dynamic error and the steady-state error within 5 %. Finally the dynamic response performance of the gas generator and gas control valve were obtained through simulation. The simulation results show that the gas adjusting system openloop responses slowly with strong nonlinearity.

关 键 词：固体火箭冲压发动机 燃气发生器 燃气流量调节阀 数学模型 仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]