微推进系统的轨控发动机动态分析  

Transient Analysis of a Divert Thruster for Micropropulsion Systems

作　　者：张国舟[1] 

机构地区：[1]北京航空航天大学宇航学院

出　　处：《北京航空航天大学学报》1999年第6期688-691,共4页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：近年来液体火箭推进系统的小型化有了极大的进展，这些先进的微推进系统是以尺寸小微型化、高压和响应快为特征的，对于这种微推进系统，推导、编制了系统各部件的数学模型，分析研究了轨控发动机在单脉冲工作进程中燃烧室压力和关机过程中推进剂阀门前压力的变化规律．为研究整个微推进系统的动态响应打下基础．In the past several years, the miniaturization of Liquid Rocket Propulsion Systems advanced tremendously. The advanced micropropulsion systems are characterized by the miniaturization, high pressure and fast response. For these micropropulsion systems, the mathematical models of components are derived and gathered together. For the divert thruster of micropropulsion system, the variation of the combustion chamber pressure during impulse working and the pressure variation during closing the divert valve are investigated and analysed. It provides a basis for research of the dynamic response of the whole micropropulsion system.

关 键 词：小推力推进 液体火箭发动机 动态响应 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]