并联式固液上面级动力系统研究  

Study on hybrid upper stage propulsion system with parallel structure

作　　者：张爱文[1] 朱浩[1] 蔡国飙[1] 刘勇[2] 李小玉[2] 

机构地区：[1]北京航空航天大学,北京100191 [2]中国科学院国家空间科学中心,北京100190

出　　处：《火箭推进》2016年第6期9-14,共6页Journal of Rocket Propulsion

摘　　要：探索了固液火箭发动机作为上面级动力系统的性能特点;采用气瓶、贮箱和燃烧室并联布局的结构,有效减少了固液火箭发动机的长细比;建立了固液火箭发动机系统设计的数学模型,采用多岛遗传算法,开展了并联式固液火箭发动机总体方案的设计优化;优化结果与某固体火箭发动机上面级的比较说明,固液火箭发动机在上面级动力系统中具有较大的应用潜力。The performance characteristics of the hybrid rocket engine taken as the upper stage propulsion system are explored. The structure of parallel arrangement of gas cylinder, storage tank and combustion chamber is adopted to decrease the slenderness ratio of the hybrid rocket engine. The mathematical model for systemdesign of the hybrid rocket engine is established. The optimization of the overall design scheme is carried out by means of the multi-island genetic algorithm. The optimization result is compared with the performance of a certain solid rocket engine （upper stage propulsion system）. The result shows that the hybrid rocket engine as an upper stage propulsion system has a big application potential.

关 键 词：上面级 固液火箭发动机 系统建模 多岛遗传算法 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]