基于液体火箭发动机的亚轨道飞行器性能参数分析  

Analysis of the parameter of repetitious air-launch adjacent space aircraft based on liquid rocket engine

作　　者：凌桂龙[1] 张建伟[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2010年第9期2111-2116,共6页Journal of Aerospace Power

摘　　要：针对一种环保推进剂组合,建立了亚轨道飞行器设计仿真模型、质量模型和弹道模型,以燃烧室压强、余氧系数及喷管出口截面压强为分析变量,对亚轨道飞行器的性能进行了分析.所得结论表明:在给定飞行任务下,为提高亚轨道飞行器性能,燃烧室压强越高越有利;最佳余氧系数在0.99处取得;喷管面积扩张比受到箭体外径及工艺水平等限制,在条件允许的情况下,尽量取大.研究结果为其他同类亚轨道飞行器的系统方案研究提供参考.For a environment propellant group,the simulation model,mass model and orbit model of adjacent space aircraft were established.By setting combustion chamber pressure,ample oxygen coefficient and nozzle exit pressure as variables,the performance of adjacent space aircraft was analyzed.The results show that it will be better with higher combustion chamber pressure under specific task for improving adjacent space aircraft performance.The best ample oxygen coefficient can be achieved at 0.99.If permitted,the nozzle area expansion ratio deployed should be as big as possible,since it is limited by rocket outer diameter and technology level,etc.The correlation study could provide a guidance for the system project study of other similar adjacent space aircrafts.

关 键 词：液体火箭发动机 亚轨道飞行器 环保推进剂 燃烧室压强 余氧系数 喷管出口压强 

分 类 号：V435.3[航空宇航科学与技术—航空宇航推进理论与工程]