近空间飞行器推进系统研究  

The Study on Propulsion System of Near Space Vehicle

作　　者：唐家鹏[1] 关世玺[1] 凌桂龙[2] 段娜[2] 

机构地区：[1]中北大学机电工程学院,太原030051 [2]北京航空航天大学宇航学院,北京100083

出　　处：《弹箭与制导学报》2009年第3期145-148,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：根据给定的飞行参数指标,建立了近空间飞行器的设计仿真模型和弹道模型。以余氧系数为变量参数,对其使用的双组元液体推进剂进行了分析和选择,并对泵压式和挤压式两种推进系统方案进行了比较研究。研究结果表明,选择过氧化氢/煤油作为组合推进剂比较合理,泵压式推进系统方案要优于挤压式推进系统方案。研究结果可为其它同类近空间飞行器的推进系统研究提供借鉴和依据。Based on the given flight specifications, the simulation model and orbit model of a near space operations vehicle were established. Making excess oxygen coefficient as variable parameter, bipropellant was selected and analyzed. The turbopump-feed and pressure-fed propulsion systems were compared and conclusions were obtained. The study can be a guidance for propwlsion system research other near space vehicles.

关 键 词：推进系统 液体火箭发动机 近空间飞行器 双组元推进剂 

分 类 号：V433[航空宇航科学与技术—航空宇航推进理论与工程]