一种三组元直排塞式喷管发动机系统方案  

A system configuration of tripropellant rocket engine with linear plug nozzle

作　　者：李兵科 沈赤兵[2] 周进[2] 

机构地区：[1]北京丰源机械研究所,北京100076 [2]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2003年第3期228-231,共4页Journal of Propulsion Technology

摘　　要：三组元发动机和塞式喷管发动机均是实现单级入轨的关键技术。针对三组元(液氢、液氧、煤油)直排塞式喷管发动机提出了一套系统结构方案,并对其进行了初步的研究计算。发动机采用泵压式燃气发生器动力循环系统。利用蝶形活门关闭煤油管路、利用可调气蚀管调节氢氧流量转变工况,利用可调气蚀文氏管和涡轮排气进行推力矢量控制。以已有的三组元塞式喷管发动机推力室设计、分析为基础,继承了三组元发动机和塞式喷管的研制成果,是技术先进、性能高、可在短期内实现的新型液体火箭发动机。Tripropellant Liquid Rocket Engine(TLRE) and Liquid Propellant Rocket Engine with Plug Nozzle(LPREPN) are both key technologies for the realization of Single-Stage-To-Orbit(SSTO). A system configuration for the Tripropellant (hydrogen, oxygen and kerosene) Rocket Engine with Linear Plug Nozzle (TRELPN) was presented, and some computational results on it were initially given. This gas generator cycle for pump-fed liquid rocket engine was chosen. The aim of the mode transfer was achieved by using the butterfly-type valve to shut off the kerosene flow and using variable-area-type Venturi tube to alter the hydrogen and oxygen flow-rate, and the thrust vector control was completed by using variable-area-type Venturi tube and the turbine gases. Based on some former design and analysis on TRELPN's thrust chamber, this paper presents a new designed TRELPN with advanced performance which takes achievements of TLRE and LPREPN into account and can be realized in near future.

关 键 词：液体推进剂火箭发动机 三元推进剂 塞式喷管 结构设计 推力向量控制 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程] V511