载人登月主动力——大推力液氧煤油发动机研究  

Research on High Thrust LOX/ Kerosene Rocket Engine As Main Power System of Manned Lunar Project

作　　者：李斌[1] 栾希亭[1] 张小平[1] 

机构地区：[1]西安航天动力研究所

出　　处：《载人航天》2011年第1期28-33,共6页Manned Spaceflight

摘　　要：大推力液氧煤油发动机是航天运载主动力的发展方向,是载人登月等重大航天活动的动力基础。提出了我国载人登月主动力—600吨级双推力室液氧煤油发动机的发展设想,并提出了该发动机补燃循环、泵后摇摆等总体方案,选择了发动机主要参数,进行了总体布局设计,梳理了关键技术,探讨了其用途。这将大幅提升我国进入空间的能力,以满足我国载人登月和深空探测等重大航天活动的动力需求。High thrust LOX/Kerosene rocket engine is not only the development orientation of aerospace main power system, but also the power foundation of important aerospace activities such as manned lunar project. The development scheme of 600t high thrust LOX/Kerosene rocket engine with two thrust chambers as main power system for China manned lunar project is proposed, and the general design of staged combustion cycle and swinging after pump is provided. The main parameters of the engine, the assembly configuration, the key technologies and the future utilization of the engine are presented also. The new engine will greatly improve the launching capability of China, and will ultimately meet the requirements of future space activities such as manned lunar project and deep space explorations.

关 键 词：载人登月 液体火箭发动机液氧煤油 补燃循环 泵后摇摆 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]