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.
出处
《载人航天》
CSCD
2011年第1期28-33,共6页
Manned Spaceflight
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
Manned Lunar Project
Liquid Propellant Rocket Engine
LOX/Kerosene
Staged Combustion Cycle
Swinging after Pump
