摘要
对以脉冲方式工作的空间姿控、末修用液体火箭发动机系统的动态特性进行数值仿真分析,并与热试车实验数据进行了比较,还讨论了多推力室动力系统在不同数量、不同类型推力室点火工作时推力响应的特点。
A numerical model is developed to simulate the transient processes of a pulsatingengine system with multiple thrust chambers. The simulating result of working processes of a spaceengine system shows that, for different numbers, or types of working thrust chambers, single thrustchamber has different response characteristics. And, the comparison between testing data andsimulating results of the same rocket engines shows the correctness of this model.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1997年第3期20-23,共4页
Journal of Propulsion Technology
关键词
姿控火箭发动机
推力控制
动态特性
数值仿真
Attitude control rocket engine, Thrust control, Dynamic response, Numerical simulation
