液体火箭发动机起动过程减损控制研究  

Research of damage-mitigating control for startup process of liquid-propellant rocket engines

作　　者：魏鹏飞[1] 吴建军[1] 陈启智[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《火箭推进》2006年第1期7-13,共7页Journal of Rocket Propulsion

基　　金：国家自然科学基金资助项目（50276068）.

摘　　要：为了控制液体火箭发动机起动过程中故障的发展,以便提高发动机的可靠性与安全性,在其关键部件损伤与系统性能之间折衷考虑,实施减损控制。提出一种以减小部件损伤为目的的发动机开环控制结构,并对其所涉及的相关模型作了简短的分析;通过综合分析减损控制律,可对控制输入序列进行优化选择。仿真研究了某火箭发动机起动过程实施减损控制后的两个实例,结果表明通过减损控制,可以实现在系统性能不明显损失的情况下,较大幅度地减小关键部件损伤。A goal of this paper is that evolution of the critical component fault is controlled so that the reliability and security of the liquid propellant rocket engine （LRE） are improved. The tradeoff between the dynamic performance and the critical component damage is considered to implement the damage mitigating control （DMC）. This paper presents an open loop control structure to reduce damage of the critical components of the LRE. The related models in the DMC for LREs are analyzed. To select a suitable control input sequence, the DMC law is analyzed and synthesized. During the startup process of a certain kind of LRE, the two cases which adopt the DMC are simulated. Results indicate that substantial decrease in the damage of critical system components can be achieved by insignificant loss of the system dynamic performance.

关 键 词：液体推进剂火箭发动机 起动过程 减损控制 控制输入 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]