摘要
针对膏体推进剂火箭发动机多次点火时间间隔的受限问题,提出了等离子点火方案;根据离子多次点火的工作流程,设计了多次点火系统,并对各个部分组成进行了介绍;在分析了等离子弧的电特性的基础上,详细介绍了控制部分模糊控制原理的设计,实现了整个点火过程的状态识别、控制和检测;同时,进行了MATLAB和半物理实验仿真。结果表明:系统能够满足膏体推进剂火箭发动机多次点火需求,控制性能良好,达到了设计任务。
Aiming at the limited problem of multiple ignition time interval for pasty propellant rocket, plasma ignition plan was proposed. Based on working process of plasma multiple ignitions, multiple igniting system was designed accordingly and each element was analyzed. On the base of electronic performance of plasma arc, the design of fuzzy controller was introduced in detail, and status recognition, control and detection of the whole ignition process was realized. Simulation of Matlab and semi-physical experimental simulation were performed. Results show the system fit the demand of pasty propellant rocket motor multiple igniting, control performance well, and the design was attained.
出处
《火工品》
CAS
CSCD
北大核心
2008年第5期1-5,共5页
Initiators & Pyrotechnics
