膏体推进剂火箭多次点火系统设计与仿真  

Design and Simulation of Multiple Igniting System for Pasty Propellant Rocket

作　　者：周守强[1] 郑亚[2] 鞠玉涛[1] 周超[1] 张家仙[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094 [2]西北工业大学,陕西西安710072

出　　处：《火工品》2008年第5期1-5,共5页Initiators & Pyrotechnics

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.

关 键 词：膏体推进剂火箭 多次点火 等离子 模糊控制 

分 类 号：TJ450.2[兵器科学与技术—火炮、自动武器与弹药工程] V439.7[航空宇航科学与技术—航空宇航推进理论与工程]