液体火箭发动机试验推力校准控制系统的设计  

Design of Controlling System on Thrust Calibration of Rocket Engine on Test

作　　者：朱子环[1] 耿卫国[1] 陈锋[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《计算机测量与控制》2008年第11期1575-1577,共3页Computer Measurement &Control

摘　　要：文中主要介绍了液体火箭发动机试验推力校准控制系统的工作原理、硬件和软件设计;硬件主要由工业控制计算机中控制卡驱动伺服电机,通过高精度仪表RS232串口实现对传感器信号采集,能很好地实现定点稳定,控制算法采用模糊控制,克服了复杂的外界条件难以确定控制表达式的因素,软件通过VB6.0语言编写界面友好,可操作性强;该系统实现推力校准的远距离控制,提高校准精度、效率和安全性,常温校准结果可达到0.05%。The paper describes the work principle, the hardware and software design of the controlling system, and gives the result of the calibration. Hardware is made of the servo electromotor drived by the controlling card of PC, the sensor sign is collected by serial port of highly precision instrument throught PC, method can realize the loating stability; controlling arithmetic adopts fuzzy control, it over- comes some factors made by environment that can＇t establish controlling expression, software compiled by VB 6.0 has the interface friendly and the operation highly. The system implements remote control and improves calibration accuracy . efficiency and security. The result of thrust calibration in normal temperature attains 0.05%.

关 键 词：火箭发动机 推力 校准 控制系统 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]