液体火箭试验控制系统设计及可靠性指标计算  

Design and Reliability Index Computation of Liquid Rocket Test Control System

作　　者：康淑婷[1] 林萌[1] 姬俊峰 KANG Shu-ting;LIN Meng;JI Jun-feng(Beijing Aerospace Test Technology, Insititute, Beijing 100074, China)

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《传感器世界》2018年第6期33-37,共5页Sensor World

摘　　要：当前,试验控制系统大多采用分系统单独控制,导致试验系统的信息化、自动化程度较低。随着大推力液体火箭工程的推进,以及硬件设备的升级换代,试验系统可靠性需要达到更高的水平,特别是多环节、多状态、多参数的少人值守环境。为了有效提高系统的可靠度,设计了一种基于冗余S7-417H PLC的液体火箭试验双机双工并联冗余控制系统,对其硬件、外围保护电路、抗干扰防错软件、冗余以太网方面的措施方法进行说明,并对系统关键设备硬件可靠性指标进行量化计算。At present, most of test control systems are controlled separately by subsystems, which leads to the low degree of automation and information. With the development of large thrust liquid rocket engineering and the upgrading of hardware equipments, the reliability of the test systems must reach a higher level, especially for the applications with less operators in multi-links, multistates and multi-parameters envirment. A dual-machine parallel redundancy control system based on redundant s7-417h PLC for liquid rocket tests is designed in this paper.Some ways to improve system reliability including hardware, peripheral protection circuits, anti-interference and error prevention software, redundant Ethernet are explained. And also, the hardware reliability indexes of the key system equipment are quantified

关 键 词：PLC冗余设计 保护电路 软件防干扰 可靠度计算 

分 类 号：V553.2[航空宇航科学与技术—人机与环境工程]