一种姿轨控发动机地面试验控制系统设计  

Design of a ground test control system for attitude and orbital control engine

作　　者：刘万龙[1] 牛向楠[1] 李全令 韩晓梅[1] 孙树江[1] 

机构地区：[1]北京航天试验技术研究所,北京100074 [2]北京中科泛华测控技术有限公司,北京100192

出　　处：《火箭推进》2015年第2期114-117,122,共5页Journal of Rocket Propulsion

摘　　要：控制系统在试车过程中发出指令信号,使发动机和试车台各工艺系统按照预定的程序完成规定试车任务。为了适应某型号姿轨控发动机试验对控制精度要求的提高,需要对现有控制系统进行改造,基于现场可编程门阵列和高速固态继电器设计了一种新的控制系统,其控制模块用于操作人员对试验系统上的各路电磁阀进行手动与自动控制,其复记模块可以实时记录系统状态以便于指挥人员了解系统工作状况,并能够进行数据分析判断。该系统建成后可以满足该型号姿轨控发动机试验的要求,控制精度为0.1 ms。In the test, the control system gives command signal to make the engine and test process systems complete a predetermined test task according to certain procedures. In order to adapt to the high-accuracy control requirement of a new attitude and orbital control engine, it is necessary to improve the existing control system. Therefore, a new control system was designed based on field programmable gate array and high-speed solid-state relay. Its control module can be used for operators to control various electromagnetic valves in the test system manually and automatically. Its record module can be used to record the status of the system, so that the command staff know the working status of the system. The system can meet the testing requirements of the new attitude and orbital control engine. The control precision is 0. 1 ms.

关 键 词：火箭发动机 地面试验 控制系统 

分 类 号：V433.934[航空宇航科学与技术—航空宇航推进理论与工程]