基于PLC和WinCC的火箭发动机热真空试验控制系统  

Control system for liquid rocket engine heat-vacuum test based on PLC and WinCC

作　　者：沈传兵[1] 苏杭[1] 朱子勇[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《火箭推进》2015年第3期93-97,共5页Journal of Rocket Propulsion

摘　　要：为了验证液体火箭发动机热防护和热管理措施的合理性和有效性,模拟飞行程序全过程,考核发动机及各组合件在热真空环境下的适应性能,需要搭建热真空试验平台。试验要求考核发动机五个关键部位的试验性能,各个部位的热流值是一个随着时间变化的参数。介绍了热真空试验平台控制系统模拟真空环境及温度环境的要求、技术途径和调试过程。控制系统采用PLC和WinCC组态软件,调节模拟装置的输出功率,达到需要的热流条件;采用真空泵抽真空方式使发动机的环境压力接近真空,各项指标符合试验要求。To validate rationality and reliability of heat protection and heat management measure for liquid rocket engine, a platform of thermal vacuum test is needed to be constructed to simulate the entire process of the flight program, and examine adaptability of rocket engine and each subassembly under the condition of thermal vacuum. The requirements, technological approaches and debugging process that the control system of heat-vacuum test platform simulates vacuum and heat environments are introduced. The PLC and WinCC configuration software are adopted in the control system to adjust the output power of the simulation device to meet the needed heat flow condition. The vacuum pump is used to make the environment pressure of the engine close to vacuum, and each index accord with the test request.

关 键 词：热真空试验 PLC 火箭发动机 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]