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.
出处
《火箭推进》
CAS
2015年第3期93-97,共5页
Journal of Rocket Propulsion
