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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。
In order to verify the rationality and effectiveness of the thermal protection and thermal management measures of liquid rocket engine, the whole process of flight simulator is simulated to evaluate the adaptability of engine and each assembly in thermal vacuum environment. The test required examination of the performance of the five key parts of the engine, and the heat flow values at various locations were a parameter that varied over time. The requirements, technical approaches and debugging process of simulating vacuum environment and temperature environment of the thermal vacuum test platform control system are introduced. The control system adopts PLC and WinCC configuration software to regulate the output power of the simulation device and achieve the required heat flow conditions. The vacuum pressure of the vacuum pump is used to make the environmental pressure of the engine close to the vacuum, and the indexes meet the test requirements.