Abstract:

There is strong coupling between environmental control system and thermal control system of manned spacecraft in terms of heat and material flow. In the design stage, it is necessary to carry out integrated system simulation analysis, so as to predict and verify the system performance. A typical integrated environmental control and thermal control system model of manned spacecraft is built using system modeling and simulation methods, including crew module, air purification module, air supply and pressure regulation module, fluid loop module, etc. The performance of the system is analyzed. The simulation analysis was carried out for the manned flight conditions of three persons in 7 days. The results show that the parameters of temperature, humidity, pressure and oxygen partial pressure in the cabin can be controlled within the requirements of aerospace medical indicators by reasonable design. The simulation results of the environmental control system and thermal control system accurately predict the working process of the system, show the changes of the main parameters, and the results are reasonable, which verify the correctness of the simulation method and the system simulation model. By controlling the opening of the bypass valve in the outer loop of the fluid circuit, the temperature of the control point in the outer loop can be accurately controlled to ensure that the temperature and humidity in the cabin are within a reasonable range. In addition, the setting of temperature control point in the outer loop will affect the state of the environmental control system and thermal control system. By reasonably designing the temperature control point in the outer loop, the temperature and humidity in the cabin can be guaranteed to meet the requirements of aerospace medical indicators. The research results play an important role in the integrated design and optimization of environmental control system and thermal control system.

Key words: manned spacecraft, environment, thermal control, integration, dynamic simulation

摘要：

采用系统建模及仿真方法搭建了一种典型载人航天器环热控一体化系统模型，分析了系统的性能。针对3人7天载人飞行工况开展了仿真分析，结果表明，经过合理设计，该系统可将舱内温湿度、压力、氧分压等参数控制在航天医学指标要求范围内。环热控系统仿真结果较好地预测了系统工作过程，显示了主要参数的变化情况，结果合理，验证了仿真方法、系统仿真模型的正确性。通过控制流体回路外回路旁通阀门开度，可准确控制外回路控温点温度，保证舱内温湿度在合理范围之内。此外，外回路控温点的设定会对环热控系统状态带来影响，通过合理设计外回路控温点，可保证舱内温湿度满足航天医学指标要求。

关键词: 载人航天器, 环境, 热控制, 集成, 动态仿真