一种载人航天器气压控制系统仿真模型  

Simulation Model for Air Pressure Control System of Manned Spacecraft

作　　者：靳健[1] 杨晨[1] 侯永青[1] 

机构地区：[1]中国空间技术研究院载人航天总体部,北京100094

出　　处：《航天器工程》2015年第3期51-57,共7页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：为支持航天员在轨驻留,载人航天器须利用气压控制系统将密封舱内的氧分压和总压控制在指标范围内。为分析气压控制系统的工作性能,文章提出了一种气压控制系统仿真模型,利用关键参数和主要特性描述公式对气压控制系统的主要要素进行定义,形成了密封舱、航天员、供氧组件、供氮组件、舱体漏孔等的数学模型,并定义了要素之间的接口关系。将正常模式和舱体泄漏模式下的仿真模型计算结果与载人航天器相关地面试验数据进行对比,证明了仿真模型的正确性。最后,利用仿真模型分析了舱体容积和漏孔通径大小对密封舱氧分压和总压变化趋势的影响。In order to support crew resides, oxygen partial pressure and total pressure of pressurized cabin in manned spacecraft should be controlled within a specific range by using air pressure control system. In order to analyze the working performance of air pressure control system, a simulation model is proposed. The air pressure control system are defined by the equations describing key parameters and characteristics, and a mathematic model is developed, including pressurized cabin, crew, oxygen makeup assemble, nitrogen makeup assemble, leaking throat on cabin wall and interface relation between modules. By comparing calculating results of normal mode and leaking mode with ground experiment results of manned spacecraft, the veracity of the model is proved. By using this model, the effects of the pressurized cabin volume and diameter of the leaking orifice on varying trend of oxygen partial pressure and total pressure are analyzed.

关 键 词：载人航天器 密封舱 氧分压 总压 

分 类 号：V444.2[航空宇航科学与技术—飞行器设计]