The invention provides a highly-integrated reusable cold air propulsion system which comprises a gas cylinder, a gas circulation pipeline and a plurality of mounting connectors are arranged on a shell of the gas cylinder, an inflation valve, a self-locking valve, a pressure reducing valve, a safety valve, a pressure sensor and a plurality of cold air engines are mounted on the gas cylinder, the inflation valve is used for inflation, the self-locking valve is used for sealing, and the pressure reducing valve is used for sealing. The pressure reducing valve is used for reducing pressure of high-pressure gas in the gas cylinder, the safety valve is used for releasing pressure, the pressure sensor is used for measuring pressure, and the cool air engine is used for aircraft attitude control. No pipeline or connector is arranged, so that the envelope size of the cold air propulsion system is greatly reduced; due to the highly integrated design, the air cylinder is fixedly connected with the cabin body only through gas cylinder equator radial constraint and gas cylinder shell upper end face axial constraint, other assemblies are all internal connectors, and the cold air propelling system has very good mechanical environment adaptability; after a sounding rocket and a small carrier rocket are recycled, the cold air propelling system can be reused, and the rocket launching cost is reduced.
本发明提供了一种高度集成可重复使用的冷气推进系统,包括气瓶,气瓶的壳体上设置有气体流通管道及多个安装接口,气瓶上安装有充气阀、自锁阀、减压阀、安全阀、压力传感器以及多台冷气发动机,充气阀用于充气,自锁阀用于密封,减压阀用于气瓶内高压气体减压,安全阀用于泄压,压力传感器用于测量压力,冷气发动机用于飞行器姿态控制。本发明没有管路和接头,大幅减小冷气推进系统包络尺寸;高度集成化设计,仅通过气瓶赤道径向约束和气瓶壳体上端面轴向约束与舱体连接固定,其他组件均为内部接口,冷气推进系统具有非常好的力学环境适应性;随探空火箭、小型运载火箭回收后,冷气推进系统可以重复使用,降低火箭发射成本。
Highly integrated reusable cold air propulsion system
高度集成可重复使用的冷气推进系统
2024-07-12
Patent
Electronic Resource
Chinese
Highly Operable Propulsion for Reusable Launch Vehicle Applications
British Library Conference Proceedings | 2003
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