The invention provides a small-sized integrated double-component propulsion module for a microsatellite. The small-sized integrated double-component propulsion module comprises a storage box module, a gas filling valve, a liquid filling valve, a self-locking valve and a double-component thruster, wherein the gas filling valve, the liquid filling valve, the self-locking valve and the double-component thruster are integrated at the bottom of the storage box module; the storage box module comprises an oxidant storage box and a combustion agent storage box, the tops of the oxidant storage box and the combustion agent storage box are communicated with an external gas storage device through gas filling valves, and the bottoms of the oxidant storage box and the combustion agent storage box are respectively communicated with an external liquid storage device through liquid filling valves; an oxidizing agent storage area at the bottom of the oxidizing agent storage box and a combustion agent storage area at the bottom of the combustion agent storage box are communicated with the two-component thruster through self-locking valves respectively. The gas filling valve, the liquid filling valve, the self-locking valve and the two-component thruster are integrated with the storage tank module, so that the layout space of the propulsion system is reduced, and the requirements of light structure weight and small size of the satellite propulsion system are met. The method can be applied to a satellite propulsion system with a limited microsatellite space structure.

    本发明提供了一种用于微小卫星的小型集成化双组元推进模块,包括贮箱模块与集成在贮箱模块的底部的气加注阀、液加注阀、自锁阀以及双组元推力器;贮箱模块包括氧化剂贮箱与燃烧剂贮箱,氧化剂贮箱与燃烧剂贮箱顶部通过气加注阀连通外界气体储存装置,氧化剂贮箱底部与燃烧剂贮箱底部均分别通过液加注阀连通外界液体储存装置;氧化剂贮箱底部所具有的氧化剂储存区与燃烧剂贮箱底部所具有的燃烧剂储存区均分别通过自锁阀连通双组元推力器。本发明将气加注阀、液加注阀、自锁阀以及双组元推力器与贮箱模块一体集成,实现了推进系统布局空间的缩减,满足了卫星推进系统结构重量轻、体积小的需求。能够应用于微小卫星空间结构受限的卫星推进系统中。


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    Title :

    Small-sized integrated two-component propulsion module for microsatellite


    Additional title:

    用于微小卫星的小型集成化双组元推进模块


    Contributors:
    ZHU YIXIAO (author) / SHEN ZHISHUAI (author) / MENG XIANGHAI (author) / LU ZIYANG (author) / YANG JUN (author) / LIAN RENZHI (author) / KAGEYASU (author)

    Publication date :

    2024-03-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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