A control assembly for a spacecraft includes a propellant management assembly configured to regulate a supply of propellant from a storage unit to a thrust generator. The control assembly also includes a controller having a processor configured to receive input from the spacecraft and to receive at least one input from the propellant management assembly or from the thrust generator. The processor is further configured to determine a desired mode of operation of the thrust generator based on the inputs, and based on the determination 1) send an output to a propellant management assembly to operate in a first mode in which the thrust generator uses propellant to electrostatically generate thrust, and a second mode in which the thrust generator does not electrostatically generate thrust. Or 2) sending an output to the propellant management assembly to operate in a second mode in which the thrust generator uses propellant to pneumatically generate thrust.

    一种用于航天器的控制组件,该控制组件包括推进剂管理组件,该推进剂管理组件构造成调节从存储单元向推力发生器的推进剂供应。该控制组件还包括控制器,该控制器具有处理器,该处理器配置成接收来自航天器的输入,并且接收来自推进剂管理组件或来自推力发生器的至少一个输入。该处理器进一步配置成基于这些输入来确定该推力发生器的期望操作模式,并且基于这一确定1)向推进剂管理组件发送输出,从而以第一模式操作,在该第一模式中,该推力发生器使用推进剂来以静电方式生成推力,或者2)向推进剂管理组件发送输出,从而以第二模式操作,在该第二模式中,该推力发生器使用推进剂来以气动方式生成推力。


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    Title :

    Propulsion system for spacecraft


    Additional title:

    用于航天器的推进系统


    Contributors:

    Publication date :

    2023-03-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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