The invention provides a thruster layout design method and device for rendezvous and docking of micro-nano satellites and a readable medium. The problems that an existing layout design method is not suitable for the micro-nano satellites, and large disturbing force is generated on an orbit during attitude control are solved. The method comprises the steps of constructing a satellite body coordinate system; determining positions and thrust directions of the four orbit control thrusters under a satellite body coordinate system according to the first constraint; selecting a first mounting surface and a second mounting surface from a satellite body coordinate system, wherein the first mounting surface and the second mounting surface are symmetrical about a satellite body; determining the position and thrust direction of the first group of attitude control thrusters on the first mounting surface and the position and thrust direction of the second group of attitude control thrusters on the second mounting surface according to the second constraint, wherein the second group of attitude control thrusters and the first group of attitude control thrusters are symmetrically mounted in a couple form; wherein the first constraint is that the resultant force of every two of the four orbit control thrusters passes through the center of mass of the satellite, and the second constraint condition is that the thrust generated by the attitude control thrusters does not pass through the center of mass of the satellite.

    本发明提供一种用于微纳卫星交会对接的推力器布局设计方法、装置及可读介质,解决了现有布局设计方法不适用于微纳卫星且在姿态控制时会对轨道产生很大的干扰力的问题。方法包括构建卫星本体坐标系;根据第一约束确定四个轨控推力器在卫星本体坐标系下的位置和推力方向;从卫星本体坐标系中选取第一安装面和第二安装面,第一安装面和第二安装面关于星体对称;根据第二约束确定第一组姿控推力器在第一安装面的位置和推力方向、第二组姿控推力器在第二安装面的位置和推力方向,第二组姿控推力器与第一组姿控推力器呈力偶形式对称安装;其中,第一约束为四个轨控推力器的两两合力过卫星质心,第二约束条件为姿控推力器产生的推力不过卫星质心。


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    Title :

    Thruster layout design method and device for rendezvous and docking of micro-nano satellites


    Additional title:

    用于微纳卫星交会对接的推力器布局设计方法、装置


    Contributors:
    CHEN TING (author) / SI CHAOMING (author) / CHANG LIANG (author) / WANG ZUN (author) / YI SHAN (author) / WU ZHAILIAN (author) / WANG MENG (author)

    Publication date :

    2023-10-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS





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