The invention is applied to the technical field of aerospace, and particularly discloses a satellite attitude and orbit integrated control device for step-length control thrusters, the satellite attitude and orbit integrated control device comprises a body, the mass center coordinate system of the body is 0-XYZ, a third thruster and a fourth thruster are rotatably mounted on the XOZ face of the body, a rotating meshing mechanism is arranged on the outer surface of the body, and the third thruster and the fourth thruster are meshed with each other through the rotating meshing mechanism. The posture of the body can be accurately adjusted by rotating the meshing mechanism. According to the satellite attitude and orbit integrated control device for controlling the thruster through the step length, when the body needs to be subjected to orbit adjustment, a nozzle in a certain axial direction is adjusted, so that the thrust direction of the nozzle is perpendicular to the axial direction of the advancing direction, the speed is provided, and orbit transfer is conducted according to the Kepler law; when the satellite needs to be subjected to attitude adjustment around a certain axis, the nozzles are adjusted to be parallel to the bottom surface, the two engines on the same plane are started to generate torque, the satellite is made to roll to adjust the attitude, and when the body needs attitude and orbit control, the engine step length can be adjusted to control thrust working time adjustment.

    本发明用于航空航天技术领域,具体公开了一种步长控制推力器的卫星姿轨一体化控制装置,包括本体,所述本体的质心坐标系为0‑XYZ,所述本体的XOZ面分别转动安装有第三推力器与第四推力器,所述本体的外表面设置有转动啮合机构,通过转动啮合机构使本体能够准确的调整姿态。该通过步长控制推力器的卫星姿轨一体化控制装置,当本体需要进行轨道调整时,调整某一轴向方向喷口,使其推力方向垂直与前进方向轴向,提供速度,根据开普勒定律使其变轨;当卫星需要绕某轴进行姿态调整时,调整喷口与底面平行,两台同面发动机启动,产生力矩,使卫星滚转调整姿态,当本体需要进行姿轨控时,可调整发动机步长来控制推力做工时间调整。


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    Title :

    Satellite attitude and orbit integrated control device and method of step-length control thruster


    Additional title:

    一种步长控制推力器的卫星姿轨一体化控制装置及方法


    Contributors:
    KANG HUIFENG (author) / CHEN XIANGQIU (author) / LIU JINGWANG (author) / XIA GUANGQING (author) / HU MIN (author) / LI ZONGGANG (author)

    Publication date :

    2025-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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