The invention relates to an orbit control thrust direction adjusting method, belongs to the technical field of solid rocket engines, and solves the problems that an existing orbit control engine is low in thrust adjusting response speed and low in thrust direction accuracy. The orbit control thrust direction adjusting method comprises the steps that S1, according to the needed orbit control thrust direction, the orientation of a gas nozzle of a rotating ring groove is determined; s2, a motor drives a rotating ring groove to rotate; s3, the gas nozzles are aligned with the gas branch channels; and the fuel gas is sprayed out through the gas nozzle to provide orbit control thrust for the aircraft. According to the orbit control thrust direction adjusting method, the motor directly drives the annular notch covering the fuel gas disc to rotate, the actual fuel gas spraying direction is controlled, and therefore adjustment of the orbit control thrust direction is achieved.

    本发明涉及一种轨控推力方向调节方法,属于固体火箭发动机技术领域,解决了现有轨控发动机推力调节响应速度慢和推力方向的精确性降低的问题。本发明的轨控推力方向调节方法包括步骤S1:根据需要的轨控推力方向,确定旋转环槽的气体喷口的朝向;步骤S2:电机驱动旋转环槽旋转;步骤S3:气体喷口与燃气支道对齐;燃气经气体喷口喷出,提供对飞行器的轨控推力。本发明的轨控推力方向调节方法通过电机直接驱动燃气盘处覆盖的环状槽口旋转,控制燃气实际喷出的方向,从而实现轨控推力方向的调节。


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    Titel :

    Orbit control thrust direction adjusting method


    Weitere Titelangaben:

    一种轨控推力方向调节方法


    Beteiligte:
    JI MENG (Autor:in) / XU NUO (Autor:in) / GAO HUI (Autor:in) / JING WENLI (Autor:in)

    Erscheinungsdatum :

    06.02.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS



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