A landing guidance method adaptive to thrust response large lag utilizes polynomial guidance to calculate a reference trajectory, takes engine response characteristics into consideration in the calculation process of the polynomial guidance method, and solves the technical problems caused by engine command thrust response large lag in the flight process. The aircraft can complete a flight task according to a polynomial guidance planning trajectory. The relation between the instruction acceleration and the response acceleration is obtained through the engine characteristics, the delay characteristic is compensated into the acceleration instruction through the reference trajectory of the polynomial, the polynomial landing guidance method considering the thrust response large lag is obtained, it can be guaranteed that the output instruction is the target acceleration calculated through the polynomial, and the reliability of landing guidance is improved. And target speed and position control of landing is accurately realized.

    一种适应推力响应大滞后的着陆制导方法,利用多项式制导计算参考轨迹,将发动机响应特性考虑到多项式制导方法的计算过程中,解决在飞行过程中由于发动机指令推力响应大滞后带来的技术问题,能够使得飞行器按照多项式制导规划的轨迹完成飞行任务。本发明通过发动机特性得到指令加速度与响应加速度之间的关系,利用多项式的参考轨迹将延迟特性补偿到加速度指令中,得到考虑推力响应大滞后的多项式着陆制导方法,能够保证输出的指令为多项式计算的目标加速度,精确实现着陆的目标速度位置控制。


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    Title :

    Landing guidance method suitable for thrust response large lag


    Additional title:

    一种适应推力响应大滞后的着陆制导方法


    Contributors:
    WANG LU (author) / HONG LIANG (author) / DING HUANYU (author) / ZHUO JUNWEI (author) / CHEN YICHENG (author) / ZHU LEILEI (author) / LIU SI (author)

    Publication date :

    2023-06-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS





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