The invention relates to an anti-interference fixed-point landing explicit guidance method for a spacecraft. The method comprises the following steps: establishing a dynamic model under an LVLH coordinate system; establishing a disturbance observer, performing online estimation on disturbance to obtain an anti-interference item, and introducing the anti-interference item into a guidance instruction for compensation to obtain a model after disturbance compensation; constructing a guidance law for the model after disturbance compensation by using an optimal principle, and resolving a guidance instruction; and resolving to obtain an analysis voyage expression, and calculating a thrust correction value to realize the control of the anti-interference fixed-point landing of the spacecraft. The method provided by the invention can ensure the guidance precision under the condition of uncertain interference, and has the advantages of small calculation amount and capability of realizing fixed-point landing.

    本发明涉及一种航天器抗干扰定点着陆显式制导方法,包括:建立LVLH坐标系下的动力学模型;建立干扰观测器,对扰动进行在线估计得到抗干扰项,并引入制导指令中进行补偿,得到扰动补偿后模型;利用最优原理对所述扰动补偿后模型构造制导律,解算制导指令;解算得到解析航程表达式,并计算推力修正值,实现航天器抗干扰定点着陆的控制。本发明的方法可以保证存在不确定性干扰情况下的制导精度,同时具有计算量小和能够实现定点着陆的优势。


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    Titel :

    Spacecraft anti-interference fixed-point landing explicit guidance method


    Weitere Titelangaben:

    航天器抗干扰定点着陆显式制导方法


    Beteiligte:
    LIU YANG (Autor:in) / PENG KUN (Autor:in) / LEE HEE-SUNG (Autor:in) / LIANG LU (Autor:in) / HOU ZHENDONG (Autor:in) / ZENG HAO (Autor:in) / YU KANG (Autor:in) / WANG PENGCHENG (Autor:in)

    Erscheinungsdatum :

    2022-10-25


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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