The invention relates to a whole-section control method for a space-atmosphere inner orbit of a ground strike spacecraft, and aims to solve the problems that when the spacecraft arrives at a reentry section from a deorbit section, the accuracy of selecting a reentry point is low, and the flight path of a reentry device in the reentry section is not required to be optimal. Establishing a kinetic model of the reentry device in a reentry section, obtaining a kinetic equation related to the strength of the transverse range capability and the longitudinal range capability of the reentry device in combination with a quasi-balance condition, obtaining a reentry point area according to target point parameters and the equation, establishing a kinetic model of the reentry device in a deorbit section, and taking a coplanar Lambert maneuvering method as a maneuvering mode of the deorbit section. And obtaining a fuel optimal deorbit section control strategy, obtaining a target reentry point according to the fuel optimal deorbit section control strategy and the reentry point region, enabling the target reentry point to be a final position point of a reentry device in a deorbit section and an initial position of the reentry section, and controlling a heeling angle and an attack angle by utilizing an hp self-adaptive Guass pseudo-spectral method to obtain an optimal track of the reentry section. The method belongs to the field of spacecraft orbit control.

    一种对地打击航天器空间‑大气层内轨道全段控制方法,为解决航天器从离轨段抵达再入段时选择再入点的准确性低,以及再入器在再入段的飞行轨迹未必最优的问题。建立再入器在再入段的动力学模型,结合准平衡条件得到有关再入器横程能力与纵程能力强弱的动力学方程,根据目标点参数和方程获取再入点区域,建立再入器在离轨段的动力学模型,将同平面Lambert机动方法作为离轨段的机动方式,得到燃料最优离轨段控制策略,根据燃料最优离轨段控制策略和再入点区域获取目标再入点,令目标再入点为再入器在离轨段的最终位置点和再入段的初始位置,利用hp自适应Guass伪谱法控制倾侧角与攻角,获取再入段的最优轨迹。属于航天器轨道控制领域。


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    Titel :

    Ground strike spacecraft space-atmosphere inner orbit whole-section control method


    Weitere Titelangaben:

    一种对地打击航天器空间-大气层内轨道全段控制方法


    Beteiligte:
    WU BAOLIN (Autor:in) / DONG YUYANG (Autor:in) / DING XUELIANG (Autor:in) / DAI HANSU (Autor:in) / SUN ZHAOBO (Autor:in) / CHEN JUNYU (Autor:in) / MA JUN (Autor:in)

    Erscheinungsdatum :

    07.04.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS





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