The invention discloses an aerodynamic capture maneuvering guidance method based on sideslip correction, and relates to the field of orbit braking energy consumption optimization, and the method comprises the steps: building a maneuvering dynamics model of a spacecraft in an atmospheric flight section in an atmospheric capture maneuvering process; s2, performing profile analysis on the maneuvering and dynamical model based on a saturation function, and designing a target aerodynamic capture heeling angle reference trajectory; basic parameters of the saturation function are set through the rolling maneuvering capability of the spacecraft, and guidance parameters with the heeling angle as modulation in the aerodynamic capture process are determined. According to the method, through a saturation function approximation step type heeling angle time sequence profile, the sensitivity of guidance parameters can be remarkably reduced, and the robustness of a guidance system is enhanced.

    本发明公开了一种基于侧滑修正的气动捕获机动制导方法,涉及轨道制动耗能优化领域,包括建立航天器在大气捕获机动过程中大气飞行段的机动动力学模型;S2、基于饱和函数对机动动力学模型进行剖面分析并设计目标气动捕获倾侧角基准轨迹;所述饱和函数的基本参数通过航天器滚转机动能力设置,并确定气动捕获过程中以倾侧角为调制的制导参数。本发明能通过饱和函数近似阶跃型的倾侧角时序剖面,可以显著降低制导参数的敏感性,增强制导系统的鲁棒性。


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    Title :

    Aerodynamic capture maneuvering guidance method based on sideslip correction


    Additional title:

    一种基于侧滑修正的气动捕获机动制导方法


    Contributors:
    HAN HONGWEI (author) / YANG ZHIKAI (author) / QIAO DONG (author)

    Publication date :

    2025-04-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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