The invention discloses a Mars entry section anti-saturation trajectory optimization method, and belongs to the field of aircraft guidance control. The implementation method comprises the following steps: defining a heeling angle obtained by tracking a resistance acceleration curve as a calculated heeling angle; a three-level orthogonal table is adopted to select an aerodynamic parameter disturbance combination, then a formula for calculating the sensitivity of the heeling angle to the disturbance combination is constructed, and the influence of aerodynamic parameter disturbance on heeling angle calculation is quantified through the sensitivity formula; in order to meet the terminal constraint requirement and the anti-saturation capability requirement of the lander under aerodynamic disturbance, a terminal constraint optimization index and an anti-saturation optimization index based on a sensitivity formula are respectively designed, and linear weighting is carried out on two optimization indexes, namely a height voyage constraint index and the anti-saturation index; and obtaining an entry trajectory optimization comprehensive index for improving the anti-saturation capability. And optimizing the comprehensive indexes by using an optimization method to obtain an optimized heeling angle-energy profile, and tracking the profile to obtain an anti-saturation entry trajectory.

    本发明公开的一种火星进入段抗饱和轨迹优化方法,属于飞行器制导控制领域。本发明实现方法为:将跟踪该阻力加速度曲线得到的倾侧角定义为计算倾侧角;采用三水平正交表选取气动参数扰动组合,进而构建计算倾侧角对扰动组合的敏感性公式,通过所述敏感性公式量化气动参数扰动对计算倾侧角的影响;为了满足着陆器在气动扰动下的终端约束要求和抗饱和能力的要求,分别设计终端约束优化指标和基于敏感性公式的抗饱和优化指标,对高度航程约束指标、抗饱和指标两个优化指标进行线性加权,得到提高抗饱和能力的进入轨迹优化综合指标。利用优化方法对上述综合指标进行优化,得到优化后的倾侧角‑能量剖面,跟踪该剖面后得到抗饱和进入轨迹。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Mars entry section anti-saturation trajectory optimization method


    Weitere Titelangaben:

    火星进入段抗饱和轨迹优化方法


    Beteiligte:
    LIANG ZIXUAN (Autor:in) / GU HENA (Autor:in) / CUI PINGYUAN (Autor:in) / ZHU SHENGYING (Autor:in) / XU RUI (Autor:in) / LONG JIATENG (Autor:in)

    Erscheinungsdatum :

    07.04.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS




    Trajectory Optimization and Guidance Methods for Mars Entry

    Li, Shuang / Liu, Xu / Jiang, Xiu-qiang et al. | Springer Verlag | 2024



    Mars Pathfinder Atmospheric Entry Trajectory Design

    Spencer, D. A. / Braun, R. D. / American Astronautical Society| American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1996