The invention discloses a weak-gravity irregular small celestial body landing adaptive guidance method, and belongs to the technical field of deep space probe guidance. The implementation method comprises the following steps: selecting the position and speed of a detector as state variables, and establishing a detector landing dynamics model; introducing a performance function to determine a constraint boundary, giving an allowable upper bound and a lower bound, and determining a steady-state value of the performance function and a convergence speed parameter of the performance function; converting the trajectory tracking system with inequality constraints into an unconstrained tracking system through a preset performance function and an error conversion function; setting a neural network node number and a Gaussian basis function, and using RBFNN to approach uncertainty disturbance caused by gravitation of a small celestial body along with reduction of a distance between a detector and a landing point; gravitational field uncertainty disturbance of neural network fitting is introduced into the adaptive guidance law, adaptive guidance law parameters are adaptively adjusted along with the detector state, the tracking error and the neural network fitting result, and rapidness and high precision of trajectory tracking in the landing process are guaranteed.

    本发明公开的弱引力不规则小天体着陆自适应制导方法,属于深空探测器制导技术领域。本发明实现方法为:选取探测器位置和速度为状态变量,建立探测器着陆动力学模型;引入性能函数确定约束边界,给定允许的上界与下界,确定性能函数的稳态值及性能函数收敛速度参数;通过预设性能函数及误差转换函数,将有不等式约束的轨迹跟踪系统转换为无约束跟踪系统;设置神经网络节点数与高斯型基函数,使用RBFNN逼近小天体的引力随着探测器与着陆点距离的减小而带来的不确定性扰动;将神经网络拟合的引力场不确定性扰动引入自适应制导律中,自适应制导律参数随探测器状态、跟踪误差及神经网络拟合结果自适应调节,保证着陆过程中轨迹跟踪的快速性与高精度。


    Access

    Download


    Export, share and cite



    Title :

    Self-adaptive guidance method for landing of small irregular celestial body with weak gravitational force


    Additional title:

    弱引力不规则小天体着陆自适应制导方法


    Contributors:
    ZHU SHENGYING (author) / SUI ZHIHUI (author) / CUI PINGYUAN (author) / XU RUI (author) / LIANG ZIXUAN (author) / LONG JIATENG (author)

    Publication date :

    2024-03-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



    Small celestial body attachment trajectory self-adaptive curvature matching guidance method

    CUI PINGYUAN / ZHAO DONGYUE / ZHU SHENGYING et al. | European Patent Office | 2020

    Free access

    Extraterrestrial celestial body soft landing augmented curvature guidance method

    ZHU SHENGYING / YANG HE / CUI PINGYUAN et al. | European Patent Office | 2023

    Free access

    Prudent small celestial body landing strategy with risk precautions

    Cui, Pingyuan / Ge, Dantong / Jia, He et al. | Elsevier | 2019


    Adaptive Force-Control Augmentation for Small Celestial Body Sampling

    Mohseni, Nima / Bernstein, Dennis S. / Quadrelli, Marco B. | AIAA | 2023


    Trajectory design for landing on small celestial body with flexible lander

    Chen, Zelong / Long, Jiateng / Cui, Pingyuan | Elsevier | 2023