The invention discloses an intelligent prediction guidance method for Mars pneumatic auxiliary orbit descending, and belongs to the field of deep space exploration. According to the method, a high-precision kinetic model of the Mars pneumatic-assisted orbit descent is constructed, a network training data set is generated by utilizing the high-precision model, a near-fire-point state intelligent forecasting model and a far-fire-point state intelligent forecasting model of the Mars pneumatic-assisted orbit descent are constructed, and meanwhile, near-fire-point heat flow constraints are constructed; designing a predictive guidance method by taking the orbit height deviation and the control input as optimization performance indexes; and optimizing and solving the control input to control the detector until the track height of the detector is reduced to be close to the preset track height, so that the detector is reduced to the preset track under the condition of meeting heat flow and control amplitude constraints, and meanwhile, the fuel consumption of the detector is reduced. According to the method, by solving the states of the near fire point and the far fire point under the two-body dynamic model, the network is constructed to predict the deviation value between the states of the near fire point and the far fire point under the high-precision dynamic model and the prediction result of the two-body model, and the training cost of the neural network is reduced.

    火星气动辅助降轨智能预测制导方法,属于深空探测领域。本发明构建火星气动辅助降轨高精度动力学模型,利用高精度模型生成网络训练数据集,构建火星气动辅助降轨近火点状态智能预报模型和远火点状态智能预报模型,同时构建近火点热流约束,以轨道高度偏差和控制输入为优化性能指标,设计预测制导方法;优化求解控制输入对探测器进行控制,直至探测器轨道高度降低至预定轨道高度附近,实现在满足热流和控制幅值约束的条件下将探测器降至预定轨道,同时降低探测器的燃料消耗。本发明通过求解二体动力学模型下的近火点和远火点状态,构建网络预测高精度动力学模型下的近火点、远火点状态与二体模型预测结果之间的偏差量,降低神经网络的训练成本。


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    Title :

    Intelligent prediction guidance method for Mars pneumatic auxiliary orbit descending


    Additional title:

    火星气动辅助降轨智能预测制导方法


    Contributors:
    CUI PINGYUAN (author) / CHEN ZELONG (author) / CHEN YUHONG (author) / LONG JIATENG (author) / ZHU SHENGYING (author) / LIANG ZIXUAN (author)

    Publication date :

    2025-03-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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