To provide a configuration construction and attitude control method for a pyramid deorbit sail.SOLUTION: A shape formulation of a pyramidal sail leaving an orbit according to the present invention establishes a three-dimensional orbit attitude binding dynamics model, by taking in consideration atmospheric drag and environmental perturbation of a shape of the earth; regards a sail leaving an orbit as a rigid body and regards a spacecraft main body as a mass point; improves precision of the dynamics model in consideration of a blocked state of airflow with respect to areas of a windward side; obtains a rule concerning a cone angle of the pyramidal sail leaving an orbit and a length of a support rod, of attitude stability and efficiency of leaving the orbit in different cases on the basis of the model; analyzes and optimizes a shape parameter of a system of the pyramidal sail leaving the orbit, on the basis of the rule; and has high attitude stability and high efficiency of leaving the orbit, which designs a quaternion feedback rearrangement PID control rule, on the basis of the model and the selected shape parameter, and stabilizes an attitude, with respect to a speed direction, of the spacecraft in which the sail leaving the orbit is arranged, so as to improve the efficiency of leaving the orbit.SELECTED DRAWING: Figure 1

    【課題】ピラミッド型軌道離脱セイルの形状構築及び姿勢制御方法を提供する。【解決手段】本発明の実現方法は、大気抗力と地球形状の環境摂動を考慮し、三次元軌道姿勢結合動力学モデルを確立し、軌道離脱セイルを剛体、宇宙機本体を質点とみなし、風上面積は気流の遮断状況を考慮して動力学モデルの精度を向上させ、前記モデルに基づいて異なる場合での宇宙機の姿勢安定性と軌道離脱効率の、ピラミッド型軌道離脱セイルのコーン角と支持棒の長さに関する法則を得て、前記法則に基づき、ピラミッド型軌道離脱セイルシステムの形状パラメータを分析及び最適化し、高い姿勢安定性と高い軌道離脱効率を備えたピラミッド型軌道離脱セイルを得て、上記のモデルと選択された形状パラメータに基づき、四元数フィードバック再配置PID制御則を設計し、軌道離脱セイルが配備された宇宙機の速度方向に対する姿勢を安定させ、軌道離脱効率を向上させることである。【選択図】図1


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    Titel :

    CONFIGURATION CONSTRUCTION AND ATTITUDE CONTROL METHOD FOR PYRAMID DEORBIT SAIL


    Weitere Titelangaben:

    ピラミッド型軌道離脱セイルの形状構築及び姿勢制御方法


    Beteiligte:
    ZHANG JINGRUI (Autor:in) / ZHANG RUONAN (Autor:in) / YANG KEYING (Autor:in) / LI LINCHENG (Autor:in)

    Erscheinungsdatum :

    2023-04-20


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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