The invention relates to a double-asteroid system periodic orbit searching method based on the speed Poincare section and belongs to the field of aerospace. The method comprises the following steps that 1, the mass and size of each asteroid are obtained and are normalized; 2, a system rotating coordinate system is built; 3, the searching range is selected, the initial position of a detector is selected in the X-axis direction, the initial speed is gradually increased, orbit integration is carried out, the stopping condition is that the detector penetrates through the predetermined section, and then a Poincare map is drawn according to the speed at the termination point; 4, two adjacent initial points, penetrating through the axis, in the curve in the map are selected, an initial state average value is obtained to be subjected to integration again, a new initial point penetrating the axis is obtained, repeated iteration is carried out, and an accurate value is obtained; 5, the initial position of the detector is changed, and the third step and the four step are carried out repeatedly until the values cover the searching area. Compared with the prior art, the method has the advantages of being high in efficiency, comprehensive in searching, simple in calculation and the like, and is suitable for orbit design occasions where the detector detects a double-asteroid system.


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    Titel :

    Double-asteroid system periodic orbit searching method based on speed Poincare section


    Beteiligte:
    QIAO DONG (Autor:in) / LI XIANGYU (Autor:in) / CUI PINGYUAN (Autor:in) / SHANG HAIBIN (Autor:in) / WANG YAMIN (Autor:in)

    Erscheinungsdatum :

    2015-04-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS





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