The present invention discloses a two-pulse planet capture orbit method based on weak stability boundary, relates to a capture orbit method when a prober is captured by a target heavenly body during interstellar travel and enters into a task orbit, and belongs to the technical field of aerospace. The two-pulse planet capture orbit method comprises the following steps of: establishing motion equation of the prober in sun-planet centroid rotation systems; determining the weak stability boundary of the sun-planet system; selecting a weak stability boundary coefficient e, a distance r0 between the prober and the planet, and an included angle [theta] of the prober and the planet according to the target task orbit; applying first engine drive to the prober to enable the prober to enter into a weak stability boundary transfer orbit from a hyperbola orbit; and applying second engine drive to the prober to enable the prober to enter into the target task orbit from the weak stability boundary transfer orbit, and finally obtaining orbit capture. Atmosphere information of the planet is not required to be considered, and the two-pulse planet capture orbit method is high in reliability without being influenced by planetary atmosphere uncertainty. In addition, required speed increment is small, application range is large, and the two-pulse planet capture orbit method has better capture orbit effect for a task orbit having higher height.


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    Titel :

    Two-pulse planet capture orbit method based on weak stability boundary


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

    Erscheinungsdatum :

    2016-01-20


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS