The method of osculating parameters is used to obtain the integral orbit restrictedness condition around the colinear libration center in the restricted elliptical three body problem. It is shown that, if a restricted orbit exists, it can be found by solving the equations of spacecraft motion under the above mentioned conditions.


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    Title :

    Limitation of Spacecraft Orbit Near Colinear Libration Center of Limited Elliptical Three Body Problem (Abstract Only)


    Contributors:

    Publication date :

    1987


    Size :

    1 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English