In this paper, the original nonlinear relative motion problem for a pair of satellites in which the leader is in a circular orbit is studied with a new perspective. This problem is regarded as a degenerate form of the circular restricted three-body problem, where only one central body's mass is considered. By using the techniques that are often adopted in the three-body problem, four integrals are found. In these integrals, the first one is the degenerate form of the well-known Jacobi integral. The other ones correspond to the orbital integral constants of the classical two-body problem in a different way. A numerical simulation is conducted to validate these theoretical results. The simulation results show that the solutions of this paper are all correct. By using these integrals, one may understand the relative motion more thoughtful.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Some integrals observed in spacecraft relative motion problem with circular reference orbit


    Contributors:
    Dang, Zhaohui (author) / Tang, Shengyong (author) / Hu, Min (author)


    Publication date :

    2016-08-01


    Size :

    98102 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English