This paper presents an analytic solution to the optimal reconfiguration problem of satellite formation flying in J2 orbital perturbation. Continuous and variable low-thrust accelerations are represented by the Fourier series, and initial and final boundary conditions are used to establish the constraints on the thrust functions. The thrust functions are implemented by optimal Fourier coefficients that minimize the cost during the maneuver. The analytic solution composed of these Fourier coefficients are simply represented in a closed form, and no approximation is needed. Numerical simulations are conducted to visualize and compare the results obtained in this paper with those of previous papers with no perturbations. The analytic solution developed in this paper is more accurate in that the general behavior of the optimal control history and reconfiguration trajectories are easily calculated even in the presence of the J2 potential disturbance. The analytic solution is useful for designing a reconfiguration controller for satellite formation flying under J2 orbital perturbation.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Analytic Solution to Optimal Reconfigurations of Satellite Formation Flying in Circular Orbit under $J_2$ Perturbation


    Contributors:


    Publication date :

    2012-07-01


    Size :

    1616195 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Dual-Spacecraft Formation Flying in Deep Space: Optimal Collision-Free Reconfigurations

    Yoonsoo Kim / Mehran Mesbahi / Fred Y. Hadaegh | AIAA | 2003




    Optimal Reconfigurations of Two-Craft Coulomb Formation in Circular Orbits

    Inampudi, R. / Schaub, H. / American Institute of Aeronautics and Astronautics; American Astronautical Society | British Library Conference Proceedings | 2010