The problem of fuel/time trajectory optimization is considered for a spacecraft moving relative to another in a perturbed, elliptical orbit. The relative motion model for the deputy satellite with respect to the chief is assumed to be well-approximated using the Gim–Alfriend state transition matrix. Control is applied in the in- and cross-track directions, which makes this an underactuated but reachable system for any eccentricity and inclination (excluding the critical inclination). The system is discretized using a zero-order hold on the input, and the control signals are computed using a linear program, which results in a bang-off-bang control profile. A balance between the time of flight and the required fuel are analyzed using a genetic algorithm and the results are compared with two well-known maneuvers from impulsive orbit theory. The results of the new method agree well with the impulsive solution in terms of the velocity change required.


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    Titel :

    Fuel-/Time-Optimal Relative Trajectories for a Satellite near a Perturbed, Elliptical Orbit


    Beteiligte:
    Rogers, Andrew (Autor:in) / Woolsey, Craig (Autor:in) / Black, Jonathan (Autor:in) / McGwier, Robert (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2016-07-18


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






    Satellite Relative Motion in Elliptical Orbit Using Relative Orbit Elements (AAS 11-497)

    Han, C. / Yin, J. / American Astronautical Society et al. | British Library Conference Proceedings | 2012