A feedback guidance scheme for autonomous orbital rendezvous is presented. The guidance scheme is developed for spacecraft equipped with thrusters that operate in an on-off mode with constant thrust magnitude. The control law is obtained by solving the discrete-time, steady-state linear quadratic regulator (LQR) problem. A parameter optimization method is used to obtain the optimal weighting matrices for the discrete-time LQR problem so that the total impulsive velocity increment (ΔV) is minimized. Several planar rendezvous maneuvers are presented for spacecraft equipped with electric propulsion thrusters and a range of sample periods (time between thruster firings) is investigated. The guidance scheme exhibits rapid convergence to minimum ΔV solutions and the subsequent simulations show good closed-loop response characteristics.


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    Titel :

    A Feedback Guidance Scheme for Orbital Rendezvous


    Weitere Titelangaben:

    J of Astronaut Sci


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.09.1999


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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