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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    Title :

    A Feedback Guidance Scheme for Orbital Rendezvous


    Additional title:

    J of Astronaut Sci


    Contributors:

    Published in:

    Publication date :

    1999-09-01


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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