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.
A Feedback Guidance Scheme for Orbital Rendezvous
J of Astronaut Sci
The Journal of the Astronautical Sciences ; 47 , 3-4 ; 229-237
1999-09-01
9 pages
Article (Journal)
Electronic Resource
English
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