AAS/AIAA Astrodynamics Specialist Conference, Utah, United States Of America, 19 - 23 August 2018, vol.167, pp.883-895
Rendezvous and docking problem of a pair of low Earth orbit spacecraft is addressed. Equations for the nonlinear orbital relative motion of spacecraft are derived and a simulation code for this motion is developed. For the control algorithm, linearized Hill-Clohessy-Wiltshire (HCW) equations are used in chaser target spacecraft configuration. All authority is given to the chaser spacecraft, and the target is kept passive. The HCW equations are linearized assuming a circular orbit. Model Predictive Control (MPC) strategy is applied with safety constraints including debris avoidance and Line of Sight constraint. This includes the avoidance of a relatively moving debris with an unbounded motion. Simulation results are given and discussed. A parametric study is also performed to obtain the proper prediction horizon as well as weighting matrices to be used in the simulations.