Safe Spacecraft Rendezvous with Constraint Model Predictive Control

2018-08-23
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 chasertarget 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.

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Citation Formats
O. Tekinalp, “Safe Spacecraft Rendezvous with Constraint Model Predictive Control,” presented at the AIAA/ Amerıcan Astronautıcal Socıety Astrodynamics Specialst Conference, 19 - 23 Ağustos 2018, Snowbird, Utah, United States, 2018, Accessed: 00, 2021. [Online]. Available: http://amz.xcdsystem.com/A464D031-C624-C138-7D0E208E29BC4EDD_abstract_File10296/FinalPaper_AAS-18-390_0910094339.pdf.