SAFE SPACECRAFT RENDEZVOUS WITH CONSTRAINED MODEL PREDICTIVE CONTROL

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2019-01-01

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BÜYÜKKOÇAK, ALİ TEVFİK
Tekinalp, Ozan

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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.

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https://hdl.handle.net/11511/53612

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Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

A. T. BÜYÜKKOÇAK and O. Tekinalp, “SAFE SPACECRAFT RENDEZVOUS WITH CONSTRAINED MODEL PREDICTIVE CONTROL,” 2019, vol. 167, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53612.