Quasi-linear model reference tracking control of approaching non-cooperative target based on direct parametric control

In this paper, a robust integrated translation and rotation tracking controller is proposed base on model reference tracking of quasi-linear system and direct parametric control approach for approaching non-cooperative target under the presence of parameter uncertainty. A tracking controller is provided in quasi-linear framework, which consists of the feedback stabilizing controller and the feed-froward compensator controller such that relative location between servicing spacecraft and target and relative attitude between chaser and the Earth can asymptotically tracking the given signal, the servicing spacecraft can observe the operating state or determine the fault point hovering on the non-cooperative target, further the integrative thruster layout is taking into account. A numerical simulation demonstrates the effect of the designed control strategy.

[1]  Tim Luu,et al.  Space shuttle testing of the TriDAR 3D rendezvous and docking sensor , 2012, J. Field Robotics.

[2]  Guang-Ren Duan,et al.  Generalized Sylvester Equations: Unified Parametric Solutions , 2015 .

[3]  Marcel J. Sidi,et al.  Spacecraft Dynamics and Control: A Practical Engineering Approach , 1997 .

[4]  Ming Xin,et al.  Integrated nonlinear optimal control of spacecraft in proximity operations , 2010, Int. J. Control.

[5]  Guang-Ren Duan Parametric control of quasi-linear systems by output feedback , 2014, 2014 14th International Conference on Control, Automation and Systems (ICCAS 2014).

[6]  Gang Xu,et al.  Direct parametric control approach to robust integrated relative position and attitude control for non-cooperative rendezvous , 2015, 2015 34th Chinese Control Conference (CCC).

[7]  J.T. Gravdahl,et al.  6-DOF mutual synchronization of formation flying spacecraft , 2006, Proceedings of the 45th IEEE Conference on Decision and Control.

[8]  Farhad Aghili,et al.  Time-Optimal Detumbling Control of Spacecraft , 2009 .

[9]  Graham G. Swinerd,et al.  Dynamics of Spacecraft , 2011 .

[10]  Hirohisa Kojima Fly-Around Motion Control Based on Exact Linearization with Adaptive Law , 2005 .

[11]  Kamesh Subbarao,et al.  Nonlinear Control of Motion Synchronization for Satellite Proximity Operations , 2008 .

[12]  G.-R. Duan,et al.  Integrated translational and rotational finite-time maneuver of a rigid spacecraft with actuator misalignment , 2012 .

[13]  V. Kapila,et al.  Output feedback control for spacecraft formation flying with coupled translation and attitude dynamics , 2005, Proceedings of the 2005, American Control Conference, 2005..

[14]  P. Gurfil,et al.  Effect of Kinematic Rotation-Translation Coupling on Relative Spacecraft Translational Dynamics , 2009 .

[15]  V. Kapila,et al.  Output feedback control for spacecraft with coupled translation and attitude dynamics , 2004, 2004 43rd IEEE Conference on Decision and Control (CDC) (IEEE Cat. No.04CH37601).

[16]  Shu-Nan Wu,et al.  Robust H ∞ Control for Spacecraft Rendezvous with a Noncooperative Target , 2013, TheScientificWorldJournal.

[17]  Guang-Ren Duan Satellite attitude control—A direct parametric approach , 2014, Proceeding of the 11th World Congress on Intelligent Control and Automation.

[18]  John Leif Jørgensen,et al.  Noncooperative Rendezvous Using Angles-Only Optical Navigation: System Design and Flight Results , 2013 .

[19]  Duan Guang-Ren,et al.  Direct parametric control of fully-actuated second-order nonlinear systems—The normal case , 2014, Proceedings of the 33rd Chinese Control Conference.

[20]  O. Yakimenko,et al.  Optimal Rendezvous Trajectories of a Controlled Spacecraft and a Tumbling Object , 2011 .

[21]  Guang-Ren Duan,et al.  Non-cooperative rendezvous and interception —A direct parametric control approach , 2014, Proceeding of the 11th World Congress on Intelligent Control and Automation.

[22]  Guang-Ren Duan,et al.  Solution to the second-order Sylvester matrix equation MVF/sup 2/+DVF+KV=BW , 2006, IEEE Transactions on Automatic Control.