Robust Tracking Control Design for Spacecraft Under Control Input Saturation

2004 ◽  
Vol 27 (4) ◽  
pp. 627-633 ◽  
Author(s):  
Jovan D. Boskovic ◽  
Sai-Ming Li ◽  
Raman K. Mehra
2018 ◽  
Vol 32 (18) ◽  
pp. 1850201
Author(s):  
Liu Yang ◽  
Dongjie Li ◽  
Donghao Xu

This paper presents a robust tracking control with discrete-time linear quadratic regulation (LQR) method for micromanipulators. The micromanipulator is composed of three piezoelectric actuators (PEAs), which results in achieving three-degree-of-freedom motion. PEAs have been widely used in micromanipulation for biomedicine because of the advantages of its infinitely small displacement resolution and precision. However, owning to the nonlinear effects of PEAs, mainly hysteresis, can drastically degrade the tracking control accuracy. Therefore, it is desirable to develop advanced controllers to compensate hysteresis effect for improving the trajectory tracking performance. Before the controller design, a compensation for motion coupling error in vertical plane is concerned. Then, a controller consisting of three parts which are a nominal feedforward control input, a LQR control input and a control input based on system uncertainties compensation is designed. At last, the robust stability of the designed controller is proved through a Lyapunov stability analysis. The simulation results demonstrate that the proposed controller is effective in tracking applications, which can provide a high resolution performance.


2017 ◽  
Vol 7 (5) ◽  
pp. 439 ◽  
Author(s):  
Muxuan Pan ◽  
Kaiwen Zhang ◽  
Ye-Hwa Chen ◽  
Jinquan Huang

2013 ◽  
Vol 2013 ◽  
pp. 1-11 ◽  
Author(s):  
Neng Wan ◽  
Ming Liu ◽  
Hamid Reza Karimi

This paper investigates a robust guaranteed cost tracking control problem for thrust-limited spacecraft rendezvous in near-circular orbits. Relative motion model is established based on the two-body problem with noncircularity of the target orbit described as a parameter uncertainty. A guaranteed cost tracking controller with input saturation is designed via a linear matrix inequality (LMI) method, and sufficient conditions for the existence of the robust tracking controller are derived, which is more concise and less conservative compared with the previous works. Numerical examples are provided for both time-invariant and time-variant reference signals to illustrate the effectiveness of the proposed control scheme when applied to the terminal rendezvous and other astronautic missions with scheduled states signal.


2014 ◽  
Vol 21 (1) ◽  
pp. 130-139 ◽  
Author(s):  
Yao Zhang ◽  
Bin Xian ◽  
Chen Diao ◽  
Bo Zhao ◽  
Jian-chuan Guo

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