Decoupling control law design with applications to flight

1998 ◽  
Author(s):  
Antony Snell
Keyword(s):  
Decoupling Control ◽  
Control Law

Control Strategy Research on Controllable Pendulum in Step Perturbation

2014 ◽  
Vol 602-605 ◽  
pp. 1387-1390
Author(s):  
Geng Biao Shen ◽  
Fan Li ◽  
Zi Chao Zhang ◽  
Jian Hui Zhao
Keyword(s):  
Autonomous Navigation ◽  
State Feedback ◽  
Decoupling Control ◽  
Control Law ◽  
Strategy Research ◽  
Existing Problems ◽  
Indirect Control ◽  
Control Scheme ◽  
Preliminary Study ◽  
And Control

Applying controllable pendulum to indicating vertical is a new method which can be used for autonomous navigation. There are some studies on the method and it puts forward the existing problems. In this paper, it carries on the preliminary study on drawbacks that it exists steady-state error in controllable pendulum, and designs a new control scheme combined direct control with indirect control while there is step perturbation. Then it designs the corresponding control law by using observer with state feedback and decoupling control. It makes software simulation by Matlab and the results show that the controllable pendulum can be controlled well to indicate vertical by using the designed control scheme and control law when it exists step perturbation.

Decoupling control law for structural control implementation

2001 ◽  
Vol 38 (34-35) ◽  
pp. 6147-6162 ◽  
Author(s):  
Q.S. Li ◽  
J.Q. Fang ◽  
A.P. Jeary ◽  
D.K. Liu
Keyword(s):  
Structural Control ◽  
Decoupling Control ◽  
Control Law ◽  
Control Implementation

Decoupling Control of Three Phase Boost Type PWM Rectifiers Based on Storage Function

2011 ◽  
Vol 71-78 ◽  
pp. 3988-3991
Author(s):  
Jiu He Wang ◽  
Hong Ren Yin
Keyword(s):  
Control System ◽  
Harmonic Distortion ◽  
Decoupling Control ◽  
Total Harmonic Distortion ◽  
Control Law ◽  
Pwm Rectifier ◽  
Storage Function ◽  
Simulink Simulation ◽  
Three Phase ◽  
Pwm Rectifiers

Based on the model of three phase boost type PWM rectifier in synchronous dq coordinates, a simple control law, which transforms the rectifier control system into decoupling and linear one,is deduced based on storage function. New rectifier control system based on the law has many advantages, such as simpler structure, and low total harmonic distortion,and good robustness for load. Decouping control system of three phase boost type PWM rectifiers is proved feasible by simulink simulation.

Decoupling in a Class of Nonlinear Systems by State Variable Feedback

1972 ◽  
Vol 94 (4) ◽  
pp. 323-329 ◽  
Author(s):  
S. N. Singh ◽  
W. J. Rugh
Keyword(s):  
Feedback Control ◽  
Nonlinear Systems ◽  
Bilinear Systems ◽  
Decoupling Control ◽  
Control Law ◽  
Sufficient Condition ◽  
Necessary And Sufficient Condition ◽  
Control Laws ◽  
State Variable ◽  
Necessary And Sufficient

For a class of nonlinear systems we derive a necessary and sufficient condition for the existence of a state variable feedback control law which accomplishes decoupling, as well as some conditions which characterize the class of decoupling control laws. Several examples are presented to illustrate the application of these results. For a special subclass which includes the so-called bilinear systems, we give two equivalent forms of the necessary and sufficient condition.

Spacecraft vibration suppression based on micro-gimbal moment of magnetically suspended flywheel with dynamic feedback and feedforward decoupling control

2017 ◽  
Vol 232 (21) ◽  
pp. 3881-3896 ◽  
Author(s):  
Xiaocen Chen ◽  
Yuanwen Cai ◽  
Yuan Ren ◽  
Qiang Liu
Keyword(s):  
High Frequency ◽  
State Feedback ◽  
Vibration Suppression ◽  
Decoupling Control ◽  
Unmodeled Dynamics ◽  
Control Law ◽  
Dynamic Feedback ◽  
Steering Law ◽  
Moment Control ◽  
Novel Method

Aimed at solving the prominent issue of spacecraft high-frequency vibration suppression, this paper creatively puts forward a novel method based on the micro-gimbal moment of magnetically suspended flywheel with dynamic feedback and feedforward decoupling control. The dynamic model of the on-orbit magnetically suspended flywheel is established first and the decoupling control law of spacecraft as well as the micro-gimbal steering law of the magnetically suspended flywheel is designed. The disturbance compensator based on dynamic feedback–feedforward current is put forward to cancel the disturbance of spacecraft to the magnetically suspended flywheel. Then the nonlinear on-orbit magnetically suspended flywheel system is converted into a linear system without spacecraft coupling, and the state feedback decoupling controller is used to realize the high-precision micro-gimbal moment control of the magnetically suspended flywheel. The dynamic compensation filter is further developed to reduce the influence of unmodeled dynamics on decoupling performances, improving the rate of convergence of vibration suppression. The above three components constitute together the dynamic feedback and feedforward decoupling controller. The simulation results show the effectiveness and superiority of this method.

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