Internal-mode based sliding mode variable structure attitude control of flexible spacecraft

2014 ◽  
Author(s):  
Xiaoxiao Jin ◽  
Zhong Wu
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
Flexible Spacecraft ◽  
Internal Mode ◽  
Sliding Mode Variable Structure

Summarization of Airship’s Attitude Control and Station-Keeping Control Methods

2012 ◽  
Vol 433-440 ◽  
pp. 6890-6895
Author(s):  
Guo Chang Hu ◽  
Mei Ping Wu ◽  
Yan Zhang
Keyword(s):  
Attitude Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
Control Methods ◽  
Station Keeping ◽  
Structure Control ◽  
Control Optimization ◽  
Disturbance Rejection Control ◽  
Optimization Control ◽  
Sliding Mode Variable Structure

As important parts of airship’s control systems, the attitude control and station-keeping control have important effects on the vehicle’s performance. This article discusses the control methods in present usage, which include PID control, robust control, optimization control, sliding mode variable structure control, auto-disturbance rejection control and other control methods. The application areas of the methods are discussed, and the developing direction is pointed at last. Introduction

Terminal Sliding Mode Control of a Lunar Lander with Electric Propulsion

2014 ◽  
Vol 494-495 ◽  
pp. 1195-1201
Author(s):  
Bo Yang ◽  
Jun Miao ◽  
Yong Yang
Keyword(s):  
Attitude Control ◽  
Electric Propulsion ◽  
Control Method ◽  
Sliding Mode ◽  
Variable Structure ◽  
Control Force ◽  
Terminal Sliding Mode ◽  
Control Precision ◽  
Sliding Mode Variable Structure ◽  
Lunar Lander

This paper presents an attitude control method based on electric propulsion systems for the lunar lander that considers the important characteristics of nonlinearity and uncertainty of lunar soft landing maneuvers with large attitudes. The attitude control law is designed according to the terminal sliding mode variable structure control method. A soft lunar landing utilizing the proposed control method is simulated, and the results show that this attitude control system demonstrates superior global robustness, consumes less propellant, and can achieve higher precision than a conventional chemical propulsion-based control system. For a lunar lander with a pulse plasma thruster as the propulsion system, the attitude control precision of the system is 0.002 degrees when the attitude control force is 0.1 Newtons. When a conventional chemical, not electric, propulsion thruster is used, if the attitude control force decreases by one order of magnitude, then the control precision of the lunar lander decreases 10-fold. This study demonstrates that a terminal sliding mode variable structure control method combined with low level thrust electric propulsion can improve the precision of lunar soft landings.

scholarly journals Design of Quad-rotor Controller Based on Fractional Order Sliding Mode Control

CONVERTER ◽  
2021 ◽  
pp. 65-72
Author(s):  
Liumin Luo Et al.
Keyword(s):  
Sliding Mode Control ◽  
Fractional Order ◽  
Attitude Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
Reaching Law ◽  
Mode Control ◽  
Mode Index ◽  
Sliding Mode Variable Structure ◽  
Exponential Reaching Law

According to the chattering problems of traditional sliding mode index exponential reaching law, this paper proposes a fractional order sliding mode index exponential reaching law control strategy, which is applied to the quad-rotor helicopter attitude control. Combined the theory of fractional order calculus and sliding mode variable structure control theory, the fractional order sliding mode controller is designed. The method of  lyapunov analysis proves that this controller can make the system asymptotically stable. Simulation and experiments show that the proposed fractional order sliding mode control system not only undermines the chattering of traditional sliding mode exponential reaching law but also reduces the adjusting time and control margin of the system.

scholarly journals Synchronous Generator Rectification System Based on Double Closed-Loop Control of Backstepping and Sliding Mode Variable Structure

Electronics ◽  
2021 ◽  
Vol 10 (15) ◽  
pp. 1832
Author(s):  
Jinfeng Liu ◽  
Xin Qu ◽  
Herbert Ho-Ching Iu
Keyword(s):  
Closed Loop ◽  
Control Structure ◽  
Low Voltage ◽  
Sliding Mode ◽  
Variable Structure ◽  
Synchronous Generator ◽  
Closed Loop Control ◽  
High Current ◽  
Loop Control ◽  
Sliding Mode Variable Structure

Low-voltage and high-current direct current (DC) power supplies are essential for aerospace and shipping. However, its robustness and dynamic response need to be optimized further on some special occasions. In this paper, a novel rectification system platform is built with the low-voltage and high-current permanent magnet synchronous generator (PMSG), in which the DC voltage double closed-loop control system is constructed with the backstepping control method and the sliding mode variable structure (SMVS). In the active component control structure of this system, reasonable virtual control variables are set to obtain the overall structural control variable which satisfied the stability requirements of Lyapunov stability theory. Thus, the fast-tracking and the global adjustment of the system are realized and the robustness is improved. Since the reactive component control structure is simple and no subsystem has to be constructed, the SMVS is used to stabilize the system power factor. By building a simulation model and experimental platform of the 5 V/300 A rectification module based on the PMSG, it is verified that the power factor of the system can reach about 98.5%. When the load mutation occurs, the DC output achieves stability again within 0.02 s, and the system fluctuation rate does not exceed 2%.

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