Study of Adaptive Variable Structure Attitude Control and Its Full Physical Simulation of Multi-body Satellite Antenna Drive Control

2009 ◽  
Author(s):  
Jie Jia ◽  
Luo Xutao ◽  
Yongyuan Qin
Keyword(s):  
Attitude Control ◽  
Physical Simulation ◽  
Variable Structure ◽  
Satellite Antenna ◽  
Drive Control ◽  
Multi Body

Design of Semi-Physical Simulation for Small Satellite by Virtual Display

2011 ◽  
Vol 130-134 ◽  
pp. 2684-2687 ◽  
Author(s):  
Kai Xu ◽  
Yan Lv ◽  
Guang Jin
Keyword(s):  
Control System ◽  
Real Time ◽  
Attitude Control ◽  
Physical Simulation ◽  
Simulation System ◽  
Space Environment ◽  
Small Satellite ◽  
Attitude Control System ◽  
Actual Environment ◽  
Virtual Display

Semi-physical simulation of attitude control system is the more synthetically test and verify for designing of small satellite control system. It is an important means of small satellite development. However, the results of current semi-physical simulation system have a lot of non-intuitive. Compare with the actual environment, the simulation environment still has striking disparity. So the shortcomings affect precision of simulation. Based on the virtual display technology, the group semi-physical simulation system has been constructed for attitude control of small satellite due to the combination with xPC real-time environment, the simulation computer, high-precision single-axis air-bearing turntable, reaction wheel, air thrust device, fiber gyroscopes, sensors synchronizer, power subsystem and wireless devices virtual display computer etc. Semi-physical simulation achieved the visual simulation in orbit and tracked new information of virtual environment of space into real-time simulation computer. Simulation results show that the simulation system for real-time attitude and orbit position of small satellite semi-physical simulation has an excellent display effect. At the same time, Real-time transfuse of orbit information provides a more accurate space environment simulation. The simulation system of small satellite attitude control to design and evaluate the more direct and convenient.

scholarly journals Dynamic Sliding Mode Controller with Variable Structure for Fast Satellite Attitude Maneuver

2021 ◽  
Vol 2021 ◽  
pp. 1-11
Author(s):  
Gao Shan ◽  
Li You ◽  
Xue Huifeng ◽  
Yao ShuYue
Keyword(s):  
Convergence Rate ◽  
Attitude Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
System Stability ◽  
System State ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Attitude Maneuver ◽  
Mode Parameter

In order to deal with the low convergence rate of the standard sliding mode in satellite attitude control, a novel variable structure sliding mode is constructed in this paper by designing the update law of the sliding mode parameter. By implementing this method, the advantage such as simple structure and strong robustness of the standard sliding mode are maintained and the system convergence rate is largely improved. The fixed sliding mode parameter is modified, and the update law is designed. When the system state is away from the sliding mode surface, the parameter is fixed, and when the system state approaches the sliding mode surface, the parameter begins to update. The constraint on control torque and angular velocity is taken into consideration, and the constraint on control parameters is given to ensure that the system state do not exceed its upper bound. System stability is proved by the Lyapunov stability theorem, and the superiority of the proposed controller is demonstrated by numerical simulation.

Double Closed-Loop Motor Modeling and Analysis for Lunar Rover Simulation

2012 ◽  
Vol 472-475 ◽  
pp. 1971-1976 ◽  
Author(s):  
Wei Dong Huang ◽  
Hong Kui Feng ◽  
Jin Song Bao ◽  
You Sheng Xu
Keyword(s):  
Pid Control ◽  
Control Algorithm ◽  
Dynamics Simulation ◽  
Motor Drive ◽  
Modeling And Analysis ◽  
Lunar Rover ◽  
System A ◽  
Drive Control ◽  
Body Dynamics ◽  
Multi Body

Motor drive control is the major study field in the development of lunar rover. Based on the double-closed DC loop adjustable-speed system, a motor drive simulation module using a position recursive PID control algorithm is developed, which is integrated into the multi-body dynamics simulation system, to carry out the whole lunar rover simulation. And the cruise process of lunar rover locomotion in the complex lunar terrain is simulated in a virtual environment.

Variable Structure Control of an Underactuated Air Spindle Testbed

2004 ◽  
Author(s):  
Hashem Ashrafiuon
Keyword(s):  
Attitude Control ◽  
Degrees Of Freedom ◽  
Variable Structure Control ◽  
Variable Structure ◽  
Vertical Axis ◽  
Lyapunov Theory ◽  
Control Approach ◽  
Structure Control ◽  
Sliding Surfaces ◽  
Air Spindle

A robust control algorithm is developed for attitude control of an air spindle testbed based on variable structure control. The variable structure control approach is formulated for underactuated systems with actuated accelerations as control inputs. First order sliding surfaces are defined per actuated degrees of freedom as a linear combination of the tracking position and velocity errors of both actuated and unactuated coordinates. The controller law is determined based on Lyapunov theory and is shown to be asymptotically stable for the tiled air spindle axis where gravitational effects are included but only marginally stable for the vertical axis. Multiple step sliding surfaces are proposed to achieve asymptotic stability in the latter case. Simulations of the controller performance verify its effectiveness and accuracy.

scholarly journals Research on Trajectory Planning and Tracking of Hexa-copter

2018 ◽  
Vol 173 ◽  
pp. 02008
Author(s):  
Qiyu Wang ◽  
Huijie Zhang ◽  
Jinrong Han
Keyword(s):  
Trajectory Planning ◽  
Flight Control ◽  
Attitude Control ◽  
Control Method ◽  
Sliding Mode ◽  
Interpolation Method ◽  
Spline Interpolation ◽  
Variable Structure ◽  
Flight Trajectory ◽  
Attitude Stability

In this paper, the flight control problem of hexa-copter is studied in detail from threedimensional trajectory planning to tracking. Then the cubic spline interpolation method is used to generate the trajectory by using these time marked waypoints. The flight trajectory curve produced by this method is smooth, twice differentiable, and it is easy to control implementation. The flight dynamics model of the UAV has the characteristics of multi-input multi-output, strong coupling, under-actuation, severe nonlinearity and external environmental disturbance. In order to improve the accuracy of flight trajectory and the stability of attitude control, a multi-loop sliding mode variable structure control method is proposed to achieve the hexa-copter flight trajectory tracking. The simulation results show that this method can track the predetermined flight trajectory and keep the attitude stability of the UAV normally.

Study on control strategies for an antenna servo system on a carrier under large disturbance

2018 ◽  
Vol 41 (9) ◽  
pp. 2545-2554
Author(s):  
Yongdong Cheng ◽  
Jun Jiang
Keyword(s):  
Attitude Control ◽  
Control Strategies ◽  
Servo System ◽  
Cable Vibration ◽  
Vibration Isolators ◽  
Reaching Law ◽  
Exponential Reaching Law ◽  
Multi Body ◽  
Control Accuracy ◽  
Large Disturbance

In this paper, control strategies and vibration isolation methods are investigated in order to enhance the attitude control accuracy of an antenna servo system on a carrier under large disturbance. First, the multi-body dynamical equations of the antenna servo system on a carrier incorporated with six wire-cable vibration isolators are derived. Then, an improved adaptive variable-rated exponential reaching law is proposed, and the non-singular terminal sliding mode control is designed based on the nonlinear multi-body model. Finally, simulations are carried out and results show that excellent control accuracies for both the azimuth and the pitch of the antenna can be achieved by the proposed control method, specifically with a shorten reaching time in the cases of holding a fixed angle and tracking a sinusoidal motion that is better than the existing adaptive variable-rated exponential reaching law. Furthermore, the six wire-cable vibration isolators with hysteretic characteristics of restoring forces are adopted that can effectively isolate the large disturbance transmitted from the carrier to the antenna servo system and are shown to be able to further improve the attitude control accuracy.

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