scholarly journals Finite-Time Control Algorithm Based on Modal State Observer for Flexible Satellite Attitude Tracking

IEEE Access ◽  
2020 ◽  
Vol 8 ◽  
pp. 184722-184730
Author(s):  
Sijia Li ◽  
Qiang Wu
Keyword(s):  
Finite Time ◽  
Control Algorithm ◽  
State Observer ◽  
Time Control ◽  
Satellite Attitude ◽  
Attitude Tracking

Finite time control strategy for satellite attitude maneuver based on hybrid actuator

2017 ◽  
Vol 40 (9) ◽  
pp. 2798-2806 ◽  
Author(s):  
Dong Ye ◽  
Xiao Zhang ◽  
Xucheng Wan ◽  
Zhaowei Sun
Keyword(s):  
Control Strategy ◽  
Finite Time ◽  
Sliding Mode ◽  
External Disturbance ◽  
Reference Trajectory ◽  
Terminal Sliding Mode ◽  
Time Control ◽  
Satellite Attitude ◽  
Attitude Maneuver ◽  
Attitude Tracking

In this paper, a Nonsingular Terminal Sliding Mode Control (NTSMC) strategy is investigated to address the finite-time attitude tracking problem of a rigid spacecraft. Hybrid thruster and flywheel actuator system is used for rapid reorientation under external disturbance. The reference torque is obtained from time-optimal attitude trajectory, and it is exerted on the satellite by thrusters in the form of feedforward compensation. Owing to thruster output torque deviation, initial measurement error and external disturbances, the practical trajectory of a satellite would deviate from reference trajectory. In order for the satellite to track the reference trajectory in finite time, the correction torque is deduced based on the error between reference trajectory and real-time measurements, and then applied through flywheels in the form of feedback compensation. The NTSMC method is used to solve nonsingular problem and to improve the control precision of the satellite attitude tracking issue. The numerical simulation results show that this control strategy is effective and it has great robustness.

Quaternion-based finite time control for spacecraft attitude tracking

2011 ◽  
Vol 69 (1-2) ◽  
pp. 48-58 ◽  
Author(s):  
Shunan Wu ◽  
Gianmarco Radice ◽  
Yongsheng Gao ◽  
Zhaowei Sun
Keyword(s):  
Finite Time ◽  
Spacecraft Attitude ◽  
Time Control ◽  
Attitude Tracking

Hovering control for quadrotor aircraft based on finite-time control algorithm

2017 ◽  
Vol 88 (4) ◽  
pp. 2359-2369 ◽  
Author(s):  
Wenwu Zhu ◽  
Haibo Du ◽  
Yingying Cheng ◽  
Zhaobi Chu
Keyword(s):  
Finite Time ◽  
Control Algorithm ◽  
Time Control ◽  
Quadrotor Aircraft ◽  
Hovering Control

Finite-Time Disturbance Observer Design and Attitude Tracking Control of a Rigid Spacecraft

2017 ◽  
Vol 139 (6) ◽  
Author(s):  
Qixun Lan ◽  
Chunjiang Qian ◽  
Shihua Li
Keyword(s):  
Finite Time ◽  
Disturbance Observer ◽  
Observer Design ◽  
Design Approach ◽  
Control Approach ◽  
Time Control ◽  
Time Simulation ◽  
Attitude Tracking ◽  
Rigid Spacecraft ◽  
Attitude Tracking Control

This paper considers the problem of finite-time disturbance observer (FTDO) design and the problem of FTDO based finite-time control for systems subject to nonvanishing disturbances. First of all, based on the homogeneous systems theory and saturation technique, a continuous FTDO design approach is proposed. Then, by using the proposed FTDO design approach, a FTDO is constructed to estimate the disturbances that exist in a rigid spacecraft system. Furthermore, based on a baseline finite-time control law and a feedforward compensation term produced by the FTDO, a composite controller is constructed for the rigid spacecraft system. It is shown that the proposed composite controller will render the rigid spacecraft track the desired attitude trajectory in a finite-time. Simulation results are included to demonstrate the effectiveness of the proposed control approach.

scholarly journals Robust Finite-Time Control Algorithm Based on Dynamic Sliding Mode for Satellite Attitude Maneuver

Mathematics ◽  
2021 ◽  
Vol 10 (1) ◽  
pp. 111
Author(s):  
You Li ◽  
Haizhao Liang
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Time Stability ◽  
Finite Time Stability ◽  
Time Control ◽  
Satellite Attitude ◽  
Attitude Maneuver ◽  
Mode Parameter ◽  
Fixed Axis ◽  
System Robustness

Robust finite-time control algorithms for satellite attitude maneuvers are proposed in this paper. The standard sliding mode is modified, hence the inherent robustness could be maintained, and this fixed sliding mode is modified to dynamic, therefore the finite-time stability could be achieved. First, the finite -time sliding mode based on attitude quaternion is proposed and the loose finite-time stability is achieved by enlarging the sliding mode parameter. In order to get the strict finite-time stability, a sliding mode based on the Euler axis is then given. The fixed norm property of the Euler axis is used, and a sliding mode parameter without singularity issue is achieved. System performance near the equilibrium point is largely improved by the proposed sliding modes. The singularity issue of finite-time control is solved by the property of rotation around a fixed axis. System finite-time stability and robustness are analyzed by the Lyapunov method. The superiority of proposed controllers and system robustness to some typical perturbations such as disturbance torque, model uncertainty and actuator error are demonstrated by simulation results.

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