Multivariable uniform finite-time output feedback reentry attitude control for RLV with mismatched disturbance

2018 ◽  
Vol 355 (8) ◽  
pp. 3470-3487 ◽  
Author(s):  
Bailing Tian ◽  
Hanchen Lu ◽  
Zongyu Zuo ◽  
Qun Zong
Keyword(s):  
Output Feedback ◽  
Finite Time ◽  
Attitude Control ◽  
Mismatched Disturbance

scholarly journals Finite-Time Attitude Control for Quadrotor with Input Constraints and Disturbances

2020 ◽  
Vol 2020 ◽  
pp. 1-11
Author(s):  
Zijun Gao ◽  
Jin Wang ◽  
Yaping Tian
Keyword(s):  
Output Feedback ◽  
Finite Time ◽  
Attitude Control ◽  
Closed Loop ◽  
Sliding Mode ◽  
Auxiliary Variable ◽  
System Stability ◽  
Terminal Sliding Mode ◽  
Command Signals ◽  
Adverse Influence

This paper investigates the adaptive output feedback attitude control of a quadrotor. First, a nonsingular terminal sliding-mode variable and auxiliary variable are introduced into a closed-loop structure. Meanwhile, a fuzzy logic system is incorporated into an adaptive algorithm to compensate for the adverse influence caused by lumped disturbances including system uncertainty and external disturbances on the attitude adjustment performance of a quadrotor. Then, a novel finite-time output feedback controller equipped with the saturation suppression algorithm is designed. Rigorous proof shows that the design control strategy ensures the closed-loop system stability and guarantees the attitude of the spacecraft to track desired command signals in finite time. Simulation results are presented to illustrate the performance of the proposed control scheme.

Finite-time output feedback control for the attitude of the spacecraft without unwinding

2017 ◽  
Vol 232 (8) ◽  
pp. 1421-1433 ◽  
Author(s):  
Yong Guo ◽  
Shen-Min Song ◽  
Xue-Hui Li ◽  
Zhibin Zhu
Keyword(s):  
Output Feedback ◽  
Finite Time ◽  
Attitude Control ◽  
Output Feedback Control ◽  
Rotation Matrix ◽  
Attitude Control System ◽  
Time Control ◽  
Attitude Error ◽  
Control Schemes ◽  
Homogeneous Method

This paper focuses on finite-time control in the attitude control system of the spacecraft based on the rotation matrix by using homogeneous method. Because the rotation matrix represents the set of attitudes both globally and uniquely, the system can overcome the drawback of unwinding which results in extra fuel consumption. In order to deal with actuator saturations, a finite-time controller is investigated by using the saturation function. Then, based on a novel filter, a finite-time output feedback controller with actuator saturations is designed. Theoretical analysis shows that the proposed controllers can make the attitude error converges to zero in finite time. Numerical simulations also demonstrate that the proposed control schemes are effective.

Finite-time output feedback attitude synchronization for multiple spacecraft

2017 ◽  
Vol 40 (10) ◽  
pp. 3023-3039 ◽  
Author(s):  
Qun Zong ◽  
Shikai Shao ◽  
Bailing Tian ◽  
Xiuyun Zhang ◽  
Wenjing Liu
Keyword(s):  
Angular Velocity ◽  
Output Feedback ◽  
Finite Time ◽  
Attitude Control ◽  
Sliding Mode ◽  
Lyapunov Theory ◽  
Calculation Algorithm ◽  
Terminal Sliding Mode ◽  
Multiple Spacecraft ◽  
Attitude Synchronization

Distributed attitude control for spacecraft formation without angular velocity measurement is complicated and challenging. Based on nonsingular terminal sliding mode, this paper designs two kinds of finite-time attitude synchronization controllers with inertia uncertainties and external disturbances. Aiming at calculating angular velocity in finite time, a nonlinear state observer and an angular velocity calculation algorithm are firstly developed. Then, two strategies for estimating reference signals and two distributed output feedback controllers, based on continuous adaptive technology and adaptive disturbance observer, are designed respectively. Different from existing results, the controllers are inherently continuous and the control chattering is greatly reduced. Also, the designed nonlinear observers need no prior knowledge on the upper bound of uncertain state and are proved finite-time convergent via Lyapunov theory. Finally, simulations and comparisons demonstrate the effectiveness of the proposed schemes.

Extended state observer–based output feedback control for spacecraft pose tracking with control input saturation

2021 ◽  
pp. 095441002110177
Author(s):  
Kejie Gong ◽  
Ying Liao ◽  
Yafei Mei
Keyword(s):  
Feedback Control ◽  
Output Feedback ◽  
Finite Time ◽  
Output Feedback Control ◽  
State Observer ◽  
Extended State Observer ◽  
Control Input ◽  
Extended State ◽  
Pose Tracking ◽  
Control Scheme

This article proposed an extended state observer (ESO)–based output feedback control scheme for rigid spacecraft pose tracking without velocity feedback, which accounts for inertial uncertainties, external disturbances, and control input constraints. In this research, the 6-DOF tracking error dynamics is described by the exponential coordinates on SE(3). A novel continuous finite-time ESO is proposed to estimate the velocity information and the compound disturbance, and the estimations are utilized in the control law design. The ESO ensures a finite-time uniform ultimately bounded stability of the observation states, which is proved utilizing the homogeneity method. A non-singular finite-time terminal sliding mode controller based on super-twisting technology is proposed, which would drive spacecraft tracking the desired states. The other two observer-based controllers are also proposed for comparison. The superiorities of the proposed control scheme are demonstrated by theory analyses and numerical simulations.

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