Impulsive control for attitude stabilization in the presence of unknown bounded external disturbances

2021 ◽  
Author(s):  
Bangxin Jiang ◽  
Jianquan Lu ◽  
Xiaodi Li ◽  
Kaibo Shi
Keyword(s):  
Impulsive Control ◽  
External Disturbances ◽  
Attitude Stabilization

scholarly journals Impulsive Flocking of Dynamical Multiagent Systems with External Disturbances

2017 ◽  
Vol 2017 ◽  
pp. 1-6
Author(s):  
Fujun Han ◽  
Yize Yang ◽  
Hong-Yong Yang
Keyword(s):  
Multiagent Systems ◽  
Disturbance Observer ◽  
Impulsive Control ◽  
Sufficient Condition ◽  
Complex Environment ◽  
Theoretical Conclusion ◽  
External Disturbances ◽  
Exogenous Disturbances ◽  
Simulation Results ◽  
Flocking Motion

Flocking motion of multiagent systems is influenced by various external disturbances in complex environment. By applying disturbance observer, flocking of multiagent systems with exogenous disturbances is studied. Based on the robust features of impulsive control, a distributed impulsive control protocol is presented with disturbance observer, and flocking motion of multiagent systems is analyzed. Moreover, a sufficient condition is obtained to ensure the flocking motion of multiagent systems following a leader. Finally, simulation results show the validity of the theoretical conclusion.

Robust Fault Tolerant Control for Spacecraft Attitude Stabilization Under Actuator Faults and Bounded Disturbance

2011 ◽  
Vol 133 (5) ◽  
Author(s):  
Bing Xiao ◽  
Qinglei Hu ◽  
Michael I. Friswell
Keyword(s):  
Closed Loop ◽  
Fault Tolerant ◽  
Fault Detection And Isolation ◽  
Spacecraft Attitude ◽  
Actuator Faults ◽  
Closed Loop System ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Bounded Disturbance ◽  
Loss Of Actuator Effectiveness

This paper investigates the design of spacecraft attitude stabilization controllers that are robust against actuator faults and external disturbances. A nominal controller is developed initially, using the adaptive backstepping technique, to stabilize asymptotically the spacecraft attitude when the actuators are fault-free. Additive faults and the partial loss of actuator effectiveness are considered simultaneously and an auxiliary controller is designed in addition to the nominal controller to compensate for the system faults. This auxiliary controller does not use any fault detection and isolation mechanism to detect, separate, and identify the actuator faults online. The attitude orientation and angular velocity of the closed-loop system asymptotically converge to zero despite actuator faults providing the nominal attitude system is asymptotically stable. Numerical simulation results are presented that demonstrate the closed-loop performance benefits of the proposed control law and illustrate its robustness to external disturbances and actuator faults.

Three-axis attitude stabilization of a flexible satellite using non-linear PD controller

2016 ◽  
Vol 40 (2) ◽  
pp. 591-605 ◽  
Author(s):  
Babak Baghi ◽  
Mansour Kabganian ◽  
Reza Nadafi ◽  
Ehsan Arabi
Keyword(s):  
Control System ◽  
Direct Method ◽  
Pd Controller ◽  
Control Torque ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Control Moment Gyroscope ◽  
Attitude Stabilization ◽  
Control Moment ◽  
Non Linear

In this paper, after complete modelling of a flexible satellite equipped with a control moment gyroscope (CMG) actuator, it is shown that a PD-like controller can globally asymptotically stabilize this satellite by using Lyapunov’s direct method. Despite the simplicity, simulations show that the controller can stabilize the flexible satellite in a three-axis manoeuvre even in the presence of external disturbances. Then, using a non-linear variable gains PD controller, which only uses angular velocity of the rigid body and the attitude parameters as the inputs, the performance of the control system is improved in some important aspects such as reducing maximum control torque, reducing maximum peak of deflection of the appendages and increasing robustness of the controller against the orbital disturbances. In addition, locally asymptotically stability of the non-linear variable gain PD controller is guaranteed using a novel Lyapunov candidate function. Considering the difficulty in measuring the appendages’ deflection and the primarily existence of parameter uncertainties, and as this controller is independent of changes in these parameters, such a control system is very useful and applicable. In order to validate the system’s mathematical model and the control system performance, an exact model of the satellite is constructed in the ADAMS/View software that is linked to the MATLAB software. The efficacy of the proposed approach is demonstrated by several numerical examples.

scholarly journals Attitude Tracking of Rigid Spacecraft with Actuator Saturation and Fault Based on a Compound Control

2020 ◽  
Vol 2020 ◽  
pp. 1-14
Author(s):  
Chunhua Cheng ◽  
Hang Yang ◽  
Qian Wang ◽  
Lin Li ◽  
Qiang Han ◽  
...  
Keyword(s):  
Disturbance Rejection ◽  
Control Input ◽  
Tracking Problem ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Actuator Failures ◽  
Compound Control ◽  
Active Disturbance Rejection ◽  
Attitude Tracking ◽  
Modeling Uncertainties

A compound control based on active disturbance rejection control (ADRC) scheme and slide mode control (SMC) is proposed to investigate the attitude tracking problem for a spacecraft with modeling uncertainties, external disturbances, actuator failures, and actuator saturations simultaneously. A positive term including control input is separated from the system, and then, the active disturbance rejection concept and the extended state observer (ESO) are applied to deal with the general uncertain item caused by uncertainties, external disturbances, actuator failures, and actuator saturations. The sliding mode surface is designed to transform the attitude tracking problem into attitude stabilization problem. In order to deal with the actuator saturations, a saturation degree coefficient and its corresponding adaptive law are introduced. Compared to other existing references, the proposed scheme does not need to know the structure or upper bound information of the inertial matrix uncertainties and external disturbances. Finally, the stability of the closed-loop system is analyzed by using input to state stability theory. Simulation results are given to verify the effectiveness of the proposed scheme. More importantly, the proposed technique can also be applied to the attitude stabilization of other aircraft, such as the attitude of unmanned aerial vehicle and helicopter in maritime rescue.

scholarly journals Finite-Time Stabilization Control for a Rigid Spacecraft under Parameter Uncertainties

2014 ◽  
Vol 2014 ◽  
pp. 1-11 ◽  
Author(s):  
Aihua Zhang ◽  
Jianfei Ni ◽  
Xing Huo
Keyword(s):  
Finite Time ◽  
Parameter Uncertainties ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Stabilization Control ◽  
Time Control ◽  
Control Scheme ◽  
Lyapunov Stability Analysis ◽  
Homogeneous Method ◽  
Rigid Spacecraft

A novel finite-time control scheme is investigated for a rigid spacecraft in present of parameter uncertainties and external disturbances. Firstly, the spacecraft mathematical model is transformed into a cascading system by introducing an adaptive variable. Then a novel finite-time attitude stabilization control scheme for a rigid spacecraft is proposed based on the homogeneous method. Lyapunov stability analysis shows that the resulting closed-loop attitude system is proven to be stable in finite time without parameter uncertainties and asymptotically stable with parameter uncertainties. Finally, numerical simulation examples are also presented to demonstrate that the control strategy developed is feasible and effective for spacecraft attitude stabilization mission.

Partial stabilization of underactuated post-capture combination with inaccurate measurement information and unknown disturbances

2017 ◽  
Vol 40 (13) ◽  
pp. 3625-3639 ◽  
Author(s):  
Shiyu Chen ◽  
Jianping Yuan ◽  
Zheng Wang ◽  
Zhanxia Zhu
Keyword(s):  
Numerical Simulations ◽  
Sliding Mode ◽  
Measurement Information ◽  
Sliding Mode Controller ◽  
Attitude Dynamics ◽  
Additional Consideration ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Adaptive Sliding Mode Controller ◽  
Unknown Disturbances

This paper aims to address the attitude stabilization issue of post-capture combination with underactuated actuators, measurement inaccuracy and unknown external disturbances during on-orbit servicing. A precise and practical form of underactuated attitude dynamics is proposed for the asymmetric combination with two control torques. With the adopted partial stabilization strategy, a sliding mode controller is first proposed to achieve partial stabilization of the combination against the effect of unknown external disturbances. Through the additional consideration of the measurement inaccuracy in the inertia tensor and the mass centroid, an underactuated adaptive sliding mode controller with compensation laws is proposed in presence of uncertainties and disturbances. Numerical simulations validate the effectiveness of proposed partial attitude stabilization controllers.

Constrained Robust Control for Spacecraft Attitude Stabilization Under Actuator Delays and Faults

2017 ◽  
Vol 139 (5) ◽  
Author(s):  
Alireza Safa ◽  
Mahdi Baradarannia ◽  
Hamed Kharrati ◽  
Sohrab Khanmohammadi
Keyword(s):  
Disturbance Observer ◽  
Sufficient Conditions ◽  
Control Input ◽  
Model Uncertainties ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Delay Effects ◽  
Rigid Spacecraft ◽  
Backstepping Controller ◽  
And Control

This paper deals with the attitude stabilizing control problem for a rigid spacecraft in the presence of model uncertainties, external disturbances, and actuator faults when delay effects and control input constraints are taken into consideration. First, a backstepping method is introduced in the control design for compensating unknown delays in inputs. Then, a disturbance observer is investigated for estimating model uncertainties, external disturbances, and actuator fault effects. The backstepping controller is augmented with the reconstructed information provided by the disturbance observer to make the closed-loop system insensitive to disturbances and faults. Next, the proposed observer–controller structure is redesigned to deal with control constraints. Rigorous proofs show that the developed control under simple sufficient conditions can render the system globally input-to-state stable (ISS). Numerical simulations are presented to illustrate the effectiveness of the proposed controllers.

Attitude stabilization of flexible spacecraft under limited communication with reinforced robustness

2019 ◽  
Vol 41 (16) ◽  
pp. 4475-4487 ◽  
Author(s):  
Syed Muhammad Amrr ◽  
M Nabi
Keyword(s):  
Attitude Control ◽  
Communication Channel ◽  
Equilibrium Points ◽  
Flexible Spacecraft ◽  
Sampled Data ◽  
External Disturbances ◽  
Attitude Stabilization ◽  
Potential Alternative ◽  
Bandwidth Constraint ◽  
Event Based

This paper proposes a robust event-driven control for attitude regulation in flexible spacecraft affected by inertial parametric uncertainties and external disturbances. The bandwidth constraint of the communication channel between controller and system requires an event-based control design. Under the action of proposed control law, the system trajectories are ensured to be uniformly ultimately bounded (UUB) in a small vicinity of their equilibrium points. Apart from the boundedness of states, the proposed event-triggered controller also satisfies bandwidth restrictions by achieving a substantially low control usage. The results obtained from numerical simulations are indeed encouraging. It demonstrates the proposed controller as a potential alternative to the periodically sampled data controllers. Moreover, the proposed control strategy successfully eludes the unwanted unwinding phenomenon encountered in quaternion based attitude control of the spacecraft.

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