scholarly journals Adaptive Finite-Time Command Filtered Fault-Tolerant Control for Uncertain Spacecraft with Prescribed Performance

Complexity ◽  
2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Zhongtian Chen ◽  
Qiang Chen ◽  
Xiongxiong He ◽  
Mingxuan Sun
Keyword(s):  
Finite Time ◽  
Controller Design ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
External Disturbance ◽  
Fault Tolerant Control ◽  
Prescribed Performance ◽  
Attitude Stabilization ◽  
Virtual Control ◽  
System Output

In this paper, an adaptive finite-time fault-tolerant control scheme is proposed for the attitude stabilization of rigid spacecrafts. A first-order command filter is presented at the second step of the backstepping design to approximate the derivative of the virtual control, such that the singularity problem caused by the differentiation of the virtual control is avoided. Then, an adaptive fuzzy finite-time backstepping controller is developed to achieve the finite-time attitude stabilization subject to inertia uncertainty, external disturbance, actuator saturation, and faults. Through using an error transformation, the prescribed performance boundary is incorporated into the controller design to guarantee the prescribed performance of the system output. Numerical simulations demonstrate the effectiveness of the proposed scheme.

Neural network-based adaptive fault tolerant tracking control for unmanned autonomous helicopters with prescribed performance

2019 ◽  
Vol 233 (12) ◽  
pp. 4350-4362 ◽  
Author(s):  
Kun Yan ◽  
Mou Chen ◽  
Qingxian Wu
Keyword(s):  
Fault Tolerant ◽  
External Disturbance ◽  
Tracking Error ◽  
Fault Tolerant Control ◽  
Actuator Fault ◽  
Error Performance ◽  
System Uncertainty ◽  
Prescribed Performance ◽  
Medium Scale ◽  
Autonomous Helicopter

In this paper, the issue of prescribed performance-based fault tolerant control is investigated for the medium-scale unmanned autonomous helicopter with external disturbance, system uncertainty and actuator fault. The altitude and attitude combination unmanned autonomous helicopter model is established. An error transformation function is proposed to guarantee that the tracking error satisfies the prescribed performance. The parameter adaptation method is adopted to handle the external unknown disturbance and the radial basis function neural networks are employed to approximate the interaction functions including the system uncertainty. The auxiliary system is introduced to weaken the effect of actuator fault, which can effectively avoid the singularity. Based on the backstepping control technology, an adaptive neural fault tolerant control scheme is developed to ensure the boundness of all closed-loop system signals and the specified tracking error performance. Simulation studies on the medium-scale unmanned autonomous helicopter are performed to demonstrate the efficiency of the designed control strategy.

scholarly journals Fault Diagnosis and Reconfigurable Control for Commercial Aircraft with Multiple Faults and Actuator Saturation

Aerospace ◽  
2021 ◽  
Vol 8 (4) ◽  
pp. 108
Author(s):  
Yishi Liu ◽  
Sheng Hong ◽  
Enrico Zio ◽  
Jianwei Liu
Keyword(s):  
Fault Diagnosis ◽  
Control Method ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
External Disturbance ◽  
Fault Tolerant Control ◽  
Adaptive Method ◽  
Reconfigurable Control ◽  
Multiple Faults ◽  
The Stability

Active fault-tolerant control systems perform fault diagnosis and reconfigurable control. There is a bidirectional uncertainty between them, and an integrated scheme is proposed here to account for that. The system considers both actuator and sensor faults, as well as the external disturbance. The diagnostic module is designed using an unknown input observer, and the controller is constructed on the basis of an adaptive method. The integrated strategy is presented, and the stability of the overall system is analyzed. Moreover, different kinds of anti-windup techniques are utilized to modify the original controllers, because of the different controller structures. A simulation of the integrated anti-windup fault-tolerant control method is demonstrated using a numerical model of Boeing 747. The results show that it can guarantee the stability of the post-fault aircraft and increase the control performance for the overall faulty system.

Fault-tolerant control considering time-varying bounds on faults

2017 ◽  
Vol 40 (10) ◽  
pp. 2982-2990 ◽  
Author(s):  
Mahmood Khatibi ◽  
Mohammad Haeri
Keyword(s):  
Controller Design ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
Domain Of Attraction ◽  
Fault Tolerant Control ◽  
Linear Matrix ◽  
Time Varying ◽  
Optimization Framework ◽  
Aerial Vehicle ◽  
Special Case

This paper presents a novel fault-tolerant control strategy to compensate the time-varying loss of actuators’ effectiveness. It considers intermediate situations where the fault is not determined precisely (unlike active approaches) but overall estimations about its rate and final value are available through the previous experiences and/or experiments. Based on the estimations, two upper and lower time-varying bounds on the actuators’ effectiveness are established to be exploited in the procedure of controller design. In a special case, where these bounds are constant, the method will be reduced to the conventional passive approach. Also, actuator saturation and the effects of [Formula: see text] disturbances are considered in the research. To tackle the conflict between attenuating the effect of L∞ disturbances and enlarging the domain of attraction, a linear matrix inequality optimization framework is suggested. The proposed method is implemented on a model of an unmanned aerial vehicle and the results are discussed.

scholarly journals Fractional-Order Finite-Time, Fault-Tolerant Control of Nonlinear Hydraulic-Turbine-Governing Systems with an Actuator Fault

Energies ◽  
2020 ◽  
Vol 13 (15) ◽  
pp. 3812
Author(s):  
Ying Yang ◽  
Bin Wang ◽  
Yuqiang Tian ◽  
Peng Chen
Keyword(s):  
Power Systems ◽  
Power System ◽  
Fractional Order ◽  
Finite Time ◽  
Control Method ◽  
Fault Tolerant ◽  
External Disturbance ◽  
Fault Tolerant Control ◽  
Hydraulic Turbine ◽  
Actuator Fault

Hydropower units undertake tasks such as peak shaving, frequency modulation, and providing accident reserves in the power system. With the increasing capacity and structural complexity of power systems, hydropower units have become more important. Hydraulic-turbine-governing systems (HTGSs) need to have higher control performance and automation levels to meet the higher regulatory requirements of the power system. To achieve high-quality control, we proposed a new finite-time, fault-tolerant control method for HTGSs with an actuator fault. First, a fractional-order model for HTGSs with uncertainty, external disturbance, and an actuator fault was introduced. Second, a fault estimator that could quickly track the fault signal for an actuator fault was proposed. Then, based on the fractional-order finite-time stability theorem, a finite-time, fault-tolerant controller was proposed for the stabilization of an HTGS. Furthermore, a controller was developed as a fractional differential form combined with a smooth bounded arctangent function to effectively suppress jitters and uncertainties. Finally, numerical experimental results verified the validity and robustness of the proposed scheme.

Fault-tolerant control for multiple networked spacecraft under actuator saturation

2016 ◽  
Vol 231 (3) ◽  
pp. 558-569 ◽  
Author(s):  
Ning Dong ◽  
Binbin Yuan ◽  
Pingli Lu
Keyword(s):  
Neural Network ◽  
Adaptive Learning ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
Sliding Mode ◽  
Learning Algorithm ◽  
External Disturbance ◽  
Fault Tolerant Control ◽  
Lyapunov Theory ◽  
Attitude Tracking

In this paper, fault-tolerant attitude tracking control problem is investigated for multiple spacecraft formation flying system with external disturbance, actuator saturation, and faults. A quaternion-based adaptive fault-tolerant control law is proposed based on input normalized neural network. The desired nonlinear smooth function is approximated by using input normalized neural network with an adaptive learning algorithm, and no prior knowledge about spacecraft dynamics is required. Meanwhile, in order to guarantee that the output of input normalized neural network used in the controller is bounded by the corresponding bound of the approximated unknown function, a modified adaptive law is designed to revise the sliding mode manifold. Moreover, the stability of system can be guaranteed by Lyapunov theory. Finally, the validity of the proposed control algorithm is verified through numerical simulations.

Sign in / Sign up

Export Citation Format

Share Document