2306 Design and flight test of fault-tolerant control system using simple adaptive control method

2014 ◽  
Vol 2014.23 (0) ◽  
pp. 139-142
Author(s):  
Daichi Tokunaga ◽  
Kazuya Masui ◽  
Shinji Suzuki
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Control Method ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Flight Test

scholarly journals Flight Evaluation of Fault-tolerant Control System Using Simple Adaptive Control Method

2015 ◽  
Vol 99 ◽  
pp. 1035-1043 ◽  
Author(s):  
Daichi Tokunaga ◽  
Kazuya Masui ◽  
Shinji Suzuki
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Control Method ◽  
Fault Tolerant ◽  
Fault Tolerant Control

scholarly journals Active Fault-Tolerant Control Based on Multiple Input Multiple Output-Model Free Adaptive Control for Four Wheel Independently Driven Electric Vehicle Drive System

2019 ◽  
Vol 9 (2) ◽  
pp. 276 ◽  
Author(s):  
Yugong Luo ◽  
Yun Hu ◽  
Fachao Jiang ◽  
Rui Chen ◽  
Yongsheng Wang
Keyword(s):  
Control System ◽  
Active Fault ◽  
Control Method ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Drive System ◽  
Input Output ◽  
Vehicle Model ◽  
Model Free ◽  
Active Fault Tolerant Control

To solve the problems with the existing active fault-tolerant control system, which does not consider the cooperative control of the drive system and steering system or accurately relies on the vehicle model when one or more motors fail, a multi-input and multi-output model-free adaptive active fault-tolerant control method for four-wheel independently driven electric vehicles is proposed. The method, which only uses the input/output data of the vehicle in the control system design, is based on a new dynamic linearization technique with a pseudo-partial derivative, aimed at solving the complex and nonlinear issues of the vehicle model. The desired control objectives can be achieved by the coordinated adaptive fault-tolerant control of the drive and steering systems under different failure conditions of the drive system. The error convergence and input-output boundedness of the control system are proven by means of stability analysis. Finally, simulations and further experiments are carried out to validate the effectiveness and real-time response of the fault-tolerant system in different driving scenarios. The results demonstrate that our proposed approach can maintain the longitudinal speed error (within 3%) and lateral stability, thereby improving the safety of the vehicles.

Flight test of fault-tolerant flight control system using simple adaptive control with PID controller

2018 ◽  
Vol 90 (1) ◽  
pp. 210-218 ◽  
Author(s):  
Hidenobu Matsuki ◽  
Taishi Nishiyama ◽  
Yuya Omori ◽  
Shinji Suzuki ◽  
Kazuya Masui ◽  
...  
Keyword(s):  
Adaptive Control ◽  
Flight Control ◽  
Pid Controller ◽  
Control Method ◽  
Fault Tolerant ◽  
Flight Test ◽  
Static Stability ◽  
Flight Tests ◽  
Content Type ◽  
Sudden Reduction

Purpose This paper aims to demonstrate the effectiveness of a fault-tolerant flight control method by using simple adaptive control (SAC) with PID controller. Design/methodology/approach Numerical simulations and flight tests are executed for pitch angle and roll angle control of research aircraft MuPAL-α under the following fault cases: sudden reduction in aileron effectiveness, sudden reduction in elevator effectiveness and loss of longitudinal static stability. Findings The simulations and flight tests reveal the effectiveness of the proposed SAC with PID controller as a fault-tolerant flight controller. Practical implications This research includes implications for the development of vehicles’ robustness. Originality/value This study proposes novel SAC-based flight controller and actually demonstrates the effectiveness by flight test.

scholarly journals Fault-tolerant control system for the formation of carbon products

2021 ◽  
pp. 22-29
Author(s):  
Liudmyla Zhuchenko
Keyword(s):  
Control System ◽  
Linear Matrix Inequalities ◽  
Control Method ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Iterative Learning ◽  
Linear Matrix ◽  
Matrix Inequalities ◽  
Unknown Disturbances ◽  
Cyclic Processes

The production of carbon products is largely resource- and energy-intensive. That is why increasing the efficiency of this production is an urgent scientific and practical task, especially in modern conditions of constant growth of energy costs. An effective way to solve this problem is to create a modern process control system, taking into account possible failures of system components. A method for the synthesis of a fault-tolerant control system for the cyclic formation of carbon products has been developed, which takes into account control errors that are caused by malfunctions of controllers under conditions of unknown disturbances. According to the cyclic nature of the technological process under consideration, a control method with iterative learning was used in the synthesis of the control system. This method considers cyclic processes based on a two-dimensional model (2D model). The proposed control algorithm ensures the convergence of the control process with the task both in time and in each work cycle in order to promote the required quality of control even in the event of unknown disturbances and errors in the performance of controllers. The synthesis of the control system is based on the solution of a system of linear matrix inequalities. Based on the combination of a control method with iterative learning and a control method that takes into account failures in controllers, a method of constructing a fault-tolerant control system for the cyclic formation of carbon products has been synthesized to ensure acceptable operation of the control object in abnormal conditions. The control system has been synthesized by solving a system of linear matrix inequalities with the MATLAB software. In the future, it is necessary to consider optimal settings of the proposed control system and examine its effectiveness in comparison with conventional fault-tolerant systems for non-cyclic processes.

Reconfigurable Flight Control System Design Using Input-Output Information

2005 ◽  
Vol 219 (4) ◽  
pp. 277-285 ◽  
Author(s):  
S Hyung ◽  
Y Kim
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Flight Control ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Control Surface ◽  
Control Technique ◽  
Input Output ◽  
Discrete State ◽  
Output Information

An adaptive control algorithm using input-output information is proposed for designing an aircraft fault tolerant control system. An input-output model is derived on the basis of a discrete state-space system. The formulated input-output model has the same structure as the autoregressive moving average (ARMA) model does, and therefore, the conventional system identification method using recursive least square can be used to identify the system. To design a reconfigurable control system, an LQ tracker with output feedback scheme is adopted. During the recursive adaptive control process, the system model is updated periodically. The proposed algorithm is applicable to time-varying systems in real time. To validate the performance of the proposed adaptive fault tolerant control technique, numerical simulation of the high performance aircraft with control surface damage was performed.

Reconfiguration for Sensor Failure of Aero-Engine Electronic Control System Based on the MRAC

2014 ◽  
Vol 602-605 ◽  
pp. 1367-1371
Author(s):  
Zhi Bo Shi ◽  
Tao Liu ◽  
Dan Sun
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Control Strategy ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Mathematic Model ◽  
Electronic Control ◽  
Sensor Failure ◽  
Electronic Control System ◽  
Aero Engine

In the paper, the fault-tolerant control strategy for the aero-engine electronic control system is researched based on the Model Reference Adaptive Control method. In the design process, a new reference model design method is proposed with the Raccatti equation, which can guarantee the reconfiguration system have satisfactory performance. According to the sensor failure models, the failure system mathematic model is given. Lyapunov stability theory was applied to obtain the adaptive control law through design a Lyapunov function, which can ensure the strictly positive realness and global asymptotic stability for the reconfiguration control system. For the typical sensor failures, the reconfiguration effect with the control strategy is simulated and verified in the Matlab, which revealed that the aero-engine control system could operate well under the failure with the fault-tolerant control.

scholarly journals Fault tolerant control of a quadrotor using C 1 adaptive control

2016 ◽  
Vol 4 (1) ◽  
pp. 43-66 ◽  
Author(s):  
Dan Xu ◽  
James Ferris Whidborne ◽  
Alastair Cooke
Keyword(s):  
Adaptive Control ◽  
Fault Tolerance ◽  
Degrees Of Freedom ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Flight Test ◽  
Adaptive Controller ◽  
Content Type ◽  
Gyroscopic Effects ◽  
High Level

Purpose – The growing use of small unmanned rotorcraft in civilian applications means that safe operation is increasingly important. The purpose of this paper is to investigate the fault tolerant properties to faults in the actuators of an C 1 adaptive controller for a quadrotor vehicle. Design/methodology/approach – C 1 adaptive control provides fast adaptation along with decoupling between adaptation and robustness. This makes the approach a suitable candidate for fault tolerant control of quadrotor and other multirotor vehicles. In the paper, the design of an C 1 adaptive controller is presented. The controller is compared to a fixed-gain LQR controller. Findings – The C 1 adaptive controller is shown to have improved performance when subject to actuator faults, and a higher range of actuator fault tolerance. Research limitations/implications – The control scheme is tested in simulation of a simple model that ignores aerodynamic and gyroscopic effects. Hence for further work, testing with a more complete model is recommended followed by implementation on an actual platform and flight test. The effect of sensor noise should also be considered along with investigation into the influence of wind disturbances and tolerance to sensor failures. Furthermore, quadrotors cannot tolerate total failure of a rotor without loss of control of one of the degrees of freedom, this aspect requires further investigation. Practical implications – Applying the C 1 adaptive controller to a hexrotor or octorotor would increase the reliability of such vehicles without recourse to methods that require fault detection schemes and control reallocation as well as providing tolerance to a total loss of a rotor. Social implications – In order for quadrotors and other similar unmanned air vehicles to undertake many proposed roles, a high level of safety is required. Hence the controllers should be fault tolerant. Originality/value – Fault tolerance to partial actuator/effector faults is demonstrated using an C 1 adaptive controller.

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