Simple Adaptive Control with PID for MIMO Fault Tolerant Flight Control Design

2016 ◽  
Author(s):  
Taishi Nishiyama ◽  
Shinji Suzuki ◽  
Masayuki Sato ◽  
Kazuya Masui
Keyword(s):  
Adaptive Control ◽  
Flight Control ◽  
Fault Tolerant ◽  
Control Design

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 Reconfigurability analysis for reliable fault-tolerant control design

2011 ◽  
Vol 21 (3) ◽  
pp. 431-439 ◽  
Author(s):  
Ahmed Khelassi ◽  
Didier Theilliol ◽  
Philippe Weber
Keyword(s):  
Flight Control ◽  
Fault Tolerant ◽  
Control Design ◽  
Fault Tolerant Control ◽  
Admissible Solution ◽  
Reliability Evaluation ◽  
Control Application ◽  
And Control ◽  
The Relationship ◽  
Control Reconfigurability

Reconfigurability analysis for reliable fault-tolerant control design In this paper the integration of reliability evaluation in reconfigurability analysis of a fault-tolerant control system is considered. The aim of this work is to contribute to reliable fault-tolerant control design. The admissibility of control reconfigurability is analyzed with respect to reliability requirements. This analysis shows the relationship between reliability and control reconfigurability defined generally through Gramian controllability. An admissible solution for reconfigurability is proposed according to reliability evaluation based on energy consumption under degraded functional conditions. The proposed study is illustrated with a flight control application.

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.

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