https://users.encs.concordia.ca/~ymzhang/publications/ARC32-2-98Zhang_pp.229-252.pdf

Bibliographical review on reconfigurable fault-tolerant control systems

Fault-Tolerant Control: The 1997 Situation

The fault-tolerant control problem belongs to the domain of complex control systems in which inter-control-disciplinary information and expertise are required. This paper outlines the state of the art in a field which remains largely a theoretical topic with most application studies based upon aerospace systems. The directions in which the subject is going are summarised and some pointers are given as to the likely future issues and where new research effort is required. The paper provides a basic literature review covering most areas of fault-tolerant control.

Fault-tolerant control systems: the 1997 situation

A fault-tolerant control system (FTCS) design technique against stuck actuators is investigated using an iterative learning observer (ILO). The principle of the proposed fault-tolerant control (FTC) is to design a reconfigurable controller using estimated system states, relying on control input adjustments on the redundant actuators to compensate for the effects of stuck actuators. The amount of adjustment is updated based on the transient of fault compensation. The ILO provides both the estimates of the system states and the information on such transients. Multiple faults can also be dealt with. The fault compensation can be carried out swiftly due to the rapid convergence of the ILO. It is shown that the proposed FTCS ensures that the system follows the reference model under both normal conditions and with some stuck actuators. The closed-loop stability of the system is established, and the performance is evaluated using the lateral dynamics of an F-8 aircraft model.

Fault-tolerant control against stuck actuator faults

There are two main approaches to fault-tolerant control: passive and active.This thesis presents both methods for passive and for active FTC.

Robust fault-tolerant control

This paper addresses flight control system synthesis and the accommodation of controlled plant variation in an aircraft design envelope by using the frequency domain based quantitative feedback theory (QFT) robust control system design method. Plant variations considered include varying flight conditions in the flight envelope and damage to aerodynamic control surfaces. A robust flight control system is designed for the aircraft's longitudinal and lateral directional channels and validated with simulations containing nonlinear saturation elements. © 1997 by John Wiley & Sons, Ltd. This paper was produced under the auspices of the US Government and it is therefore not subject to copyright in the US.

Fault tolerant control system: qft design

This paper addresses flight control system synthesis and the accommodation of controlled plant variation in an aircraft design envelope by using the frequency domain based quantitative feedback theory robust control system design method The plant variations considered include varying flight conditions in the flight envelope and damage to aerodynamic control surfaces A digital flight controller for the aircraft's longitudinal channel is designed and validated with simulations containing nonlinear saturation elements

http://ieeexplore.ieee.org/iel3/3920/11350/00529234.pdf

QFT applied to fault tolerant flight control system design

A controlled plant's dynamics can very significantly if the operating points change. This presents problems for flight control system synthesis procedures based on pointwise designs, as aircraft dynamics vary widely within the flight envelope. This paper addresses flight control system synthesis and the accommodation of controlled plant variation in its design envelope by using the frequency domain based quantitative feedback theory multiple-input multiple-output robust control system design method. Plant variations considered include varying flight conditions in the flight envelope and damage to aerodynamic control surfaces. The aircraft used in the design is an unmanned research vehicle owned by the United States Air Force Wright Laboratory. Digital flight controllers for the aircraft's longitudinal and lateral channels and an outer-loop autopilot are designed and validated with simulations containing nonlinear saturation elements. >

M.S. Keating

Papers

Fault tolerant control system: qft design

QFT applied to fault tolerant flight control system design

Damaged aircraft control using a QFT designed flight controller