Propulsion control of crippled aircraft by H/sub ∞/ model matching

Often, dynamical aircraft systems cannot always be accurate because some approximation assumptions, imprecisions or uncertainties may have been introduced or imposed during the modeling process. Mathematical models of aircraft systems always contain uncertain elements, which model the designer's lack of knowledge about some parameter values, disturbances and unmodeled dynamics. Using both Lyapunov's direct method and the linear matrix inequality approach, we develop the controller design procedure, and give a definite feel for stability analysis and robust control for aircraft systems with significant uncertainty. An example of an uncertain thrust vectoring aircraft is studied to illustrate our control design strategy.

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“…Consider the longitudinal model of the L1011 thrust vectoring aircraft described by the linear model (Jonckheere and Yu, 1999) …”

Section: Stabilization Of Uncertain Thrust Vectoring Aircraftmentioning

confidence: 99%

Robust Stabilization of Uncertain Aircraft Active Systems

Ibrir

Botez

2005

Journal of Vibration and Control

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“…[5] and [6] and the reference therein), classical approaches for LTI systems with gain scheduling, Linear Quadratic control theory, H ¥ optimal tracking solutions and sliding mode controllers ( [7]- [13]). Recently the Linear Matrix Inequality technique with 2 / H H ¥ requirements is applied to design flight control laws for LPV (linear parameter varying) aircraft models (see f.e.…”

Section: Introductionmentioning

confidence: 99%

Longitudinal flight multi condition control using robust PID controllers

Skarpetis¹,

Koumboulis²,

Ntellis³

2011

Etfa2011

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A multi flight condition aircraft control autopilot system is proposed to control the horizontal flight of an aircraft involving atmospheric gusts. The control system involves a robust PID controller that stabilizes the closed loop system for various flight conditions. Considering the stability derivatives of the aircraft and the velocity of the aircraft to be uncertain parameters the robust stabilizing and disturbance attenuation controller is designed to cover full envelop pitch control. The robust PID controller parameters are computed using a finite step algorithm based on a Hurwitz invariability technique. Solvability conditions are derived. Simulation results for four different flight conditions are presented indicating the satisfactory performance of the robust controller in the presence of atmospheric gusts.

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“…For example: pseudo-inverse methods [2]; H -control [3]; closedloop eigenstructure [4]; Optimal control [5]; model-predictive control [6] etc.…”

Section: Introductionmentioning

confidence: 99%

Fault-tolerant control of dynamic positioning vessel by means of a virtual thruster

Fu¹,

Ning²,

Wei³

2011

2011 IEEE International Conference on Mechatronics and Automation

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This paper presents a method for on-line reconfiguration of fault-tolerant control to dynamic positioning (DP) vessel by means of a virtual thruster after the occurrence of thruster failures. First, a brief review of the main idea of a virtual actuator is presented. Then a suitable linear state-space model of DP vessel is derived which consists of motions in 3 DOF. A virtual thruster design is finished which combines with virtual actuator and DP vessel model. The reconfiguration block of virtual thruster generates suitable inputs for the faulty vessel based on the output of the nominal controllers. At last, the feasible and effective of this method are demonstrated by a simulation of a DP vessel.

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Propulsion control of crippled aircraft by H/sub ∞/ model matching

Cited by 31 publications

References 12 publications

Robust Stabilization of Uncertain Aircraft Active Systems

Robust Stabilization of Uncertain Aircraft Active Systems

Longitudinal flight multi condition control using robust PID controllers

Fault-tolerant control of dynamic positioning vessel by means of a virtual thruster

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