Static Output Feedback-Based PI Control for Aeroengines Using Linear Matrix Inequality

Wang, Xi; Sun, Yongxia; Tan, Daoliang

doi:10.2514/6.2008-4581

Cited by 5 publications

(4 citation statements)

References 5 publications

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“…Furthermore, this paper differs from the previous PI work [2] in three aspects: 1) A derivative part is incorporated in the current work, compared with no derivative part in the PI paper; 2) we address the issue of control constraints in a cascade way in this paper, as opposed to the parallel style in the previous paper; and 3) this paper handles the nonstrict-properness of linear models by means of a degenerate linear transformation, rather than approximate H ∞ model transform in the preceding work.…”

Section: Introductionmentioning

confidence: 79%

“…(7), then a procedure can be derived of devising a PI controller for the linear engine model E (with D e = 0). The corresponding details can be found in the work by Wang et al [2].…”

Section: Lmi-based Pid Controlmentioning

confidence: 99%

“…Hence the demand of engine controllers for good robustness and simplicity becomes natural. In the previous work, we explored the efficient design of multivariable PI controllers and considered control constraints for linear aeroengine models simultaneously in the framework of linear matrix inequality (LMI) [2]. That work reveals that the proposed procedure can produce PI controllers having good robustness against model perturbation.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Multivariable Aeroengine PID Control With Amplitude Saturation: An LMI Solution

Tan

Wang

et al. 2010

Volume 3: Controls, Diagnostics and Instrumentation; Cycle Innovations; Marine

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This paper presents an approach to automatic tuning of the parameters of a PID controller for the multivariable gas turbine engine control, taking into account amplitude saturation and model nonstrict-properness. First of all, we illustrate that the PID controller design problem can be transformed into seeking a static output feedback controller for some augmented statespace model. Then we compute an initial stabilizable parameters of the involved PID controller in the strictly proper case, using a well-known static output feedback algorithm. As far as a nonstrictly proper model is concerned, this paper uses a degenerate linear transformation to change its output equation into a strictly proper form. The drawback of the initially computed PID controller lies in its high gains (triggering amplitude saturation) that prevent it from being applicable to practical gas turbine engine control. In this paper, we build on a linear matrix inequality (LMI) based antiwindup scheme to address the constraints from amplitude saturation. Both of these problems are formulated in the LMI framework and can be efficiently solved using off-theshelf software. Experimental results show the promising performance of the proposed method.

show abstract

Section: Introductionmentioning

confidence: 79%

“…(7), then a procedure can be derived of devising a PI controller for the linear engine model E (with D e = 0). The corresponding details can be found in the work by Wang et al [2].…”

Section: Lmi-based Pid Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Multivariable Aeroengine PID Control With Amplitude Saturation: An LMI Solution

Tan

Wang

et al. 2010

Volume 3: Controls, Diagnostics and Instrumentation; Cycle Innovations; Marine

Self Cite

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“…Gas from the core and airflow from the mixer leave through the nozzle. 23–25 The common equation of the turbofan engine both in steady and dynamic operations follows flow capacity balance as equation (1) and spool power balance as equation (2), which are separately described as…”

Section: Turbofan Engine Speed Model and Controlmentioning

confidence: 99%

Iterative learning NARMA-L2 control for turbofan engine with dynamic uncertainty in flight envelope

Li¹,

Yan²,

Tang³

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Nonlinear control of turbofan engines in the flight envelope has attracted much attention in consideration of the inherent nonlinearity of the engine dynamics. Most nonlinear control design techniques rely on the correction theory of reference model parameter to extend the typical flight operations from ground operation. However, dynamic uncertainties in flight envelope lead to the deviation of operating state, and it is negative to control performance. This article is to develop online correction neural network–based speed control approaches for the turbofan engine with dynamic uncertainty in the flight envelope. Two improved online correction nonlinear ways combined with nonlinear autoregressive moving average (NARMA) are proposed, such as gradient search nonlinear autoregressive moving average with feedback linearization (NARMA-L2) control and iterative learning NARMA-L2 control. The contribution of this article is to provide better control quality of fast regulation and less steady errors of engine speed by the proposed methodology in comparison to the conventional NARMA-L2 control. Some important results are reached on both turbofan engine controller design and dynamic uncertainty tolerance at the typical flight operations, and the numerical examples demonstrate the superiority of the proposed control in the flight envelope.

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Inverted decoupling and LMI-based controller design for a turboprop engine with actuator dynamics

Chen

Wang

et al. 2020

Chinese Journal of Aeronautics

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Static Output Feedback-Based PI Control for Aeroengines Using Linear Matrix Inequality

Cited by 5 publications

References 5 publications

Multivariable Aeroengine PID Control With Amplitude Saturation: An LMI Solution

Multivariable Aeroengine PID Control With Amplitude Saturation: An LMI Solution

Iterative learning NARMA-L2 control for turbofan engine with dynamic uncertainty in flight envelope

Inverted decoupling and LMI-based controller design for a turboprop engine with actuator dynamics

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