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Technical Briefs

Nonlinear Control of Aircraft Engines Using a Generalized Gronwall-Bellman Lemma Approach

[+] Author and Article Information
Jiqiang Wang

College of Energy and Power Engineering,  Nanjing University of Aeronautics & Astronautics, 29 Yudao Street, Nanjing 210016, P. R. Chinajiqiang.wang@nuaa.edu.cn

Zhifeng Ye

College of Energy and Power Engineering,  Nanjing University of Aeronautics & Astronautics, 29 Yudao Street, Nanjing 210016, P. R. Chinayzf@nuaa.edu.cn

Zhongzhi Hu

College of Energy and Power Engineering,  Nanjing University of Aeronautics & Astronautics, 29 Yudao Street, Nanjing 210016, P. R. Chinahuzhongzhi@nuaa.edu.cn

J. Eng. Gas Turbines Power 134(9), 094502 (Jul 23, 2012) (6 pages) doi:10.1115/1.4007011 History: Received June 01, 2012; Accepted June 14, 2012; Published July 23, 2012; Online July 23, 2012

Model-based design has attracted much attention in the field of aircraft engine control in recent years. As an aircraft engine is a complicated thermomechanical system, it can only be represented by a nonlinear process model. This necessitates the study of the nonlinear control techniques. Based on our recent results, this paper proposes a novel design approach based on a generalized Gronwall-Bellman lemma. Important results are obtained on bounding behavior of the nonlinear states of the engine. The proposed method is easy to design and tune with the appealing feature of enlarging the feasible control envelope. Finally, a simulation study is provided to validate the effectiveness of the control design approach.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Comparison of transient response of state signals, x0=[−0.2−0.3]T

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Figure 2

Comparison of transient response for \|x(t)‖ with theoretical bound. Right corner is the magnified view of the state norm evolution for controlled and uncontrolled systems.

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Figure 3

Comparison of transient response of state signals, x0=[−0.2−0.3]T

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Figure 4

Comparison of regulation performance of output signals

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Figure 5

Tracking performance of the proposed design. Also shown is the performance for corresponding linearized systems (a) PCN2R, (b) P56/P25, (c) P16/P56.

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