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Research Papers: Gas Turbines: Controls, Diagnostics, and Instrumentation

Aeroengine Multivariable Nonlinear Tracking Control Based on Uncertainty and Disturbance Estimator

[+] Author and Article Information
Lingfei Xiao

College of Energy and Power Engineering,
Jiangsu Province Key Laboratory
of Aerospace Power Systems,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: lfxiao@nuaa.edu.cn

Contributed by the Controls, Diagnostics and Instrumentation Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received May 30, 2014; final manuscript received June 3, 2014; published online July 2, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(12), 121601 (Jul 02, 2014) (7 pages) Paper No: GTP-14-1256; doi: 10.1115/1.4027820 History: Received May 30, 2014; Revised June 03, 2014

The multivariable robust tracking control problem for aeroengine is considered in this paper. On the basis of the aeroengine nonlinear affine uncertain dynamic model, and according to uncertainty and disturbance estimator (UDE) control approach, a novel aeroengine multivariable robust nonlinear tracking control method is presented in order to provide favorable tracking and disturbance rejection performance. After getting a generalization form of UDE-based aeroengine multivariable controller, a simplification form of control law is obtained when a specified form of low-pass filter is applied. Reference model of the aeroengine system should have satisfying dynamic, thus an optional reference model is provided. Simulation on a twin-shaft aeroengine with two inputs, verifies the effectiveness of the proposed method.

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References

Figures

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Fig. 1

Generalized schematic of twin-shaft aeroengine [18]: I, fan (LP compressor); II, HP compressor; III, bypass duct; IV, main combustion chamber; V, HP and LP turbines; VI, mixing chamber; and VII, nozzle

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Fig. 4

Comparison of LP spool speed n1 responses

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Fig. 5

Comparison of HP spool speed n2 responses

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Fig. 6

Tracking errors of spool speeds

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Fig. 7

Comparison of main fuel flow Wfb and nozzle throat area A8

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Fig. 2

UDE-based aeroengine control algorithm block diagram

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Fig. 3

Desired states and reference trajectory

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