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Research Papers

Adaptive Actuator Failure and Structural Damage Compensation of NASA Generic Transport Model

[+] Author and Article Information
Jiaxing Guo, Yu Liu

Department of Electrical
and Computer Engineering,
University of Virginia,
Charlottesville, VA 22904

Gang Tao

Department of Electrical
and Computer Engineering,
University of Virginia,
Charlottesville, VA 22904
e-mail: gt9s@virginia.edu

1Corresponding author.

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received November 22, 2012; final manuscript received December 3, 2013; published online February 19, 2014. Assoc. Editor: Won-jong Kim.

J. Dyn. Sys., Meas., Control 136(3), 031009 (Feb 19, 2014) (10 pages) Paper No: DS-12-1385; doi: 10.1115/1.4026162 History: Received November 22, 2012; Revised December 03, 2013

This paper studies design and evaluation of a multivariable model reference adaptive control (MRAC) scheme for aircraft systems under simultaneous actuator failures and structural damage. A key design condition–system infinite zero structure is investigated for nominal and posthazard aircraft systems and the invariance of this essential condition is concluded under realistic failure and damage conditions. The multivariable model reference adaptive control scheme is developed to ensure stability and asymptotic output tracking for the aircraft in the presence of uncertain actuator failures and structural damage. The developed fault-tolerant control design is evaluated by a high-fidelity nonlinear aircraft model–the NASA generic transport model.

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Figures

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Fig. 1

Linearization-based adaptive control system

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Fig. 2

Linearized GTM outputs versus reference signals (case I)

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Fig. 3

Linearized GTM outputs versus reference signals (case II)

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Fig. 4

GTM outputs (solid) versus reference outputs (dotted) (case I)

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Fig. 5

Deflections of four elevator segments (case I)

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Fig. 6

Deflections of two rudder segments (case I)

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Fig. 7

GTM outputs (solid) versus reference outputs (dotted) (case II)

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Fig. 8

Deflections of four elevator segments (case II)

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Fig. 9

Deflections of two rudder segments (case II)

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