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Technical Brief

Experimental Verification of Linear and Adaptive Control Techniques for a Two Degrees-of-Freedom Helicopter

[+] Author and Article Information
Pavan Nuthi

Mechanical and Aerospace Engineering,
University of Texas at Arlington,
Arlington, TX 76019
e-mail: pavankumar.nuthinagavenkatas@mavs.uta.edu

Kamesh Subbarao

Associate Professor
Mechanical and Aerospace Engineering,
University of Texas at Arlington,
Arlington, TX 76019
e-mail: subbarao@uta.edu

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received December 19, 2013; final manuscript received November 22, 2014; published online January 27, 2015. Assoc. Editor: Yang Shi.

J. Dyn. Sys., Meas., Control 137(6), 064501 (Jun 01, 2015) (6 pages) Paper No: DS-13-1520; doi: 10.1115/1.4029273 History: Received December 19, 2013; Revised November 22, 2014; Online January 27, 2015

This paper presents the design procedure and experimental results of a high performance adaptive augmentation technique applied to a controller derived based on linear quadratic methods. The Quanser two degrees-of-freedom (2DOF) helicopter was chosen as the experimental platform on which these controllers were implemented. The paper studies the implementation of each of these controllers standalone as well as in the augmented scheme, and discusses its performance and robustness for cases with parametric uncertainties, and unmodeled dynamics. An attempt is made to combine linear quadratic tracker's reliability with the adaptive augmentation's robustness toward modeling uncertainties. It is found that appropriate tuning of parameters in the adaptive framework is key to its performance and thus the process of choosing the parameters is elaborated along with guidelines for choosing a reference model. Tuning considerations for controller implementation on the experimental setup as compared to the same on the numerical model are also addressed. The experiments performed on this system serve as a suitable research test and evaluation basis for robotics and flight control applications.

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References

Figures

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Fig. 1

Quanser 2DOF helicopter

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Fig. 2

Control architecture

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Fig. 3

Pitch doublet tracking (A)

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Fig. 4

Inertia uncertainties (B)

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Fig. 5

Perturbation in unmodeled dynamic states (C)

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