Nonlinear Control of a Prototypical Wing Section with Torsional Nonlinearity

Ko, Jonghan; Kurdila, Andrew J.; Strganac, Thomas W.

doi:10.2514/2.4174

Cited by 187 publications

(102 citation statements)

References 13 publications

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“…This model has proven to be adequate for low reduced frequency, subsonic flow, as validated by the experiments. 7,8,15 The wing section modeled by these equations of motion has been built for experiments on the nonlinear aeroelastic test apparatus (NATA) 16 in the 2 × 3 ft low-speed wind tunnel. A unique feature of NATA is the presence of two cams that are fabricated to permit prescribed nonlinear responses in pitch and plunge.…”

Section: System Modelmentioning

confidence: 99%

“…The controller stabilized the system if activated during the transient phase of the motion, but its capability was limited once the system was entrained in LCO motion. Ko et al 8 developed a control law using partial feedback linearization via Lie algebraic methods. The pitch degree of freedom was chosen as the primary variable to control because the system could be transformed to cancel out the nonlinearities introduced by the torsion stiffness.…”

mentioning

confidence: 99%

“…Because control with feedback linearization requires the exact cancellation of the nonlinear parameters, 8 adaptive methods were introduced to account for uncertainties in the nonlinear parameters.…”

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confidence: 99%

“…Furthermore, with two control surfaces, it is possible to achieve a globally stabilizing controller. 8,9 Herein, the extension and validation of control laws as applied to a wing section with both a leading-and trailing-edge full-span control surface is studied.…”

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confidence: 99%

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Control of a Nonlinear Wing Section Using Leading- and Trailing-Edge Surfaces

Platanitis

Strganac

2004

Journal of Guidance, Control, and Dynamics

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140

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The control of nonlinear aeroelastic response of a wing section with a continuous stiffening-type structural nonlinearity is examined through analytical and experimental studies. Motivated by the limited effectiveness of using a single, trailing-edge control surface for the suppression of limit-cycle oscillations of a typical wing section, improvements in the control of limit-cycle oscillations are investigated through the use of multiple control surfaces, namely, an additional leading-edge control surface. The control methodology consists of a feedback linearization approach that transforms the system equations of motion via Lie algebraic methods and a model reference adaptive control strategy that augments the closed-loop system to account for inexact cancellation of nonlinear terms due to modeling uncertainty. Specifically, uncertainty in the nonlinear pitch stiffness is examined. It is shown through simulations and experiments that globally stabilizing control may be achieved by using two control surfaces. Nomenclature a = nondimensional distance from midchord to elastic axis position b = semichord of wing section= pitch cam moment of inertia I cg − wing = wing section moment of inertia about the center of gravity I α = total pitch moment of inertia about elastic axis k h = plunge stiffness m T = total mass of pitch-plunge system m wing = mass of wing section m W − tot = total wing section plus mount mass r cg = distance from elastic axis to center of mass s = wing section span U = freestream velocity x α = nondimensional distance from elastic axis to center of mass α = angle of attack β = trailing-edge control surface deflection γ = leading-edge control surface deflection ρ = air density

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Section: System Modelmentioning

confidence: 99%

mentioning

confidence: 99%

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confidence: 99%

mentioning

confidence: 99%

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Control of a Nonlinear Wing Section Using Leading- and Trailing-Edge Surfaces

Platanitis

Strganac

2004

Journal of Guidance, Control, and Dynamics

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140

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“…Of more relevance to the present work is a series of publications by Strganac and colleagues [9][10][11][12][13][14], in which the application of active control on aeroelastic systems with hardening-type structural nonlinearities has been investigated both theoretically also experimentally, through the use of quasi-steady aeroelastic models. These studies utilised the feedback linearisation nonlinear control method, in conjunction with LQR control as the linear control objective.…”

Section: Introductionmentioning

confidence: 99%

Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

Jiffri

Fichera

Mottershead

et al. 2017

Journal of Guidance, Control, and Dynamics

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TP Model Transformation as a Manipulation Tool for QLPV Analysis and Design

Bárányi¹

2015

Asian Journal of Control

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The main motivation of the TP model transformation is that modern identification and control analysis, along with design methodologies, are based on various kinds of different representations that have different benefits and drawbacks in terms of identification and modeling effort and structure, however, the link between these representations is in many cases difficult to establish, especially if the model components are not given by closed formulae but rather by various soft-computing-based or black box models. This paper shows that the TP model transformation can serve as a gateway between different representations by bridging to a widely adopted polytopic representation. Further, it is capable of readily manipulating the resulting polytopic representation for further design requirements, which in many cases has a strong effect on the resulting control performance and the conservativeness of the solution. The paper discusses how the TP model transformation can be used as a final step of modeling and, at the same time, as a preprocessing step in polytopic model based design approaches. The paper introduces the generalized TP model transformation, which is a tractable, non-heuristic numerical tool that can be executed on sets of functions. Different manipulation techniques are investigated to show the benefits of the generalized TP model transformation. Finally, a stability verification technique is proposed for cases where system components are available in different representations.Key Words: qLPV and polytopic system based control design, TP model transformation, linear matrix inequality based design.

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Nonlinear Control of a Prototypical Wing Section with Torsional Nonlinearity

Cited by 187 publications

References 13 publications

Control of a Nonlinear Wing Section Using Leading- and Trailing-Edge Surfaces

Control of a Nonlinear Wing Section Using Leading- and Trailing-Edge Surfaces

Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

TP Model Transformation as a Manipulation Tool for QLPV Analysis and Design

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