Suppression of Control Reversal Using Leading- and Trailing-Edge Control Surfaces

Platanitis, George; Strganac, Thomas W.

doi:10.2514/1.6692

Cited by 38 publications

(15 citation statements)

References 6 publications

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“…The dynamical model of the aeroelastic system considered here has been developed in [8,[10][11][12]. The second-order differential equations governing the evolution of the pitch angle (α) and the plunge displacement (h) are given by…”

Section: Aeroelastic Model and Control Problemmentioning

confidence: 99%

“…The instability of this model has been analyzed using computation method as well as laboratory tests in the wind-tunnel [9]. For the suppression of limit cycle oscillations of this wing section control systems have been designed using a single trailing-edge control surface as well as leading-and trailing-edge control surfaces [8,[10][11][12]. For the stability in the closed-loop system with only trailing-edge control surface, the zero dynamics must be stable.…”

Section: Introductionmentioning

confidence: 99%

“…For the stability in the closed-loop system with only trailing-edge control surface, the zero dynamics must be stable. But using the trailing-and leading-edge control surfaces global stabilization for this model is possible [11,12]. Researchers have developed several adaptive control systems for the control of this aeroelastic system with uncertainties, using single as well as two control surfaces [11,[13][14][15][16][17].…”

Section: Introductionmentioning

confidence: 99%

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Multi-Input Higher-order Sliding Mode Control of Aeroelastic Systems With Uncertainties and Gust Load

Lee

Singh

2014

AIAA Guidance, Navigation, and Control Conference

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This paper presents the design of a higher-order sliding mode controller for finite-time stabilization of a multi-input multi-output nonlinear aeroelastic system with uncertain dynamics using leading-and trailing-edge control surfaces. The model describes the plunge and pitch dynamics of a prototypical wing section. It is assumed that the system parameters are not known precisely and external disturbance inputs are present in the model. The uncontrolled model exhibits limit cycle oscillations. The objective is to control the state vector of the system to the origin. A robust control law is designed for the finite-time trajectory control of the plunge and pitch angle trajectory. The control law includes a nominal finite-time stabilizing control signal designed for the system without uncertainties, and a discontinuous control signal for nullifying the effect of uncertain functions in the model. For the nominal control law design, the notion of geometric homogeneity is utilized and the discontinuous part of the controller is derived based on a second-order sliding mode control scheme. In the closed-loop system including the nominal and discontinuous control signals, finite-time control of the complete state vector associated with the plunge-pitch motion of the system to the origin is accomplished. Simulation results are presented which show the suppression of the limit cycle oscillations, despite parameter uncertainties and triangular, exponential, sinusoidal and random gust loads.

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Section: Aeroelastic Model and Control Problemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Multi-Input Higher-order Sliding Mode Control of Aeroelastic Systems With Uncertainties and Gust Load

Lee

Singh

2014

AIAA Guidance, Navigation, and Control Conference

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“…Firstly, much smaller deflections of control surfaces are required and the wing can be subject to much larger twist than a conventionally designed wing when an MIMO controller is used. Secondly, a control reversal may occur when the twist due to the control-surface deflection negates the control-induced maneuvering loads, 11 if only a trailing-edge control surface is used. However, the control reversal problem can be improved by using a leading-edge control surface at the same time.…”

Section: Introductionmentioning

confidence: 99%

Active flutter suppression of a multiple-actuated-wing wind tunnel model

Qian

Huang

et al. 2014

Chinese Journal of Aeronautics

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In this study, a multi-input/multi-output (MIMO) time-delay feedback controller is designed to actively suppress the flutter instability of a multiple-actuated-wing (MAW) wind tunnel model in the low subsonic flow regime. The unsteady aerodynamic forces of the MAW model are computed based on the doublet-lattice method (DLM). As the first attempt, the conventional linear quadratic-Gaussian (LQG) controller is designed to actively suppress the flutter of the MAW model. However, because of the time delay in the control loop, the wind tunnel tests illustrate that the LQG-controlled MAW model has no guaranteed stability margins. To compensate the time delay, hence, a time-delay filter, approximated via the first-order Pade approximation, is added to the LQG controller. Based on the time-delay feedback controller, a new digital control system is constructed by using a fixed-point and embedded digital signal processor (DSP) of high performance. Then, a number of wind tunnel tests are implemented based on the digital control system. The experimental results show that the present time-delay feedback controller can expand the flutter boundary of the MAW model and suppress the flutter instability of the open-loop aeroelastic system effectively. ª 2014 Production and hosting by Elsevier Ltd. on behalf of CSAA & BUAA.

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“…The Nonlinear Aeroelastic Test Apparatus (NATA) model with 3 degrees-of-freedom (DoF) and unsteady aerodynamics was designed in [2,3] with several control solution approaches found in [4,5,6,7,8,9,10,11,12,13,14,15] to name a few. These papers include adaptive control, nonlinear backstepping adaptive control, neural network based approach, optimal infinite-horizon control law, full-state feedforward/feedback control and other control design approaches.…”

Section: Introductionmentioning

confidence: 99%

TP Model-based Robust Stabilization of the 3 Degrees-of-Freedom Aeroelastic Wing Section

Takarics

Bárányi

2014

APH

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Active stabilisation of the 2 and 3 degrees-of-freedom (DoF) aeroelastic wind sections with structural nonlinearities led to various control solutions in the recent years. The paper proposes a control design strategy to stabilise the 3 Dof aeroelastic model. It is assumed that the aeroelastic model has uncertain parameters in the trailing edge dynamics and only one state variable, the pitch angle is measurable, therefore, robust output feedback control solution is derived based on the Tensor Product (TP) type convex representation of the aeroelastic model. The control performance requirements include robust asymptotic stability and constraint on the l 2 norm of the control signal. The control performance requirements are formulated in terms of Linear Matrix Inequalities (LMIs). As the first step of the proposed strategy, the TP type model is obtained by executing TP transformation. As the second step, LMI based control design is performed resulting in controller and observer solution defined with the same polytopic structure as the TP type model. The validation and evaluation of the derived control solutions is based on numerical simulations.Keywords: aeroelastic wing, robust LMI-based multi-objetive control, TP model transformation, qLPV systems NomenclatureThe variables used in the paper are defined as below:-a = non-dimensional distance from the mid-chord to the elastic axis

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Suppression of Control Reversal Using Leading- and Trailing-Edge Control Surfaces

Cited by 38 publications

References 6 publications

Multi-Input Higher-order Sliding Mode Control of Aeroelastic Systems With Uncertainties and Gust Load

Multi-Input Higher-order Sliding Mode Control of Aeroelastic Systems With Uncertainties and Gust Load

Active flutter suppression of a multiple-actuated-wing wind tunnel model

TP Model-based Robust Stabilization of the 3 Degrees-of-Freedom Aeroelastic Wing Section

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