Advances in the linear/nonlinear control of aeroelastic structural systems

Librescu, Liviu; Marzocca, Pier

doi:10.1007/s00707-005-0222-6

Cited by 75 publications

(37 citation statements)

References 106 publications

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“…As the control gain, g h , and the control perturbation, δ h , vary, the flutter speed remains almost constant at its uncontrolled value. This is in agreement with the findings reported in [Librescu & Marzocca, 2005]. Under pitch control, a considerable change in flutter speed is observed.…”

Section: Steady Modelsupporting

confidence: 93%

“…From results not displayed in this paper it can be concluded that for higher control gains the region before the flutter speed is unstable. This is consistent with [Librescu & Marzocca, 2005], where it was demonstrated that an optimal gain value exists. Plunging control gains should be kept small for the best result in both flutter and LCO behavior.…”

Section: Lco Amplitude Analysissupporting

confidence: 91%

“…For larger perturbations the flutter speed is not improved, but decreased, further limiting the safe flight boundary. Considering the δ α value as delay, these results are consistent with [Librescu & Marzocca, 2005]. It was shown that small time delay in the control could be advantageous, whereas large time delay could destabilize the system.…”

Section: Flutter Analysissupporting

confidence: 84%

“…The next generation of aircraft will not be mission specific, but will instead be able to adapt to many different situations and requirements, so the use of these controls to expand the safe flight boundary of an aircraft opens large opportunities in this direction. These facts emphasize the importance of at least two issues: (i) various nonlinear effects should be included in the aeroelastic analysis; (ii) implementing adequate control methodologies will enable one to expand the flight envelope by increasing the flutter speed, or to enhance the aeroelastic response by attenuating the excessive vibrations, but also to convert the unstable LCO into a stable one [Librescu & Marzocca, 2005].…”

Section: Introductionmentioning

confidence: 99%

“…Limiter control offers several advantages of system simplicity and feasibility, in particular simplicity for effective practical engineering, over previous parametric feedback methods more traditionally used in the field of controlling chaos, as reviewed and compared in [Bollt, 2003]. While other forms of nonlinear control of aeroelastic structural systems have previously been researched [Librescu & Marzocca, 2005], the feasibility of limiter control as applied to a nonlinear airfoil, is explored in this paper. In Sec.…”

Section: Introductionmentioning

confidence: 99%

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Active Aeroelastic Control of Lifting Surfaces via Jet Reaction Limiter Control

Rubillo

Bollt

Marzocca

2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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In this paper we present, the design and modeling of the novel nonlinear limiter control feedback control plant [Myneni et al., 1999;Corron et al., 2000;Corron & Pethel, 2002], applied for the first time here in an aeroelastic system, and actuated as a jet reaction torquer control of a wing with potentially chaotic dynamics. This study will provide a better understanding of the nonlinear dynamics of the open/closed-loop aeroelasticity of flexible wings with either steady or unsteady aerodynamic loads. The limiter control can be applied to either the plunging or pitching characteristic of the wing or to both of them. We show that the control can effectively suppress Limit Cycle Oscillations (LCO) and chaos well beyond the nominal flutter speed. This could lead to a practical implementation of the control mechanism on actual and future generation aircraft wings via implementation of a combination of propulsive/jet type forces, micro surface effectors and fluidic devices. Analysis of this control produced favorable results in the suppression of LCO amplitude and increased flutter boundaries for plunging and pitching motion. The limiting control has asymptotically zero power, and is simply implemented, making it a feasible solution to the problem of the chaotic dynamics of the oscillating airfoil.

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Section: Steady Modelsupporting

confidence: 93%

Section: Lco Amplitude Analysissupporting

confidence: 91%

Section: Flutter Analysissupporting

confidence: 84%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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