Frequency and time domain flutter computations of a wing with oscillating control surface including shock interference effects

Kwon, Jae Ryong; Kim, Dong-Hyun; Lee, In

doi:10.1016/j.ast.2004.04.001

Cited by 14 publications

(8 citation statements)

References 11 publications

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“…Kim and Lee (2000) also evaluated the unsteady aerodynamic forces on the airfoil in transonic and low-supersonic regions using 2D unsteady Euler code. Kwon et al (2004) used a modified transonic small-disturbance theory to analyze the unsteady aerodynamics of a wing with an oscillating control surface in the transonic and supersonic regimes.…”

Section: Equation Of Motion Of the Aeroelastic Systemmentioning

confidence: 99%

“…Jegarkandi et al (2009) researched the aeroelastic stability of a flexible supersonic flight vehicle using non-linear dynamics, nonlinear aerodynamics, and a linear structural model. Kwon et al (2004) examined the non-linear aeroelastic characteristics of a wing with an oscillating control surface in transonic and supersonic regimes and observed the effects of rotational stiffness on the flutter properties.…”

Section: Introductionmentioning

confidence: 99%

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Improving the Aeroelastic Flutter Characteristics of Supersonic Beams Using Piezoelectric Material

Chen

Cao

2011

Journal of Intelligent Material Systems and Structures

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The active aeroelastic flutter characteristics of supersonic beams are investigated. The main contribution of this research is that the piezoelectric material is used to increase the flutter velocities of the supersonic beams. A modeling approach based on the conventional theory of structural dynamics is employed. The process of deriving equations is not complicated and easy to understand. This methodology is verified to be accurate and effective. Hamilton’s principle with the assumed mode method is used to develop the equation of motion of the structural systems. The supersonic piston theory is adopted to evaluate the aerodynamic pressure. Using the standard eigenvalue methodology, the solutions for complex eigenvalue problem are obtained. A displacement and acceleration feedback control strategy is used to obtain the active stiffness and active mass. The aeroelastic flutter bounds are obtained by calculating the natural frequencies and damping ratios. The effects of the active stiffness and mass on the flutter properties of the supersonic beams are analyzed. From the numerical results, it is seen that by adding the active stiffness and mass to the supersonic beams, the aeroelastic flutter properties can be effectively improved. Especially, if the acceleration and displacement feedback gains are increased to proper values, the flutter can even be eliminated for the supersonic cantilevered beams.

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Section: Equation Of Motion Of the Aeroelastic Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Improving the Aeroelastic Flutter Characteristics of Supersonic Beams Using Piezoelectric Material

Chen

Cao

2011

Journal of Intelligent Material Systems and Structures

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“…With the advances in CPU speeds, CFD-based directly aeroelastic simulation has been used in aircraft design more and more [8][9][10][11]. Coupling structural equations with unsteady Euler/NS CFD algorithm, the structural aeroelastic response can be predicted in time domain.…”

Section: Introductionmentioning

confidence: 99%

Control law design for transonic aeroservoelasticity

Zhang

2007

Aerospace Science and Technology

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“…The TSD code is widely recognized as one of the most efficient tools among the conventional CFD-based approaches. In addition, for a grid system, the TSD code does not require an additional grid remeshing process since it uses the changes of the wing airfoil slopes at each wall grid point to simulate arbitrary wing surface motions (3) . In the past, many aeroelastic analyses were performed using the TSD equation for various aircraft models (4) .…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Aeroelastic Instability of a Complete Aircraft Model

Kim

Kwon

Kim

et al. 2005

JSME international journal. Ser. B, Fluids and thermal engineer

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A nonlinear aeroelastic analysis system has been developed using the coupled numerical techniques of computational fluid dynamics (CFD) and computational structural dynamics (CSD) in the present study and the analysis system has been applied to an actual aircraft design procedure to examine aeroelastic stabilities. An aerodynamic analysis is performed using the transonic small disturbance (TSD) theory for computational efficiency and the results are compared with experimental data. An aeroelastic analysis in the time domain is performed to obtain the flutter boundaries of the aircraft model. Finally, the various effects of launchers and control surfaces are investigated.

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Frequency and time domain flutter computations of a wing with oscillating control surface including shock interference effects

Cited by 14 publications

References 11 publications

Improving the Aeroelastic Flutter Characteristics of Supersonic Beams Using Piezoelectric Material

Improving the Aeroelastic Flutter Characteristics of Supersonic Beams Using Piezoelectric Material

Control law design for transonic aeroservoelasticity

Numerical Investigation on the Aeroelastic Instability of a Complete Aircraft Model

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