Transonic and Low-Supersonic Aeroelastic Analysis of a Two-Degree-of-Freedom Airfoil With a Freeplay Non-Linearity

Kim, Dong-Hyun; Lee, In

doi:10.1006/jsvi.2000.2907

Cited by 74 publications

(17 citation statements)

References 20 publications

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“…Kim and Lee [13] investigated the aeroelastic characteristics of a two-degree-of-freedom airfoil with free-play structural nonlinearity in the transonic and low-supersonic regions. Using a state space unsteady aerodynamics model, Murty [14] studied the aeroelastic stability of an airfoil with a cubic structural nonlinearity in torsional stiffness.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear aeroelastic analysis of a two-dimensional wing with control surface in supersonic flow

Zheng

2010

Acta Mech Sin

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Based on the piston theory of supersonic flow and the energy method, a two dimensional wing with a control surface in supersonic flow is theoretically modeled, in which the cubic stiffness in the torsional direction of the control surface is considered. An approximate method of the chaotic response analysis of the nonlinear aeroelastic system is studied, the main idea of which is that under the condition of stable limit cycle flutter of the aeroelastic system, the vibrations in the plunging and pitching of the wing can approximately be considered to be simple harmonic excitation to the control surface. The motion of the control surface can approximately be modeled by a nonlinear oscillation of one-degree-of-freedom. The range of the chaotic response of the aeroelastic system is approximately determined by means of the chaotic response of the nonlinear oscillator. The rich dynamic behaviors of the control surface are represented as bifurcation diagrams, phase-plane portraits and PS diagrams. The theoretical analysis is verified by the numerical results.

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Section: Introductionmentioning

confidence: 99%

Nonlinear aeroelastic analysis of a two-dimensional wing with control surface in supersonic flow

Zheng

2010

Acta Mech Sin

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“…It should be pointed out that panel flutter can occur on flat or curved panels [5,23,25,[26][27][28][29][30][31]. Various non-linearities can influence differently the character of the flutter boundary.…”

Section: Introductionmentioning

confidence: 99%

Static/Dynamic Edge Movability Effect on Non-Linear Aerothermoelastic Behavior of Geometrically Imperfect Curved Skin Panel: Flutter and Post-Flutter Analysis

Abbas

Rui

Marzocca

et al. 2012

Journal of Applied Mechanics

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This paper addresses the problem of the aerothermoelastic modeling behavior and analyses of skin curved panels with static and dynamic edge movability effect in high supersonic fiow. Flutter and post-fiutter behavior will be analyzed toward determining under which conditions such panels will exhibit a benign instability, that is a stable limit cycle oscillation, or a catastrophic instability, that is an unstable LCO. The aerothermoelastic governing equations are developed from the geometrically non-linear theory of infinitely long two dimensional curved panels. Von Kármán non-linear strain-displacement relation in conjunction with the Kirchhoff plate-hypothesis is adopted. A geometrically imperfect curved panel forced by a supersonic/hypersonic unsteady flow is numerically investigated using Galerkin approach. These equations are based on the third-order piston theory aerodynamic for modeling the fiow-induced forces. Furthermore, the effects of thermal degradation and Kelvin's model of structural damping independent of time and temperature are also considered in this model. Computational analysis and discussion of the finding along with pertinent conclusions are presented.

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“…Bendiksen [17] studied the period-tripling flutter of a wing in transonic flow. Kim and Lee [18] present structural nonlinearity effects on aeroelastic responses in the flow region with aerodynamic nonlinearity using the simultaneous time integration method coupled with CFD code of the Euler-based compressible aerodynamic theory. Also, the combined nonlinear effects of pitch-plunge free-play is investigated.…”

Section: Introductionmentioning

confidence: 99%

Chaotic motions and limit cycle flutter of two-dimensional wing in supersonic flow

Zheng

Yang

2008

Acta Mech. Solida Sin.

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Based on the piston theory of supersonic flow and the energy method, the flutter motion equations of a two-dimensional wing with cubic stiffness in the pitching direction are established. The aeroelastic system contains both structural and aerodynamic nonlinearities. Hopf bifurcation theory is used to analyze the flutter speed of the system. The effects of system parameters on the flutter speed are studied. The 4th order Runge-Kutta method is used to calculate the stable limit cycle responses and chaotic motions of the aeroelastic system. Results show that the number and the stability of equilibrium points of the system vary with the increase of flow speed. Besides the simple limit cycle response of period 1, there are also period-doubling responses and chaotic motions in the flutter system. The route leading to chaos in the aeroelastic model used here is the period-doubling bifurcation. The chaotic motions in the system occur only when the flow speed is higher than the linear divergent speed and the initial condition is very small. Moreover, the flow speed regions in which the system behaves chaos are very narrow.

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Transonic and Low-Supersonic Aeroelastic Analysis of a Two-Degree-of-Freedom Airfoil With a Freeplay Non-Linearity

Cited by 74 publications

References 20 publications

Nonlinear aeroelastic analysis of a two-dimensional wing with control surface in supersonic flow

Nonlinear aeroelastic analysis of a two-dimensional wing with control surface in supersonic flow

Static/Dynamic Edge Movability Effect on Non-Linear Aerothermoelastic Behavior of Geometrically Imperfect Curved Skin Panel: Flutter and Post-Flutter Analysis

Chaotic motions and limit cycle flutter of two-dimensional wing in supersonic flow

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