Limit-Cycle Oscillations in High-Aspect-Ratio Wings

Patil, Mayuresh; Hodges, Dewey H.; Cesnik, Carlos E. S.

doi:10.1006/jfls.2000.0329

Cited by 178 publications

(77 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Such nonlinearities are found in high-aspect-ratio wings, such as those found in high-altitude surveillance airplanes, and are characterized by a high flexibility and large deformations [4].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Reliability-Based Design Optimization of Nonlinear Aeroelasticity Problems

Missoum

Dribusch

Beran

2010

Journal of Aircraft

View full text Add to dashboard Cite

This paper introduces a methodology for the reliability-based design optimization of systems with nonlinear aeroelastic constraints. The approach is based on the construction of explicit flutter and subcritical limit cycle oscillation boundaries in terms of deterministic and random design variables. The boundaries are constructed using a support vector machine that provides a way to efficiently evaluate probabilities of failure and solve the reliabilitybased design optimization problem. Another major advantage of the approach is that it efficiently manages the discontinuities that might appear during subcritical limit cycle oscillations. The proposed approach is applied to the construction of flutter and subcritical limit cycle oscillation boundaries for a two-degree-of-freedom airfoil with nonlinear stiffnesses. The solution of a reliability-based design optimization problem with a constraint on the probability of subcritical limit cycle oscillation is also provided.

show abstract

Section: Introductionmentioning

confidence: 99%

“…In some situations, it might be difficult to clearly separate the contribution of these two factors. Studies have typically focused on one or the other [1,2,4]. In this paper, we will only consider LCOs due to structural nonlinearities.…”

Section: Introductionmentioning

confidence: 99%

Reliability-Based Design Optimization of Nonlinear Aeroelasticity Problems

Missoum

Dribusch

Beran

2010

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…Patil et al 1 have studied static and dynamic aeroelastic characteristics of a high-aspect-ratio wing. For a structural analysis, large deflection effects of a beam are described using Rodrigues parameter.…”

Section: Introductionmentioning

confidence: 99%

Fluid-Structure Interaction Analysis of a High-Aspect-Ratio Wing Considering Structural Nonlinearity

et al. 2009

View full text Add to dashboard Cite

In this research, fluid-structure interaction problem including geometric structural nonlinearity is studied for a high-aspect-ratio wing. When a high-aspect-ratio wing structure is interacted with external airload, geometric structural nonlinearity can be caused by large deflection of a wing. For the investigation of such a fluid-structure interaction problem, the transonic small disturbance theory for the aerodynamic analysis and the large deflection beam theory for the structural analysis are used, respectively. For the coupling between fluid and structure, the transformation of a displacement from the structural mesh to the aerodynamic grid is performed by a shape function which is used for the finite element and the inverse transformation of force by work equivalent load method. Static deformations in the vertical and twist deflections caused by gravity loading are compared with experimental results. Also, static aeroelastic analysis results are compared with experimental data. From the analysis results, effects of structural nonlinearity on static aeroelastic characteristics are investigated.

show abstract

“…= section torsional moment coefficient c, c = wing chord and dimensionless chord, c=L dF v , dF w = section aerodynamic forces in lag and flap directions dM x = section pitch moment about elastic axis E = modulus of elasticity e = section mass center from elastic axis G = shear modulus g = gravitational constant I 1 , I 2 = flap and lag area moments I x0 , I y0 , I z0 = moments of inertia for tip slender body U NINHABITED HALE (high-altitude long-endurance) aircraft are of great current interest. High altitudes and low air densities dictate the use of a large wing area and a light structural design to increase lift and endurance, thus leading to the design of flexible high-aspect ratio wings.…”

mentioning

confidence: 99%

“…These wings undergo large deflections and the geometric structural nonlinearity becomes a very important factor that affects the aeroelastic stability and response of the HALE aircraft. Recent studies ( [1][2][3][4][5][6][7][8][9][10]) have shown that there are significant differences in the flutter boundary, limit cycle oscillation (LCO) and gust response between a linear structural analysis and a nonlinear structural analysis.…”

mentioning

confidence: 99%

Gust Response for Flexibly Suspended High-Aspect Ratio Wings

2010

View full text Add to dashboard Cite

A theoretical aeroelastic study for a flexibly suspended high-aspect ratio wing aeroelastic model excited by gust loads is presented along with a companion wind-tunnel test. A flexible support system at the wing root has been constructed to simulate a rigid body mode. Structural equations of motion based on a nonlinear beam theory are combined with the ONERA aerodynamic model. Also, a dynamic perturbation analysis about a nonlinear static equilibrium is used to determine the small perturbation flutter boundary and structural natural frequencies. The effects of the flexible support system (bi-beam system) on the wing structural dynamics, the static aeroelastic displacement at root, nonlinear flutter, and gust response to a harmonic or a frequency sweep excitation are discussed. Also the effect of gust distribution along the span on the response is described based upon computations. The fair to good quantitative agreement between theory and experiment demonstrates that the present analysis method has reasonable accuracy.

show abstract

Limit-Cycle Oscillations in High-Aspect-Ratio Wings

Cited by 178 publications

References 13 publications

Reliability-Based Design Optimization of Nonlinear Aeroelasticity Problems

Reliability-Based Design Optimization of Nonlinear Aeroelasticity Problems

Fluid-Structure Interaction Analysis of a High-Aspect-Ratio Wing Considering Structural Nonlinearity

Gust Response for Flexibly Suspended High-Aspect Ratio Wings

Contact Info

Product

Resources

About