Experimental and Theoretical Study on Aeroelastic Response of High-Aspect-Ratio Wings

Tang, Deman; Dowell, Earl H.

doi:10.2514/2.1484

Cited by 252 publications

(102 citation statements)

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“…Using linear finite element analysis (FEA) and 2D unsteady strip theory aerodynamics, they pointed out that including flexible deformation modes has a dramatic effect on predicted aircraft stability. Several other studies on HALE wings have used low-order aerodynamics [5][6][7][8][9][10][11][12][13][14]. First, Patil, Hodges, and Cesnik authored a series of works [5,6,8] about the coupling of an exact intrinsic beam model with Peters' finite-state aerodynamics [15] and its application to highly flexible aircraft.…”

Section: Introductionmentioning

confidence: 99%

“…Patil and Hodges [9] use nonlinear beam theory, with non-planar doublet and vortex lattice aerodynamics for similar applications. Tang and Dowell [10] also incorporate a geometrically nonlinear beam model, but use 2D strip theory for aerodynamics. A comprehensive Nonlinear Aeroelastic Simulation Toolbox (UM/NAST) [11] which uses a strain-based structural formulation and Peters finite-state aerodynamics [15] was developed at the University of Michigan.…”

Section: Introductionmentioning

confidence: 99%

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High-fidelity Aeroelastic Analysis of Very Flexible Aircraft

Hallissy

Cesnik

2011

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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This paper describes the development and capabilities of a high-fidelity aeroelastic simulation tool for very flexible aircraft (HiFi-VFA) within a Multi-Disciplinary Computing Environment (MDICE). The code loosely couples a geometrically nonlinear, quasi-3D structural solver with an Euler/Navier-Stokes flow solver capable of arbitrary, large, mesh deformation. Verification of the static aeroelastic solver is presented for a hypothetical high aspect ratio wing discussed in the literature. Time domain aeroelastic simulations using the new code generally agree well with the response of an in-house aeroelastic simulation toolbox, but the high-fidelity results suggest the presence of higher aerodynamic damping than predicted by the finite state aerodynamics. With these results, flutter boundaries are sought using two flutter prediction methods (ARMA and FMDS) and the advantages/disadvantages of these prediction methods in computational aeroelasticity are assessed.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

High-fidelity Aeroelastic Analysis of Very Flexible Aircraft

Hallissy

Cesnik

2011

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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“…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%

“…Following [6], we construct a new HALE wing model to simulate a HALE wing flexibly suspended at its root. The boundary constraints at the wing root satisfy the following conditions:…”

mentioning

confidence: 99%

“…In [6][7][8] an experimental high-aspect ratio wing aeroelastic model cantilevered at the root and with a tip mass was constructed and a wind-tunnel test conducted to measure flutter and limit cycle oscillations. For the companion computational model, the theoretical structural equations of motion are based on nonlinear beam theory [11] and the ONERA aerodynamic stall model [12].…”

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confidence: 99%

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Gust Response for Flexibly Suspended High-Aspect Ratio Wings

2010

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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.

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Finite Wings

2017

Introduction to Nonlinear Aeroelasticity

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Experimental and Theoretical Study on Aeroelastic Response of High-Aspect-Ratio Wings

Cited by 252 publications

References 2 publications

High-fidelity Aeroelastic Analysis of Very Flexible Aircraft

High-fidelity Aeroelastic Analysis of Very Flexible Aircraft

Gust Response for Flexibly Suspended High-Aspect Ratio Wings

Finite Wings

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