Aeroelastic analysis of a composite wingbox with varying root flexibility

Baets, Peter Wilfried Gaston De; Battoo, R.; Mavris, Dimitri N.

doi:10.2514/6.2000-1623

Cited by 3 publications

(2 citation statements)

References 5 publications

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“…The aeroelasticity of composite high aspect ratio wings modelled using an exact beam formulation has been considered by Cesnik et al [27] where a composite spar-box with flap-twist coupling has been considered, and the effect of various ply angles on the instability of the wing has been assessed. Baets et al [28] looked at the aeroelastic behaviour and flutter speed sensitivity of composite spar-box wings with root flexibility; they observed that wing's root flexibility significantly affects its stability and can change both flutter and divergence speeds. The effect of combined twisting and bending actuation on the aeroelasticity of composite high aspect ratio wings has been investigated by Cesnik et al [29] where the nonlinear aeroelastic response of the wing with embedded anisotropic piezoelectric actuators was considered.…”

Section: Introductionmentioning

confidence: 99%

The effect of elastic couplings and material uncertainties on the flutter of composite high aspect ratio wings

Amoozgar

Ajaj

Cooper

2022

Journal of Fluids and Structures

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Section: Introductionmentioning

confidence: 99%

The effect of elastic couplings and material uncertainties on the flutter of composite high aspect ratio wings

Amoozgar

Ajaj

Cooper

2022

Journal of Fluids and Structures

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“…Chen [5] proposed a complex wing box system and studied empirical mode decomposition (EMD) by using the Hilbert-Huang transform (HHT). Baets [6,7] investigated the sensitivity of the flutter speed, divergence speed and modal response when varying the composite skin lay-up, fiber orientation, and the root flexibility of the model. Ovesy [8] concluded that optimum lay-up configuration had great dependency to the buckling modal shape of the wing box.…”

Section: Introductionmentioning

confidence: 99%

Natural characteristics analysis of aircraft wing box based on finite element method and measured data

Zhang¹,

Ling²,

Xu³

et al. 2018

Vib. proced.

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Compared with other mechanical products, aircraft structures have more rigorous requirements on flying performance, safety, reliability and service life. Based on the finite element method (FEM), the key component of the wing box model is explored in this paper, which provides a reference for the structure design and manufacture of aircraft wing box. The three-dimensional point cloud data of components are obtained by optical measurement systems, the deviation analysis between the point cloud model and the nominal model is carried out as a prerequisite, and then the natural characteristics of the model is analyzed. The results show that 99.15 % of the measured points have deviations within 0.38 mm, which verifies the accuracy of the nominal model. The first six modes are all bending modal shape, and the larger amplitude region mainly occurs in the wing ribs, which means its bending strength should be improved for structure design. Besides, the sixth-mode simultaneously result in front spar, stringer and rib bending vibration.

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Effects of Elastic Foundations on Flutter of High Aspect Ratio Wings

Kriskovich¹,

Eslami²,

Dhainaut³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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This work studies the flutter characteristics of a metallic high-aspect ratio wing, with linearly varying chord across the semi-span, and a simulated elastic foundation at the root. The general planform of the wing is similar to the one found in a High-Altitude Long-Endurance Uninhabited Aerial Surveillance Vehicle (HALE USAV). The problem is studied using a simplified aerodynamic loading based on thin-airfoil theory, which is then combined with a Lagrangian formulation to solve the system as stationary. The wing has no control surfaces or external stores, and is modeled as a beam with known mechanical properties, being attached to a combination of torsion springs at the root to reproduce the elastic foundation. The analysis of the problem includes the development of a Matlab 14 code, which permits different root conditions to be defined, and computes the flutter speed and frequency, outputting information in the form of plots and data lists. I. IntroductionThe study and understanding of the flutter characteristics of a wing is extremely important during the aircraft design process. This structural dynamics phenomenon is responsible for limiting the flight speed due to its unstable nature, and represents a potentially catastrophic condition if not taken properly into account. Flutter is understood as the harmonic oscillation of a structural member as a result of its interaction with the surrounding fluid stream. In the case of wing flutter, the wing is subjected to aerodynamic loads as it moves into the airstream; when the harmonic oscillations for bending and torsion are coupled with no damping, any increase in the airspeed will introduce an increase in the amplitude of these oscillations, making the structure unstable and leading to the risks which this represents. At this particular airspeed, the structure is said to reach its critical flutter speed. The flutter phenomenon related to aircraft structures has been studied for many years, for almost all different types of wing configurations and airspeed regimes such as subsonic incompressible flow (sailplanes, general aviation aircraft, etc.), transonic compressible flow (high speed turboprops, jet liners, propeller and turbo machinery blades, etc.), supersonic compressible flow with the effects of temperature (jet fighters and jet liners, missiles, etc.), and hypersonic compressible flow with heat interaction for space reentry vehicles. In the classical theoretical approach for the flutter of a cantilever wing, the wing's root boundary conditions are typically fixed constraints requiring all displacements and rotations at the boundary to be zero with no damping. These conditions make solution to the problem tractable and complete. Using this approach and a simplified aerodynamic load, the flutter of a uniform cantilever wing was studied by the author of this report in a previous work 1 (using a similar model to the one developed by Dhainaut 2 to study the aeroelastic behavior of swept wings) that was validated with results obtained by Goland 3 in his work on th...

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Aeroelastic analysis of a composite wingbox with varying root flexibility

Cited by 3 publications

References 5 publications

The effect of elastic couplings and material uncertainties on the flutter of composite high aspect ratio wings

The effect of elastic couplings and material uncertainties on the flutter of composite high aspect ratio wings

Natural characteristics analysis of aircraft wing box based on finite element method and measured data

Effects of Elastic Foundations on Flutter of High Aspect Ratio Wings

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