Aeroelastic tailoring using crenellated skins-modelling and experiment

François, Guillaume; Cooper, Jonathan E.

doi:10.12989/aas.2017.4.2.093

Cited by 4 publications

(4 citation statements)

References 23 publications

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“…shape and root/tip chord wise location) of the spars and stringers as illustrated in Figure 1. An un-tapered wind tunnel model wing was chosen as a test case in this work as experimental studies of this wing geometry have also been performed elsewhere 32,33 ; the underlying conclusions from the work is expected to scale up to a full-scale aircraft wing model. The figures illustrating the shape of structural elements have the spars, the ribs, the stringers, the wing aerodynamic limits and the wing flexural axis shown in red, blue, black, magenta and green respectively.…”

Section: A Concept Exploredmentioning

confidence: 99%

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Aeroelastic Tailoring using the Spars and Stringers Planform Geometry

François

Cooper

2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. The aeroelastic performance of a wing, including static aeroelastic shape, flutter/divergence speed and gust load response, has a significant influence on aircraft design. The tailoring of aeroelastic responses therefore offers potential weight savings. In this paper, the spars and stringers planform geometry (i.e. shape and root/tip chord wise location) on a representative wind tunnel model aircraft wing are used to modify the wing aeroelastic performance. Several optimisations are performed to illustrate the ability of the spars and stringers planform geometrical features to change the wing vibrational mode natural frequencies, deformation under a static tip load and aerodynamic load, gust response and aeroelastic instability speed. Changing the stringers planform geometry is shown to offer minor variation in the wing deformation and loads. Changing the spars planform geometry is shown to enable a reduction in root bending moment under static aerodynamic loading greater than 10%, a reduction in maximum root bending moment encounter during a worst case scenario gust event greater than 10% and a 25% increase in flutter speed. The improvements due to a change in the spar planform geometry are compared to the effect of changing the wing sweep angle. A framework to characterise Euler-Bernoulli beam properties on wings with geometric coupling is then developed and validated to relate the stiffness and bend/twist coupling parameter to the full 3D FE models.

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Section: A Concept Exploredmentioning

confidence: 99%

“…The wing was assumed to be made using a solidified polyamide material -a material used in previous experiments 32,33 -with a Young's modulus of 1,650.0MPa, a Poisson's ratio of 0.4 and a density of 1.15g/cm 3 . The material was assumed to be isotropic and homogenous.…”

Section: Figure 2 Wing External Dimensions In MMmentioning

confidence: 99%

Aeroelastic Tailoring using the Spars and Stringers Planform Geometry

François

Cooper

2017

58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…For a given sweep angle the variation of the rib orientation from the 0ᵒ orientation implies an increase/decrease in rib length and the addition of a half rib at the tip and root thus to maintain the wing mass constant, the rib thickness was varied as the rib orientation changes. The wing was assumed to be made in a solidified polyamide material -a material used in previous experiments 25,26 -with a Young's modulus of 1,650.0MPa, a Poisson's ratio of 0.4 and a density of 1.15g/cm 3 . The material was assumed to be isotropic and homogenous.…”

Section: B Wing Modelmentioning

confidence: 99%

“…In this effort, Harmin et al 24 showed the impact of varying the rib/spar orientation on the wing deformation while Francois et al 25,26 attempted to illustrate such impact through a series of experiments using 3D printed wings. Additionally, there is a need to translate this understanding into simple tools that designers can use in the early design phase to make a better judgement as to how the structural members should be arranged.…”

Section: Introductionmentioning

confidence: 99%

Impact of the Wing Sweep Angle and Rib Orientation on Wing Structural Response for Un-Tapered Wings

François

Cooper

2016

57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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In this paper, the impact of varying the sweep angle of the spar and the rib orientation on wing structural deformation is investigated and related to a beam model. 3D Finite-Element wing wind tunnel models with varying wing sweep angle and rib orientation are considered. The wing models tip displacement and tip twist under static tip loads and aerodynamic loading are considered as well as the wing's natural frequencies, aeroelastic instability speed and maximum root bending moment during a gust encounter. A framework to characterise Euler-Bernoulli beam properties on wings with geometric coupling is then developed and validated to relate the stiffness and bend/twist coupling parameter to the full FE models.

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