Aeroelastic Analysis of High Aspect Ratio Wings Using Joined 3D Finite Elements and Variational Asymptotic Beam Models

2017 ◽  
Author(s):  
Hanif Hoseini ◽  
Dewey H. Hodges
Keyword(s):  
Finite Elements ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aeroelastic Analysis ◽  
Variational Asymptotic

Absolute Nodal Coordinate Formulation With Vector-Strain Transformation for High Aspect Ratio Wings

2020 ◽  
Vol 16 (1) ◽  
Author(s):  
Keisuke Otsuka ◽  
Yinan Wang ◽  
Kanjuro Makihara
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Degrees Of Freedom ◽  
Absolute Nodal Coordinate Formulation ◽  
Lattice Method ◽  
Absolute Nodal Coordinate ◽  
Aeroelastic Analysis ◽  
Strain Transformation ◽  
Highly Nonlinear ◽  
Analytical Approaches

Abstract High aspect ratio wings are potential candidates for use in atmospheric satellites and civil aircraft as they exhibit a low induced drag, which can reduce the fuel consumption. Owing to their slender and light weight configuration, such wings undergo highly flexible aeroelastic static and dynamic deformations that cannot be analyzed using conventional linear analysis methods. An aeroelastic analysis framework based on the absolute nodal coordinate formulation (ANCF) can be used to analyze the static and dynamic deformations of high aspect ratio wings. However, owing to the highly nonlinear elastic force, the statically deformed wing shape during steady flight cannot be efficiently obtained via static analyses. Therefore, an ANCF with a vector-strain transformation (ANCF-VST) was proposed in this work. Considering the slender geometry of high aspect ratio wings, the nodal vectors of an ANCF beam element were transformed to the strains. In this manner, a constant stiffness matrix and reduced degrees-of-freedom could be generated while capturing the highly flexible deformations accurately. The ANCF-VST exhibited superior convergence performance and accuracy compared to those of analytical approaches and other nonlinear beam formulations. Moreover, an aeroelastic analysis flow coupling the ANCF-VST and an aerodynamic model based on the unsteady vortex lattice method was proposed to perform the static and dynamic analyses successively. The proposed and existing aeroelastic frameworks exhibited a good agreement in the analyses, which demonstrated the feasibility of employing the proposed framework to analyze high aspect ratio wings.

On the use of high aspect ratio finite elements to model hydraulic fracturing in deformable porous media

2019 ◽  
Vol 350 ◽  
pp. 57-80 ◽  
Author(s):  
Osvaldo L. Manzoli ◽  
Pedro R. Cleto ◽  
Marcelo Sánchez ◽  
Leonardo J.N. Guimarães ◽  
Michael A. Maedo
Keyword(s):  
Porous Media ◽  
Finite Elements ◽  
Aspect Ratio ◽  
Hydraulic Fracturing ◽  
High Aspect Ratio ◽  
Deformable Porous Media

2D numerical modeling of naturally fractured media using finite elements with high aspect ratio

2017 ◽  
Author(s):  
Pedro Rogério Cleto ◽  
Osvaldo Luís Manzoli ◽  
Heber Agnelo Antonel Fabbri ◽  
Eduardo Alexandre Rodrigues ◽  
José Henrique Krähenbühl Ambiel
Keyword(s):  
Numerical Modeling ◽  
Finite Elements ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Fractured Media ◽  
Naturally Fractured

Non-linear aeroelastic analysis in the time domain of high-aspect-ratio wings: Effect of chord and taper-ratio variation

2016 ◽  
Vol 121 (1235) ◽  
pp. 21-53 ◽  
Author(s):  
A. Suleman ◽  
F. Afonso ◽  
J. Vale ◽  
É. Oliveira ◽  
F. Lau
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Bending Moment ◽  
Equilibrium Solutions ◽  
Computational Framework ◽  
Wing Model ◽  
Aeroelastic Analysis ◽  
Non Linear ◽  
Time Marching ◽  
The Time Domain

ABSTRACTCommercial jets usually have relatively low-aspect-ratio wings, in spite of the associated benefits of increasing the wing aspect-ratio, such as higher lift-to-drag ratios and ranges. This is partially explained by the fact that the wing becomes more flexible by increasing the aspect-ratio that results in higher deflections which can cause aeroelastic instability problems such as flutter. An aeroelastic computational framework capable of evaluating the effects of geometric non-linearities on the aeroelastic performance of high-aspect-ratio wings has been developed and validated using numerical and experimental data. In this work, the aeroelastic performance of a base wing model with 20 m span and 1 m chord is analysed and the effect of changing the wing chord or the taper-ratio is determined. The non-linear static aeroelastic equilibrium solutions are compared in terms of drag polar, root bending moment and natural frequencies, and the change in the flutter speed boundary is assessed as a function of aspect-ratio using a time-marching approach.

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