Nonlinear Static Aeroelasticity of High Aspect Ratio Wing Aircraft by FEM and Multibody methods

Abstract A nonlinear static aeroelastic methodology based on the coupled CFD/CSD approach has been developed to study the geometrical nonlinear aeroelastic behaviors of high-aspect-ratio or multi-material flexible aerial vehicles under aerodynamic loads. The Reynolds-averaged Navier–Stokes solver combined with the three-dimensional finite-element nonlinear solver is used to perform the fluid-structure coupling simulation. The interpolation technique for data transfer between the aerodynamic and structural modules employs radial basis function algorithm as well as dynamic mesh deformation. A high-aspect-ratio structure with multi-material is modeled by the finite element method to investigate the effects of geometrical nonlinearity on the aeroelastic behavior. Numerical simulations of the linear and nonlinear static aeroelasticity were conducted at transonic regime with different angles of attack. By comparing the aeroelastic behaviors of linear and nonlinear structure, it shows that geometrical nonlinearity plays an important role for flexible high-aspect-ratio wings undergoing the large static aeroelastic deformation and should be taken into account in aeroelastic analysis for such structures.

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Static Aeroelasticity Analysis of High Aspect Ratio Wing and the Jig-Shape Design Based on Multi-Block Structural Grid

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.302.377 ◽

2013 ◽

Vol 302 ◽

pp. 377-383 ◽

Cited By ~ 2

Author(s):

Yan Liu ◽

Jun Qiang Bai ◽

Jun Hua

Keyword(s):

Aspect Ratio ◽

Design Process ◽

High Aspect Ratio ◽

Design Method ◽

Aerodynamic Characteristics ◽

Shape Design ◽

Transport Aircraft ◽

Mesh Motion ◽

Static Aeroelasticity ◽

Motion Method

The influence of structural elastic deformation on the aerodynamic characterisitcs of large transport aircraft has been researched. A method of static aeroelasticity based on multi-block structural grid of high aspect ratio wing has been established, and then a design method of jig-shape is developed. The technology of RBF interpolation is used to exchange the data of CFD/CSD. Based on RBF&Delaunay technology, a mesh motion method is developed to make the design process less time-consuming, which can be applied to large deformation of multi-block structural grid. The static aeroelastic deformation of a wing-body of large transport aircraft is analyzed. Then the wing-body's jig-shape is designed. Compared the aerodynamic characteristics between design cruise shape and target cruise shape, it shows that the aerodynamic characteristics of design cruise shape is almost equal to target cruise shape and the design process of jig-shape is feasible.

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Nonlinear Static Aeroelastic Analysis of a High-Aspect-Ratio Wing with Large Deflection Effects

Journal of the Korean Society for Aeronautical & Space Sciences ◽

10.5139/jksas.2006.34.3.031 ◽

2006 ◽

Vol 34 (3) ◽

pp. 31-36 ◽

Cited By ~ 2

Keyword(s):

Aspect Ratio ◽

High Aspect Ratio ◽

Large Deflection ◽

Aeroelastic Analysis ◽

Nonlinear Static

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Fuel efficiency optimization of high-aspect-ratio aircraft via variable camber technology considering aeroelasticity

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410020959964 ◽

2020 ◽

pp. 095441002095996

Author(s):

Liqiang Guo ◽

Jun Tao ◽

Cong Wang ◽

Miao Zhang ◽

Gang Sun

Keyword(s):

Aspect Ratio ◽

High Aspect Ratio ◽

Fuel Efficiency ◽

Free Form ◽

Deformation Method ◽

Grid Deformation ◽

Computational Structural Dynamics ◽

Control Matrix ◽

Nonlinear Static ◽

Original Configuration

In this study, variable camber technology is applied to improve the fuel efficiency of high-aspect-ratio aircraft with aeroelasticity considered. The nonlinear static aeroelastic analyses are conducted for CFD/CSD (computational fluid dynamics/computational structural dynamics) numerical simulations. The RBF (radial basis function) method is adopted for the transmission of aerodynamic loads and structural displacements, the diffusion smoothing method is employed for grid deformation in each iteration of CFD/CSD coupling, and the FFD (free-form deformation) method is introduced for the parameterization of variable camber wing. Based on the aerodynamic characteristic curves under different cambers, the discrete variable camber control matrix for the high-aspect-ratio aircraft during the cruise phase is established. The Fibonacci method is employed to optimize the fuel efficiency by utilizing the control matrix. The results indicate that the drag during the cruise phase is reduced obviously and the fuel efficiency is improved evidently comparing to the original configuration.

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