scholarly journals Effect of ply angle on nonlinear static aeroelasticity of high-aspect-ratio composite wing

2020 ◽  
Vol 22 (4) ◽  
pp. 959-970
Author(s):  
Junli Wang ◽  
Shuai Lei ◽  
Tuolei Li ◽  
Wensheng Zhang ◽  
Zhigui Ren ◽  
...  
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Static Aeroelasticity ◽  
Nonlinear Static ◽  
Composite Wing

scholarly journals Nonlinear Static Aeroelasticity of High-Aspect-Ratio-Wing Aircraft by Finite Element and Multibody Methods

2017 ◽  
Vol 54 (2) ◽  
pp. 548-560 ◽  
Author(s):  
Michele Castellani ◽  
Jonathan E. Cooper ◽  
Yves Lemmens
Keyword(s):  
Finite Element ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Static Aeroelasticity ◽  
Nonlinear Static

Numerical analysis of geometrical nonlinear aeroelasticity with CFD/CSD method

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Xueyuan Nie
Keyword(s):  
Finite Element ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Data Transfer ◽  
Geometrical Nonlinearity ◽  
Three Dimensional ◽  
Geometrical Nonlinear ◽  
Static Aeroelasticity ◽  
Nonlinear Static ◽  
Linear And Nonlinear

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.

Structural design and analysis of a composite wing with high aspect ratio

2019 ◽  
Vol 20 (10) ◽  
pp. 781-793 ◽  
Author(s):  
Yu-shan Meng ◽  
Li Yan ◽  
Wei Huang ◽  
Tian-tian Zhang ◽  
Zhao-bo Du
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Structural Design ◽  
Composite Wing

SOME ASPECTS OF MODELING A HIGH-ASPECT-RATIO COMPOSITE WING-BOX BY AN ANISOTROPIC BEAM

2015 ◽  
Vol 46 (3) ◽  
pp. 289-305 ◽  
Author(s):  
Sergei Aleksandrovich Tuktarov ◽  
Vasilii Vasil'evich Chedrik
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Composite Wing ◽  
Wing Box

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

2013 ◽  
Vol 302 ◽  
pp. 377-383 ◽  
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.

HALE UAV Composite Wing Structure Design

2010 ◽  
Vol 123-125 ◽  
pp. 105-108
Author(s):  
Myoung Keon Lee ◽  
Chang Min Cho ◽  
Se Yong Jang
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Composite Structure ◽  
Buckling Analysis ◽  
Design Parameters ◽  
Critical Design ◽  
Design Requirements ◽  
Wing Structure ◽  
Long Endurance ◽  
Composite Wing

HALE (High Altitude Long Endurance) UAVs are aircraft systems for surveillance and reconnaissance for over 25 hours. Most of UAVs consist of fuselage and high aspect ratio wing because of long-endurance flight mission. The structural weight of HALE UAV is one of the most critical design requirements. In addition, the structural stiffness for the high aspect ratio wing is another critical design requirement because the UAV has to keep the minimum clearance between wing tip and ground when the UAV is being towed. For above design requirements, the wing structure of the UAV has been designed by intermediate modulus Gr/Ep composite materials. The goal of this research is to present the optimized design concepts for the composite wing structure of the UAV. Although there are many design parameters for the composite structure of the aircraft, this research is focused on composite structure strength and buckling analysis for the plate type structures, such as cover panel skins and spar webs, which are loaded in in-plane shear and/or compression. This research presents that the wing structural weight can be reduced when the material allowables based on tape laminate are applied instead of unidirectional lamina allowables. For the buckling analysis, this report has a trade off study to find an optimized lay-up design and stacking sequence with 0°, ±45° and 90° plies. This research shows that the critical buckling load is a function of the number of ±45° plies and the position of the ±45° plies through the laminate thickness using a typical Gr/Ep composite tape material. The structural design of the UAV composite wing regarding buckling analysis is more effective when the laminates are stacked up with high percent of ±45° plies and the ±45° plies are located toward outside through the laminate.

Sign in / Sign up

Export Citation Format

Share Document