scholarly journals High-fidelity Multipoint Aerostructural Optimization of a High Aspect Ratio Tow-steered Composite Wing

2017 ◽  
Author(s):  
Timothy R. Brooks ◽  
Graeme Kennedy ◽  
Joaquim R. R. A. Martins
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
High Fidelity ◽  
Aerostructural Optimization ◽  
Composite Wing

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

Numerical Simulation of a High-Aspect-Ratio Wing Using High Fidelity Aero-Structural Coupled Method

2013 ◽  
Vol 465-466 ◽  
pp. 352-357
Author(s):  
Ze Hai Wang ◽  
Ming Yun Lv ◽  
Jun Hui Meng ◽  
Guo Quan Tao
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aerodynamic Force ◽  
Geometrical Nonlinearity ◽  
High Fidelity ◽  
Coupled Method ◽  
Design And Optimization ◽  
Rigid Model ◽  
Inherent Nature ◽  
Drag Ratio

High-aspect-ratio wings, with the inherent nature of maximizing the lift-to-drag ratio, have been widely employed in modern airplanes. However, highly flexibility wing structure renders previous rigid model in aerodynamic simulation and ideal aerodynamic force distribution in structural simulation meet serious challenges. In this article, a high fidelity aero-structural coupled method is employed to better evaluating the deformation of a high-aspect-ratio wing. Summarily, this method takes into consideration the aerodynamic redistribution and the geometrical nonlinearity caused by large deformation of the wing, and the deflection calculated using coupled method is approximately 20% more than traditional unidirectional method, providing a more accurate model for structural design and optimization.

Replica Molding of High-Aspect-Ratio Polymeric Nanopillar Arrays with High Fidelity

Langmuir ◽  
2006 ◽  
Vol 22 (20) ◽  
pp. 8595-8601 ◽  
Author(s):  
Ying Zhang ◽  
Chi-Wei Lo ◽  
J. Ashley Taylor ◽  
Shu Yang
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
High Fidelity ◽  
Replica Molding ◽  
Nanopillar Arrays

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.

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