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

scholarly journals Loads analysis and structural optimization of a high aspect ratio, composite wing aircraft

2021 ◽  
Author(s):  
Kautuk Sinha ◽  
Thomas Klimmek ◽  
Matthias Schulze ◽  
Vega Handojo
Keyword(s):  
Aspect Ratio ◽  
Structural Optimization ◽  
Design Process ◽  
High Aspect Ratio ◽  
Structural Design ◽  
Composite Structures ◽  
Selection Process ◽  
Weight Ratio ◽  
Bending Moment ◽  
Composite Wing

AbstractComposite structures have shown a prominent impact in the aircraft structural design. With an increasing shift towards incorporating more composite materials in the primary aircraft structure it is imperative to have corresponding design tools to simplify the design process. In the present work, a simplified implementation for composite optimization has been developed within the DLR-AE (German Aerospace Centre, Institute of Aeroelasticity) automated aeroelastic structural design framework cpacs-MONA. This paper presents the results of structural optimization of a high aspect ratio composite wing aircraft model developed in the DLR project ATLAs. The generation of almost all involved simulation models for this study is done using the in-house DLR tool ModGen. An aeroelastic trim analysis is conducted for various manoeuvre and gust conditions. A load selection process is used to determine the most relevant sizing load cases. A comparison is made between the optimization results of a composite wing and an aluminium wing to demonstrate the more favourable strength to weight ratio of the composite wing. A manoeuvre load alleviation procedure has been introduced in the load calculation process. The results show further weight savings in the design process when load alleviation is utilized due to reduction in the span wise bending moment.

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

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.

scholarly journals A Study on Manufacture of Integrated Composite Wing with High Aspect Ratio

2013 ◽  
Vol 41 (2) ◽  
pp. 127-133
Author(s):  
Young-Sik Joo ◽  
Oo-Chul Jun ◽  
Kwan-Hwa Byun ◽  
Chang-Min Cho ◽  
Jin-Wook Han
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Composite Wing

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
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