Paper Title:
HALE UAV Composite Wing Structure Design
  Abstract

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.

  Info
Periodical
Advanced Materials Research (Volumes 123-125)
Edited by
Joong Hee Lee
Pages
105-108
DOI
10.4028/www.scientific.net/AMR.123-125.105
Citation
M. K. Lee, C. M. Cho, S. Y. Jang, "HALE UAV Composite Wing Structure Design", Advanced Materials Research, Vols. 123-125, pp. 105-108, 2010
Online since
August 2010
Export
Price
$32.00
Share

In order to see related information, you need to Login.

In order to see related information, you need to Login.

Authors: Xiao Jun Shao, Zhu Feng Yue
Abstract:Compressive experiments and finite element method (FEM) have been used to study the mechanical behavior of composite laminate with plies...
301
Authors: Ke Feng Li, Tian Hui Xia
Abstract:The helicopter tail drive shafts are designed by using aluminum alloy conventionally. The composite materials have the advantages of high...
365
Authors: N. Hamani, D. Ouinas, N. Taghezout, M. Sahnoun, J. Viña
Chapter 1: Materials Engineering and Materials Processing
Abstract:In this study, a buckling analysis is performed on rectangular composite plates with single and double circular notch using the finite...
95
Authors: Yue Liang Chen, Yuan Ling Lei, Yong Zhang
Chapter 14: Materials Mechanical Behavior and Fracture
Abstract:The mechanism of injury and damage evolution of composite aircraft is complex, traditional methods fatigue test relies on a large number of...
1558