Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer

被引：1

作者：

Liu, Tiejun ^{[1
,2
]}

Zhang, Yong ^{[3
]}

Li, Gang ^{[3
]}

Wang, Fenghui ^{[1
]}

机构：

[1] Northwestern Polytech Univ, Sch Mech & Civil & Architecture, Xian 710129, Peoples R China

[2] Zhengzhou Inst Aeronaut Ind Management, Dept Mech & Elect Engn, Zhengzhou 450015, Peoples R China

[3] Sales Dept Petrochina Tarim Oilfield Co, Ku erle 841000, Peoples R China

来源：

VIBRATION, STRUCTURAL ENGINEERING AND MEASUREMENT I, PTS 1-3 | 2012年 / 105-107卷

关键词：

Composites; Dynamic response; HALE; Natural frequency; Viscoelastic damping layer; DESIGN;

D O I：

10.4028/www.scientific.net/AMM.105-107.491

中图分类号：

TU [建筑科学];

学科分类号：

0813 ;

摘要：

In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are lower than stiffened structure. The maximum displacement response value decreased when thickness increased and that of laminates is higher than structured with stiffer. The presented work is helpful for type selection and designing of solar powered aircraft wing panel.

引用

页码：491 / +

页数：2

共 50 条

[41] Frequency Response Analysis of Composite Aircraft Wing Using a Finite Element Euler-Bernoulli Beam Model
Bennamia, Ismail
Badereddine, Aimad-eddine
Yahia Cherif, Mansour
Zebbiche, Toufik
ROMANIAN JOURNAL OF ACOUSTICS AND VIBRATION, 2018, 15 (01): : 26 - 32
[42] Importance Measure Analysis for Use in Dynamic Performance Design of a Co-cured Composite Damping Instrument Panel
郝文锐
梁森
Journal of Donghua University(English Edition), 2017, 34 (06) : 780 - 783
[43] DYNAMIC RESPONSE ANALYSIS OF A SOLAR POWERED HELIOTROPIC FLUID-MECHANICAL DRIVE SYSTEM.
Cope, N.A.
Ingley, H.A.
Farber, E.A.
Morrison, C.A.
Alternative Energy Sources: Proceedings of the Miami International Congress on Energy and the Environment, 1979, 1 : 249 - 261
[44] Asymptotic analysis on flexural dynamic characteristics for a laminated composite plate with embedded and perforated periodically viscoelastic damping material core
Zhou, X. Q.
Yu, D. Y.
Shao, X. Y.
Zhang, S. Q.
Wang, S.
COMPOSITE STRUCTURES, 2016, 154 : 616 - 633
[45] Dynamic effective equivalent stiffness analysis on the periodical honeycomb reinforced composite laminated structure filled with viscoelastic damping material
Zhou, X. Q.
Wang, L.
Yu, D. Y.
Zhang, C. Y.
COMPOSITE STRUCTURES, 2018, 193 : 306 - 320
[46] Discrete layer beam finite element for the dynamic analysis of composite sandwich beams with integral damping layers
Acentech Inc, Cambridge, United States
Comput Struct, 6 (647-666):
[47] A discrete layer beam finite element for the dynamic analysis of composite sandwich beams with integral damping layers
Zapfe, JA
Lesieutre, GA
COMPUTERS & STRUCTURES, 1999, 70 (06) : 647 - 666
[48] Comparative Study and Airspeed Sensitivity Analysis of Full-Wing Solar-Powered UAVs Using Rigid-Body, Multibody, and Rigid-Flexible Combo Models
Guo, An
Mu, Shanshan
Zhou, Zhou
Tang, Jiwei
INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING, 2024, 2024
[49] Dynamic response analysis of bird strike on aircraft windshield based on damage-modified nonlinear viscoelastic constitutive relation
Wang Xinjun
Feng Zhenzhou
Wang Fusheng
Yue Zhufeng
CHINESE JOURNAL OF AERONAUTICS, 2007, 20 (06) : 511 - 517
[50] Dynamic Response Analysis of Bird Strike on Aircraft Windshield Based on Damage-modified Nonlinear Viscoelastic Constitutive Relation
Wang Xinjun
Chinese Journal of Aeronautics, 2007, (06) : 511 - 517

← 1 2 3 4 5 →