Response of composite panels subjected to varying impact energies

被引:0
|
作者
Mouring, Sarah E. [1 ]
Louca, Luke A. [2 ]
Johnson, Hayley E. [2 ]
机构
[1] US Naval Acad, Dept Naval Architecture & Ocean Engn, Annapolis, MD 21402 USA
[2] Imperial Coll London, Dept Civil & Environm Engn, London, England
关键词
impact testing; composites; delamination; damage; finite element analysis; cohesive layers;
D O I
暂无
中图分类号
TE [石油、天然气工业]; TK [能源与动力工程];
学科分类号
0807 ; 0820 ;
摘要
The advantages of using fiber reinforced plastics, composed of glass fibers embedded in a resin mix, for offshore structures and shipbuilding have been recognized for many years. These advantages include: (a) reduced weight, (b) better corrosion resistance, (c) lower life cycle costs, (d) no hot work required for retrofitting and (e) better thermal, acoustic and vibration properties. For naval vessels, they have the added advantages of lower signatures and the elimination of fatigue crack issues between steel decks and composite deckhouses. Despite this, their use on large scale structures as primary members has been restricted in the offshore industry. Naval applications have recently increased from the traditional mine countermeasure vessels to large hangers on destroyers. Many other naval applications are being proposed and a large volume of research is currently being undertaken. One of the drawbacks with composites is the lack of robust damage models applicable to large composite structures capable of reliably predicting damage growth and ultimate failure loads. This is particularly so in the prediction of delamination which can occur when composites are subjected to lateral impact or shock loads. The focus of this research is to examine the effects of low-velocity impact loading on the behavior of large-scale composite panels. Comparisons of the contact force and panel displacement are made using both an energy balance model and non-linear finite element analysis (FEA).
引用
收藏
页码:3513 / +
页数:2
相关论文
共 50 条
  • [21] Buckling response of metallic foam composite sandwich panels subjected to edgewise compression
    Wang, Xin-Zhu
    Wu, Lin-Zhi
    Wang, Shi-Xun
    MULTI-FUNCTIONAL MATERIALS AND STRUCTURES II, PTS 1 AND 2, 2009, 79-82 : 1241 - 1244
  • [22] On the response of graphene platelet reinforced composite conical panels subjected to mechanical shock
    Mirzaei, M.
    Jafari, M.
    MATERIALS TODAY COMMUNICATIONS, 2023, 34
  • [23] Low Velocity Impact Response of Composite Panels for Aeronautical Applications
    Grasso, M.
    Penta, F.
    Pucillo, G. P.
    Ricci, F.
    Rosiello, V.
    WORLD CONGRESS ON ENGINEERING, WCE 2015, VOL II, 2015, : 1138 - 1143
  • [24] Low-velocity impact response of composite sandwich panels
    Zhu, Shengqing
    Chai, Gin Boay
    PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART L-JOURNAL OF MATERIALS-DESIGN AND APPLICATIONS, 2016, 230 (02) : 388 - 399
  • [25] Impact response of integrated hollow core sandwich composite panels
    Vaidya, UK
    Hosur, MV
    Earl, D
    Jeelani, S
    COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING, 2000, 31 (08) : 761 - 772
  • [26] Computational Analysis of Low Velocity Impact Response of Composite Panels
    Rahman, Mustafizur
    Morozov, Evgeny V.
    Shankar, Krishna
    Fien, Alan
    MECHATRONICS AND APPLIED MECHANICS, PTS 1 AND 2, 2012, 157-158 : 1135 - 1138
  • [27] Composite structural panels subjected to explosive loading
    Lan, SR
    Lok, TS
    Heng, L
    CONSTRUCTION AND BUILDING MATERIALS, 2005, 19 (05) : 387 - 395
  • [28] Buckling of composite panels subjected to biaxial loading
    Tuttle, M
    Singhatanadgid, P
    Hinds, G
    EXPERIMENTAL MECHANICS, 1999, 39 (03) : 191 - 201
  • [29] Buckling of composite panels subjected to biaxial loading
    M. Tuttle
    P. Singhatanadgid
    G. Hinds
    Experimental Mechanics, 1999, 39 : 191 - 201
  • [30] Comparison of damage in FMLs, aluminium and composite panels subjected to low-velocity impact
    Ma, Yu'e
    Hu, Haiwei
    Xiong, Xiaofeng
    Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica, 2014, 35 (07): : 1902 - 1911