Experimental investigation of composite laminates subject to low-velocity edge-on impact and compression after impact

被引：42

作者：

Thorsson, Solver I. ^{[1
]}

Sringeri, Sunil P. ^{[1
]}

Waas, Anthony M. ^{[2
]}

Justusson, Brian P. ^{[3
]}

Rassaian, Mostafa ^{[4
]}

机构：

[1] Univ Michigan, Dept Aerosp Engn, Ann Arbor, MI 48109 USA

[2] Univ Washington, William E Boeing Dept Aeronaut & Astronaut, Seattle, WA 98195 USA

[3] Boeing Co, Berkeley, MO 63134 USA

[4] Boeing Co, Seattle, WA 98124 USA

来源：

COMPOSITE STRUCTURES | 2018年 / 186卷

关键词：

Polymer matrix composites; Low velocity impact; Edge-on impact; Compression after impact; Delamination; DAMAGE RESISTANCE; PREDICTION; PANELS; PLATES; TOLERANCE; STRENGTH; BEHAVIOR;

D O I：

10.1016/j.compstruct.2017.11.084

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

In this paper, the experimental response of polymer matrix composite laminates subject to low-velocity edge-on impact and compression after impact is studied. An experimental method for coupon level edge-on impact is introduced. Experiments at different impact energies were conducted to establish the edge-on barely visible impact damage (BVID) limit for a specific laminate. Two different impact angles were investigated, 0 degrees and 45 degrees with respect to the impacted edge. Non-destructive and destructive post impact inspection was conducted. Surface damage measurements by visual inspection were compared against ultrasound scanning methods for validation. Fractography using optical microscopy was performed on chosen impact energies for further visualization of the impact damage mechanisms. Industry standard for compression after face-on (transverse) impact was found to be insensitive to the impact damage. An adjusted version of the Combined Loading Compression (CLC) method was introduced for capturing the compressive strength after edge-on impact. A reduction in compressive strength after impact was seen for the impact energy range studied.

引用

页码：335 / 346

页数：12

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