• Journal of the Society of Naval Architects of Korea
• /
• v.36 no.4
• /
• pp.87-94
• /
• 1999

Empirical design is still used to avoid a structural damage because impact phenomenon and structural behaviour due to wave impact load can not examined accurately. The damage due to wave impact load is largely affected by impact pressure impulse and impact load area. The objective of this study is, as the second step, to develop an efficient scantling program of bow flare structure, and to predict its impact load area by comparing maximum dented deformations at center of idealized panel structure model of bow flare structure of 300k DWT VLCC using LS/DYNA3D code, which will be used for its verification of dynamic structural analysis, as the next step. Through this study, the impact load area was estimated as $1.5s{\times}1.5s$ stiffener space(s) in the case of panel with stiffeners and as $2.5s{\times}2.5s$, with stringers, under impact pressure curve with peak height 6.5MPa, tail height 1.0MPa, and duration time 5.0msec.

• Composites Research
• /
• v.16 no.2
• /
• pp.9-17
• /
• 2003

We have implemented a system of falling weight impact tester in order to evaluate the impact energy absorbing characteristics and impact strength of CFRP laminate plates. The absorbed energy of T-300 orthotropic composites is higher than that of quasi-isotropic specimen over impact energy 7J, but in case of using T700 fiber, much difference does not show. Also, absorbed energy of T-300 orthotropic composites, which are composed of the same stacking number and orientation became more than that of T700 fiber specimen however there was no big difference in case of quasi-isotropic specimens. Delamination area of impacted specimens was measured with ultrasonic C-scanner to find correlation between impact energy and delamination area. Delamination area and frequency responses were evaluated between impacted and unimpacted specimens. There is a strong correlation between frequency responses and impact-induced delamination. The presence and scale of damages have been investigated based on the variations of frequency responses.

• Korean Journal of Crystallography
• /
• v.9 no.2
• /
• pp.125-130
• /
• 1998

본 논문에서는 부직포를 삽입한 Gr/Ep 복합재료의 충격 흡수 특성을 연구하였다. 계면(interface) 층에 유리 부직포 또는 탄소 부직포를 삽입하여 복합적층판을 제작하였다. 저속충격 시험을 수행하였으며, 충격에 의한 층간분리(delamination)를 C-Scan과 현미경을 사용하여 관찰하였다. 실험결과 계면에 부직포를 삽입함으로써 충격에 의한 층간분리 면적이 감소함을 알 수 있었다.

• Journal of the Korean Society for Nondestructive Testing
• /
• v.17 no.2
• /
• pp.81-88
• /
• 1997

Impact behavior of carbon fiber reinforced plastics (CFRP) laminates were evaluated with tension test and compact tension test. A steel ball launched by an air gun collides against CFRP laminates to generate impact damage of relatively low energy. The static tensile and fracture toughness tests were performed to evaluate the residual strength and the AE behavior of impact-damaged laminates. As a results, it was found that the static strength, the fracture toughness and the AE-event count were decreased with increasing of impact velocity and delamination area, and to have a different strength ratio and fracture toughness ratio for each stacking method. And also, it was confirmed that strength and fracture toughness of impact-damaged CFRP laminates could be evaluated and analyzed quantitatively by AE techniques.

• Composites Research
• /
• v.18 no.3
• /
• pp.7-13
• /
• 2005

This paper presents a study on the low velocity impact response of the woven fabric laminates for the hybrid composite bodyshell of a tilting railway vehicle. In this study, the low velocity impact tests for the three laminates with size of $100mm\times100mm$ were conducted at three impact energy levels of 2.4J, 2.7J and 4.2J. Based on the tests, the impact force, the absorbed energy and the damaged area were investigated according to the different energy levels and the stacking sequences. The damage area was evaluated by the visual inspection and the C-scan device. The test results show that the absorbed energy of [fill]8 laminate is highest whereas (fill2/warp2)s is lowest. The [fill]8 laminate has the largest damage area because of the highest impact energy absorption.

• Composites Research
• /
• v.13 no.6
• /
• pp.30-38
• /
• 2000

In this paper, a system of falling weight impact tester was built up to evaluate the impact energy absorbing characteristics and impact strength of CFRP laminate plates in consideration of stress wave propagation theory. Delamination area of impacted specimens for the different ply orientation was measured with ultrasonic C-scanner to find correlation between impact energy and delamination area. Absorbed energy of quasi-isotropic specimen having four interfaces was higher than that of orthotropic laminates with two interfaces. The more interfaces, the more absorbed energy. Hybrid specimen containing GFRP layer was higher than that of normal specimens.

• Journal of the Korean Institute of Gas
• /
• v.17 no.6
• /
• pp.52-57
• /
• 2013

In this study, the strain energy density, stress and deformation behaviors have been analyzed as functions of a thickness and a force area of protective helmets with and without an extruder on the top of the shell structure using the finite element method. The strain energy density in which is related to the absorption capacity of an impact energy transfer is one of a key element of the helmet safety. The FEM analyzed results show that when the impulsive force of 4,540N is applied on the top surface of the helmets, the maximum stress is linearly reduced for an increased area of impact forces. But, the maximum strain energy density has been reduced for the increased force area. The reduced strain energy density may increase the impulsive forces transferred to the head and neck of helmet wearers, which may decrease the impact energy absorption safety of the helmets. In thus, it is safer design of the helmet in which has an extruded structure on the summit surface, but the modified helmet may decrease the impact energy absorption capacity.

• Journal of the Korean Society for Nondestructive Testing
• /
• v.17 no.1
• /
• pp.1-10
• /
• 1997

In this paper, the effects of temperature change (low and high temperature) on the impact damages of CFRP laminates was experimentally studied. Composite laminates used for this experiment are CF/epoxy orthotropic laminated plates, which have two-interfaces $[0^{\circ}\;_6/90^{\circ}\;_6]s$ and $[0^{\circ}\;_4/90^{\circ}\;_4]s$. And CF/PEEK orthotropic laminated plates, which have two-interfaces $[0^{\circ}\;_4/90^{\circ}\;_4]s$. And, this study aims experimentally to present the interrelations between the impact energy vs. impact damages (i.e. delamination area and matrix crack) of CFRP laminates (CF/epoxy, CF/PEEK) subjected to FOD(foreign object damage) under low and high temperatures. A steel ball launched by the air gun collides against CFRP laminates to generate impact damages.

• Proceedings of the Korean Society for Agricultural Machinery Conference
• /
• 2002.02a
• /
• pp.257-262
• /
• 2002

본 연구에서는 분쇄방법에 따른 감초 분쇄생성물의 특성을 분석한 결과는 다음과 같다. 1. Hammer mill의 경우 d$_{80}$=750$\mu\textrm{m}$로 중간미분쇄의 입도범위를 가지며 비표면적은 0.269m/g로 분석되었고, Pin mill의 경우 d$_{80}$=600$\mu\textrm{m}$로 Hammer mill보다 입자크기는 조금 작으나 중간미분쇄영역의 입도범위를 가지며 비표면적은 0.324m$^2$/g로 분석되었고, Turbo mill은 d$_{80}$=250$\mu\textrm{m}$와 비표면적은 0.370m$^2$/g로 입자의 크기가 가장 작아 다른 분쇄기보다 분쇄능이 가장 우수한 것으로 분석되었다. 2. Hammer mill의 분쇄메커니즘은 대부분 충격, 일부 전단과 마찰에 의해 분쇄가 행해지고, Pin mill은 핀 사이에서의 전단, 충격, 마찰에 의해 분쇄된다. 즉 충격과 마찰에 의한 분쇄는 전단력에 의한 분쇄메커니즘보다 분쇄 능이나 분쇄효율이 상대적으로 낮은 것을 알 수 있었으며 주로 전단력과 충격, 반발력에 의해 분쇄가 이루어지는 Turbo mill의 분쇄능 및 분쇄 효율이 우수함을 알 수 있었다. 본 연구에 의해서 감초와 같이 섬유질을 많이 함유하고 있는 원료를 분쇄할 경우 분쇄메커니즘이 전단력인 분쇄기가 가장 적합하고, 분쇄중 소요되는 동력 면에서도 기존 분쇄기보다 우수한 Turbo mill의 분쇄조건을 확립해야 한다고 사료된다. 사료된다.

• Journal of the Society of Naval Architects of Korea
• /
• v.37 no.1
• /
• pp.99-110
• /
• 2000

The damages due to wave impact loads are largely affected by impact pressure impulse and impact load area. The objective of this study is, as the third step, to perform dynamic structural analysis of bow flare structure of 300,000 DWT VLCC using LS/DYNA3D code, and to verify its dynamic structural behaviors. The impact load areas of stiffener space $1.5s{\times}1.5s$ and $2.5s{\times}2.5s$ are applied to bow flare structure part with relatively flexible stiffeners, and with stiff members such as stringers, webs etc., respectively, under the wave impact load with peak height 6.5MPa, tail 1.0MPa, and duration time 5.0msec. Through the dynamic structural analysis in this study, it might be thought that the structural strength of bow flare structure is generally sufficient for these wave impact load and areas, except that large damages were found at bow flare structure area with flexible wide span stiffeners.