• Elastomers and Composites
• /
• v.47 no.3
• /
• pp.194-200
• /
• 2012

Rubber components have been widely used in automotive industry as anti-vibration components for many years. These subjected to fluctuating loads, often fail due to the nucleation and growth of defects or cracks. To prevent such failures, it is necessary to understand the fatigue failure mechanism for rubber materials and to evaluate the fatigue life for rubber components. The objective of this study is to develop the durability analysis process for vulcanized rubber components, which is applicable to predict fatigue life at initial product design step. The determination method of nonlinear material constants for FE analysis was proposed. In order to investigate the applicability of the commonly used damage parameters, fatigue tests and corresponding finite element analyses were carried out and strain energy density was proposed as the fatigue damage parameter for rubber components. The fatigue analysis for automotive rubber components was performed and the durability analysis process was reviewed.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.36 no.10
• /
• pp.1275-1282
• /
• 2012

Helicopter rotor systems are dynamically loaded structures with many composite components such as the main and the tail rotor blades. The fatigue properties of composite materials are extremely important to design durable and reliable helicopter rotor blades. The safe-life methodology has generally been used in the helicopter industry to substantiate dynamically loaded composite components. However, it cannot be used to evaluate the strength reducing effects of flaws and defects that may occur during manufacturing and operational usage. The damage tolerance methodology provides a proper means to overcome this shortcoming; however, it is difficult to economically apply it to every composite component. The flaw tolerant methodology is an equivalent option to the damage tolerance methodology for civil and military rotorcraft. In this study, the flaw tolerant safe-life evaluation is described and illustrated by means of successful application to substantiate the retirement time of composite rotor blades.

• Proceedings of the Korea Concrete Institute Conference
• /
• 1990.10a
• /
• pp.23-28
• /
• 1990

지진하중에 의한 콘크리트의 손상 및 파괴의 적절한 평가를 위한 많은 연구가 수행되고 있지만 현재까지 손상을 당한 부재의 잔여강도를 예측할 수 있는 적절한 손상 모델이 없는 실정이다. 본 논문은 콘크리트의 손상에 관한 기본적인 현상들을 면밀히 조사 연구한 후 콘크리트의 low-cycle 피로현상을 해석모델링하여 반복하중 하에서의 손상모델을 제안하였다. 제안된 모델은 콘크리트가 파괴에 도달할 시 싸이클 수 대신에 부재의 흡수에너지 능력을 주요변수로 택하였다. 특히 본 손상모델으 정확성은 기 제안한바 있는 반복하중 작용시의 콘크리트 부재의 해석적인 이력모델[3]을 사용하여 예증하였다.

• Proceedings of the Computational Structural Engineering Institute Conference
• /
• 2011.04a
• /
• pp.195-198
• /
• 2011

석유 및 천연가스 생산에 사용되는 고정식 해양플랜트에는 자켓 구조물이 가장 많이 사용되고 있다. 생산에 사용되는 자켓 구조물은 풍하중이나 파랑하중에 의해 인명의 피해 없이 변위 및 응력에 대해 안전해야 한다. 그러나 1940년대 후반부터 사용되어 온 자켓 구조물은 피로하중, 노후화로 인해 내구성에 문제가 생기고 있다. 본 논문에서는 자켓 구조물의 안전성을 검토하기 위해 모드형상을 이용하여 자켓 구조물의 손상 위치를 탐색하는 방법을 제시한다. 제시한 손상탐지기법의 효용성을 입증하기 위해 자켓 구조물의 유한요소모델에 임의의 손상을 모사하였다. 유한요소모델의 손상 전 모드형상과 손상 후 모드형상의 모달 변형에너지의 변화를 이용하여 손상 지수를 유도하고 유도한 손상지수를 사용하여 손상이 있는 부재와 손상이 없는 부재를 분류하였다. 연구 결과 손상지수가 '0'인 부재를 제외한 나머지 부재 모두 본 연구에서 제시한 손상탐지기법으로 손상 부재를 판별할 수 있었다.

• Journal of the Korean Society for Nondestructive Testing
• /
• v.35 no.3
• /
• pp.179-184
• /
• 2015

In this study, the flap fatigue test of a 48 m long wind turbine blade was performed for 1 million cycles to evaluate the characteristics of acoustic emission signals generated from fatigue damage of the wind blades. As the number of hits and total energy continued to increase during the first 0.6 million cycles, blade damage was constant. The rise-time result showed that the major aspects of damage were initiation and propagation of matrix cracks. In addition, the signal analysis of each channel showed that the most seriously damaged sections were the joint between the skin and spar, 20 m from the connection, and the spot of actual damage was observable by visual inspection. It turned out that the event source location was related to the change in each channel's total energy. It is expected that these findings will be useful for the optimal design of wind turbine blades.

• Journal of the Korean Society for Nondestructive Testing
• /
• v.19 no.2
• /
• pp.129-144
• /
• 1999

플랜트와 같은 장치산업은 내구성 구조물이므로 사용중에 열화가 발생하는 것은 필연적이다. 특히 고온, 고압의 부식환경하에서 사용되는 설비는 손상이 심하므로 가동중에 돌발적인 고장이 발생하여 플랜트의 가동을 중지하거나 파손사고가 일어나 생산손실은 물론 경우에 따라서는 안전사고의 발생, 환경오염 등 사회적인 문제를 일으키므로 이들 설비의 경년열화 실체를 충분히 이해하고 대책을 수립하는 것은 대단히 중요하다. 따라서 본고에서는 장치산업에서 발생하는 열화현상(재료의 연화, 경화 및 취화, 크리프, 피로, 부식, 마모 등)중 손상의 주류를 이루는 연화, 경화 및 취화, 크리프 피로에 대하여 기본적인 손상기구(damage mechanism)와 비파괴적 진단 및 평가 방법에 주안점을 두어, 현재 국내의 각종 플랜트 진단에 실용화된 기술을 해설하여 이 분야에 종사하는 관계자 여러분의 이해에 조금이라도 기여코자 한다.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.37 no.10
• /
• pp.1251-1259
• /
• 2013

In this study, high temperature design and creep-fatigue damage evaluation of a decay heat exchanger (DHX) in the decay heat removal systems of a sodium-cooled fast reactor (SFR) have been performed. Detail design and 3D finite element analysis have been conducted for the DHXs to be installed in active and passive decay heat removal systems in Korean Generation IV SFR, and the DHX installed in the STELLA-1(Sodium integral effect test loop for safety simulation and assessment) at KAERI (Korea Atomic Energy Research Institute). Evaluations of creep-fatigue damage based on full 3D finite element analyses were conducted for the two Mod.9Cr-1Mo steel heat exchangers according to the elevated temperature design codes of ASME Section III Subsection NH and RCC-MR code. Code comparisons were made based on the creep-fatigue damage evaluation and issues on conservatisms of the design codes were discussed.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.34 no.9
• /
• pp.1257-1263
• /
• 2010

The naval structure exposes to environmental vibration of shafted propeller propulsion and engine vibration. The shipboard equipments are developed compliance to MIL-STD-167-1A. For this purpose, vibration fatigue life of shipboard equipment for long lives should be estimate via an analytical approach and vibration test. In this paper, High cycle fatigue strength of cast aluminum alloy A356 using shipboard equipment was evaluated by 14 S-N method. The stress applied on the structure is evaluated by an analytical method(frequency response analysis with sinusoidal input and a fatigue evaluation) to simulate a MIL-STD-167-1A test. The frequency with the maximum equivalent stress is shown by Max. test frequency and the vibration fatigue life of shipboard equipment was estimated by Miner's rule.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.1
• /
• pp.105-112
• /
• 2009

For the purpose of facing battle damage that a fighter is subject to in combat, following recovery procedures such as damage assessment, repair design and structural integrity evaluation are investigated. A sample study is presented on the battle damage of F-15 ECS bay, which is comprised of damage assessment and repair design based on ABDR(Aircraft Battle Damage Repair) skills and work procedure complying with AFTO(Air Force Technical Order) forms. Further, the flight safety of repaired structure is validated and the time the permanent repair should be done is estimated through the evaluation of structural integrity such as the calculation of static strength and fatigue life.

• Journal of Aerospace System Engineering
• /
• v.17 no.4
• /
• pp.126-132
• /
• 2023

Recently, the consideration of eco-friendly technology to reduce greenhouse gas is being emphasized in the aviation field. Various studies for applying electro-mechanical actuators that control mechanical linear and rotational movements using electricity as the primary power source are in progress. In this study, the fatigue analysis of the electro-mechanical actuator for the front wheel steering of a single aisle aircraft was carried out. A unit load stress table was constructed for the vulnerable part selected through structural analysis, and the representative stress for each load profile was calculated using the unit load stress table constructed for the vulnerable part. Then, individual profiles of representative stress group were extracted from continuous load profiles by applying the rainflow counting method. The damage of each profile was calculated by applying the S-N diagram. Finally, the total damage in the vulnerable parts was calculated by the linear cumulative damage law, and the fatigue life of the electro-mechanical actuator for the front wheel steering of a single aisle aircraft was evaluated.