• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.117-117
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• 2004

일반적으로 접촉 피로 마멸은 구름 또는 미끄럼 접촉시 작용하는 반복 응력에 의해 표면과 표면 아래에 균열이 형성되고 성장 및 합체의 과정을 거쳐 표면의 일부가 떨어져 나가는 손상으로 기어나 캠-롤러, 구름 베어링과 같이 구름-미끄럼 접촉상태로 운전하는 기계요소에서 가장 중요하게 고려되어야 할 파손 메커니즘이다. 특히 기어나 구름 베어링 같이 고주기 접촉 피로 특성을 지니는 기계요소의 수명은 피로수명 실험과 통계적 기법을 이용한 Weibull 이론을 기초로 한 수명식을 대부분 사용하고 있다.(중략)

• Journal of the KSME
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• v.29 no.2
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• pp.125-137
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• 1989

구름접촉 피로는 반복적인 구름 접촉에 의해 나타나는 것으로서 피로의 원인이 되는 반복 하중이 두 물체의 반복적인 접촉에 의해서 일어난다는 점 때문에 일반적으로 피로연구 분야에서 다루 어지지 않고 마멸, 마찰 연구 분야에서 다루어지고 있다 구름접촉 피로현상이 나타나는 실제 예로서 베어링, 철도레일 등이 있다.

• Korean Journal of Materials Research
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• v.7 no.9
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• pp.744-749
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• 1997

본 연구에서는 고주파 유도경화처리한 중탄소강의 회전접촉 피로거동을 0.44wt.%C강과 0.55wt.%C강을 사용하여 조사하였다. 회전접촉 피로시험은 Polymet RCF-1 시험기에서 탄성유체 윤활 조건으로 회전속도 8,000rpm, 최대 Hertz응력 492kg/m$m^2$을 가하면서 실시하였다. 미세한 lath마르텐사이트가 고주파 유도경화한 0.44wt.%C강과 0.55wt.%C강의 표면경화층에 형성되었고 소량의 페라이트가 일부 형성되었으며 0.44wt.%C강과 0.55wt.%C에 비해 비교적 큰 페라이트가 나타났다. 회전접촉 피로시험 후 표면경도가 거의 유지되는 표면경화층에서 회전접촉 피로시험전에 비해 경도가 상승하였다. 이 경도증가량의 최대치($\Delta$ Hv$_{max}$)와 피로수명과의 관계를 조사한 결과 0.55wt.%C강이 0.44wt.%C강에 비해 회전접촉 피로중에 일어나는 소변형에 대한 높은 저항성에 주로 기인하여 $\Delta$ Hv$_{max}$값은 낮게 나타나고 피로수명은 높게 나타났다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.601-611
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• 2007

Most of mechanically jointed aircraft structures are always encountered the fretting damages on the contact surfaces between two jointed structural members or at the edges of fastener holes. The partial slip and contact stresses associated with fretting contact can lead to severe reduction in service lifetime of aircraft structures. Thus a critical need exists for predicting fretting crack initiation in mechanically jointed aircraft structures, which requires characterizing both the near-surface mechanics and intimate relationship with fretting parameters. In this point of view, a series of fretting fatigue specimen tests for 2024-T351 Al-alloy, have been conducted to validate a mechanics-based model for predicting fretting fatigue life. And included in this investigaion were elasto-plastic contact stress analyses using commercial FEA code to quantify the stress and strain fields in subsurface to evaluate the fretting fatigue crack initiation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.7
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• pp.642-652
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• 2009

Most of lap jointed aircraft structures encounter the fretting damages, which provoke fretting cracks prematurely and lead to significant reduction of fatigue life. In the case of ageing aircrafts especially, this fretting fatigue problem is a fatal threat for the safety and airworthiness. Recently, as the service life extension program(SLEP) of ageing aircrafts has become a hot issue, the prediction of fretting fatigue life is also indispensable. On these backgrounds, a series of experimental tests of fretting fatigue on bolted lap joint specimens, were performed. And the fretting crack initiation and propagation life of each specimen were evaluated using existing and newly proposed prediction models with the fretting parameters obtained from the FEA results for elasto-plastic contact stress analyses. The validations of prediction models were also discussed, comparing the prediction results with experimental test ones.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.26 no.3
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• pp.199-205
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• 2013

In this study, the methodology for the fatigue life prediction using finite element method(FEM) in wire, bundle and assembly level of the wire harness system and the development of the fatigue life test machine for the numerical analysis are investigated. To obtain stress-life(S-N) histories of the componential wires of the system, five kinds of wires are prepared and applied to the repeated bending motion using developed fatigue life test equipment. Equivalent model of the wire from the rule of mixtures theory is used for the material modeling of sheath and wire core combination. Contact conditions among the wires, taping conditions are established through the bundle level test and numerical bundle analysis. Wire and bundle level results are adopted for the assembly level analysis. For the assembly level analysis, real wire harness system including bundle and grommet is numerically modeled and applied contact condition between wires with real opening motion. The fatigue life more than 700,000 cycles of the assembly is obtained from the FEM, and it is confirmed that the result has good agreement with the experimental result.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1995.06a
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• pp.25-30
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• 1995

본 연구에서는 건식 구름접촉시 발생하는 tribological한 현상들을 plate on ball tester를 이용하여 실험적으로 고찰하였다. 실험의 주된 관심은 각 열처리 방법으로 제작한 시편에 대하여 건식 구름접촉시 cycle수에 따른 plate의 표면 거칠기, 트랙의 형상, 졍도 및 구름저항의 변화이며 이런 자료를 토대로 열처리공정의 차이에서 오는 정도수명 및 피로수명에 대한 상대평가를 통해 마찰, 마멸의 저감에 적합한 열처리방법을 제시하고자 한다.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.36 no.11
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• pp.1391-1397
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• 2012

A cam ring gear (CRG) system based on a hypotrochoid curve consists of a pinion with roller teeth and its conjugated internal CRG. In this study, we investigated contact forces, contact stresses, and load stress factors to predict the surface pitting life using an exact CRG profile by introducing the profile modification coefficient. The results show that the pitting life can be extended significantly by increasing the profile modification coefficient without any other change of parameters in the CRG system.

• Journal of the Korean Society for Precision Engineering
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• v.33 no.1
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• pp.53-61
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• 2016

Angular misalignment has a significant effect on the characteristics of angular contact ball bearings (ACBBs). This paper presents an analysis of fatigue life for ACBBs subjected to angular misalignment. A simulation model is developed with de Mul's bearing model and the ISO basic reference rating life model. Simulation is performed to calculate the life of the ACBBs subjected to angular misalignment. The numerical results show that angular misalignment influences the load distribution significantly, thus reducing the bearing rating life. The fatigue life of ACBBs is decreased by angular misalignment regardless of axial preload, external radial load and rotational speed. The results show that angular misalignment should be maintained at less than 1mrad for ACBBs.

• Transactions of the Korean Society of Automotive Engineers
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• v.16 no.3
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• pp.137-143
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• 2008

For most bearings, it is a common requirement to have long durability. Especially wheel bearing fatigue life is the most important in automotive quality. The contact fatigue life analysis of automotive wheel bearing considering real raceway rough surface is presented in this paper. Contact stresses are obtained by contact analysis of a semi-infinite solid based on the use of influence functions; the subsurface stress field is obtained using rectangular patch solutions. Mesoscopic multiaxial fatigue criterion which can yield satisfactory results for non-proportional loading is then applied to predict fatigue damage. Suitable counting method and damage rule were used to calculate the fatigue life of random loading caused by rough surface. The life analysis considering real rough surface of wheel bearing raceway is in good agreement with the experimental results.