• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회A
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• pp.1766-1771
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• 2007

This paper presents plastic limit loads and approximate J-integral estimates for circumferential part-through surface crack at the interface between elbows and pipes. Based on finite element limit analyses using elastic-perfectly plastic materials, plastic limit moments under in-plane bending are obtained and it is found that they are similar those for circumferential part-through surface cracks in the center of elbow. Based on present FE results, closed-form limit load solutions are proposed. Welds are not explicitly considered and all materials are assumed to be homogeneous. And the method to estimate the elastic-plastic J-integral for circumferential part-through surface cracks at the interface between elbows and straight pipes is proposed based on the reference stress approach, which was compared with corresponding solutions for straight pipes.

• 대한설비공학회지:설비저널
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• 제17권4호
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• pp.466-472
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• 1988

Pneumatic transportation systems are operated most economically, if the transportation velocity is somewhat greater than the limit velocity. Therefore it is very important to find out this limit velocity. That is well known for coarse and fine particles, but not yet for long ribbon type material. In this study a formula for the mass ratio of transported material to air in limit load point is derived for ribbon type material from the pneumatic transportation theory and the model theory. A relationship for estimating the limit velocity is also found out through experiments. The possibility of the generalization of this formula, which is obtained from a given pneumatic transportation system, should be estimated through further systematic studies.

• 한국산학기술학회논문지
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• 제17권1호
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• pp.159-164
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• 2016

본 논문은 전자식 조정장치 헬리콥터의 비행영역 보호를 위한 하중제안 로직 설계에 대한 결과이다. 헬리콥터는 로터, 동체, 엔진등 구조가 복잡하기 때문에 여러 가지 제약조건에 가지고 비행을 해야 한다. 이 때문에 조종사가 그 제약조건을 고려하여 조종을 하면서 조종사의 작업부하가 증가하고 비행 조종성을 떨어뜨리는 결과가 발생한다. 이러한 헬리콥터의 비행제약조건으로부터 자유롭게 조정 하도록 하여 조종사를 도와주는 기능이 필요하고 본 논문에서는 그 중의 대표적인 제약조건인 하중제약조건에 대한 제한 로직을 전자식 조정장치 헬리콥터에 설계하고자 한다. 하중범위를 벗어나는 비행은 피치 싸이클릭 스틱을 급격하게 입력하여 주로 발생한다. 이때 조종스틱 명령과 피치축 자세명령모델사이에 비행영역제한로직을 추가하여 하중범위를 벗어나지 않도록 하였다. 현재의 하중 값에 대한 자세범위를 동적으로 계산하는 로직을 사용하였고 헬리콥터 모델에 적용하여 시뮬레이션을 통하여 알고리즘을 검증하였다. 시뮬레이션을 통하여 정지비행영역, 전진비행영역에서 하중제한로직을 적용하지 않았을 때와 적용하였을 때를 비교한 결과, 하중제한로직을 적용하지 않았을 때는 하중제한 리미트를 20% 이상 초과하였으나 본 연구에서 제한한 로직을 적용하였을 때는 하중제한 리미트가 초과하지 않음을 확인하였다. 결론적으로 시뮬레이션을 통하여 동적으로 할당하는 제한로직이 헬리콥터 전자식 조정장치 제어기에 적합함을 확인하였다.

• 한국구조물진단유지관리공학회 논문집
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• 제26권6호
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• pp.212-221
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• 2022

이 연구에서는 국내 도로교량 평가에서도 설계와 일관성이 있도록 한계상태설계법에 상응하는 평가방법을 마련하고, 선진국과 같이 평가에서 목표신뢰도지수를 감소시키는 경우 신뢰도분석을 통하여 보정하여 평가 활하중계수를 제안한다. 국내 대표 교량형식을 대상으로 수집한 실교량 자료를 활용하여 각 설계기준 별 설계활하중에 대한 하중효과를 산정하여 비교한다. 현행 설계법에 의해 산정된 하중효과를 바탕으로 최소요구강도를 산정하여 이에 대한 신뢰도분석을 통해 활하중계수 보정을 수행한다. 설계수준에 비하여 낮춰진 평가수준의 활하중계수를 교량 안전성평가를 수행하고, 이전 설계법의 안전성평가 결과와 비교하여 평가결과가 증가함을 확인하였다.

• 한국자동차공학회논문집
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• 제22권4호
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• pp.121-130
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• 2014

This paper is the second investigation on the effects of intake flow control methods on the part load performance in a spark ignition engine. In the previous work, two control methods, port throttling and masking, were compared with respect to lean misfire limit, fuel consumption and emissions. In this work, the effects of these two methods on EGR characteristics were studied and simultaneously the differences between EGR and lean combustion as a dilution method were investigated. The results show that EGR limit is expanded up to 23% and 3 ~ 5% improvement in the fuel consumption are achieved around 8 ~ 13% rates by the flow controls comparing with 10% limit and 1.5% reduction around 3% rate of non-control case. The masking method is more effective on the limit expansion than throttling as like as lean misfire limit; however there is no substantial difference in fuel consumptions improvement regardless the control methods except high load condition. Also it is observed that there exist critical EGR rates around which the combustion performance and NOx formation change remarkably and these rates generally coincide with optimum rates for the fuel consumption. In addition, dilution with fresh air is much more advantageous than that of the exhaust gas from the view point of dilution limit and fuel consumption, while utilization of the exhaust gas is more effective on NOx reduction in spite of considerably small dilution compared with the use of fresh air. Finally, the improvement of fuel consumption by massive EGR is highly dependent on the EGR limit at which the engine runs stably, therefore the stratified combustion technique might be a best solution for this purpose.

• 대한기계학회논문집A
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• 제34권11호
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• pp.1675-1680
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• 2010

캐나다형 중수로에서 피더관은 가동 중에 유동 가속 부식에 의해 감육이 발생한다. 피더관에 감육이 발생하면 배관 건전성이 떨어진다. 본 논문은 원형 감육이 발생한 피더관에서의 기기신뢰성 평가를 위한 한계 하중을 연구하였다. 유한요소 해석을 통하여 면내 굽힘 하중과 내압을 받는 경우에 대하여 연구하였다. 재료는 대변형 효과를 고려하고 탄성-완전소성 재료로 가정하였다. 원형 감육이 발생한 피더관에 대하여 내압과 닫힘 방향, 열림 방향 굽힘 하중에 대하여 한계하중해를 제시하였다.

• International Journal of Control, Automation, and Systems
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• 제4권4호
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• pp.524-528
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• 2006

A controller built with the gyro effect for a balance-beam can freely control the attitude of an unstructured object by changing the position of an inner gimbal. In this paper, we propose a new balance-beam controller that can detect the inertia of the load to limit the velocity of the load commanded by a user. We found that when there was smaller load inertia, a larger restoration displacement occurred. Therefore, the load can be identified by issuing a predefined command to measure the restoration displacement, which enables us to construct a controller that can limit the angular velocity of the load by planning the motion. Experimental results show the performance of the controller with different loads.

• 대한기계학회논문집
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• 제18권12호
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• pp.3395-3403
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• 1994

The structural test technique and equipment for strength test of astronautical structures, such as rocket, were presented in this paper. Structural strength tests of the fin assembly with fin and fin frame in the scientific sound rocket were performed with load levels of 100% limit load and 150% ultimate load of design lift force. Safety factors in each part of the fin assembly were calculated at these two load levels and the stiffnesses based on the measured deflection of fin assembly and strains on fin and fin frame were evaluated at these two load level. As the result of structural test, the fin assembly was estimated to be safe.

• Computers and Concrete
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• 제6권5호
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• pp.357-376
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• 2009

In the design of concrete columns, it is important to provide some nominal flexural ductility even for structures not subjected to earthquake attack. Currently, the nominal flexural ductility is provided by imposing empirical deemed-to-satisfy rules, which limit the minimum size and maximum spacing of the confining reinforcement. However, these existing empirical rules have the major shortcoming that the actual level of flexural ductility provided is not consistent, being generally lower at higher concrete strength or higher axial load level. Hence, for high-strength concrete columns subjected to high axial loads, these existing rules are unsafe. Herein, the combined effects of concrete strength, axial load level, confining pressure and longitudinal steel ratio on the flexural ductility are evaluated using nonlinear moment-curvature analysis. Based on the numerical results, a new design method that provides a consistent level of nominal flexural ductility by imposing an upper limit to the axial load level or a lower limit to the confining pressure is developed. Lastly, two formulas and one design chart for direct evaluation of the maximum axial load level and minimum confining pressure are produced.

• Structural Engineering and Mechanics
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• 제48권6호
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• pp.879-914
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• 2013

In part I of the article, formulation and characteristics of the several well-known structural geometrical nonlinear solution techniques were studied. In the present paper, the efficiencies and capabilities of residual load minimization, normal plane, updated normal plane, cylindrical arc length, work control, residual displacement minimization, generalized displacement control and modified normal flow will be evaluated. To achieve this goal, a comprehensive comparison of these solution methods will be performed. Due to limit page of the article, only the findings of 17 numerical problems, including 2-D and 3-D trusses, 2-D and 3-D frames, and shells, will be presented. Performance of the solution strategies will be considered by doing more than 12500 nonlinear analyses, and conclusions will be drawn based on the outcomes. Most of the mentioned structures have complex nonlinear behavior, including load limit and snap-back points. In this investigation, criteria like number of diverged and complete analyses, the ability of passing load limit and snap-back points, the total number of steps and analysis iterations, the analysis running time and divergence points will be examined. Numerical properties of each problem, like, maximum allowed iteration, divergence tolerance, maximum and minimum size of the load factor, load increment changes and the target point will be selected in such a way that comparison result to be highly reliable. Following this, capabilities and deficiencies of each solution technique will be surveyed in comparison with the other ones, and superior solution schemes will be introduced.