• 대한기계학회논문집B
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• 제26권8호
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• pp.1153-1163
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• 2002

A transient analysis on temperatures of fuel and oil in hydraulic and lubrication systems in an aircraft was studied using the finite difference method. Numerical calculation was performed by an explicit method with modified Dufort-Frankel scheme. Among various missions, air superiority mission was considered as a mission model with 20% hot day ambient condition in subsonic region. The ambience of the aircraft was assumed as turbulent flow. Convective heat transfer coefficient were used in calculating heat transfer between the aircraft surface and the ambience. For an aircraft on the ground, an empirical equation represented as a function of free-stream air velocity was used. And the heat transfer coefficient for flat plate turbulent flow suggested by Eckert was employed for in-flight phases. The governing equations used in this analysis are the mass and energy conservation equations on fuel and oils. Here, analysis of fuel and oil temperature in the engine was not carried out. As a result of this analysis, the ground operation phase has shown the highest temperature and the largest rate of temperature increase among overall mission phases. Also, it is shown that fuel flow rate through fuel/oil heat exchanger plays an important role in temperature change of fuel and oil. This analysis could be an important part of studies to ensure thermal stability of the aircraft and can be applicable to thermal design of the aircraft fuel system.

• 대한토목학회논문집
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• 제13권5호
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• pp.99-107
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• 1993

본 논문에서는 콘크리트 균열 사이의 인장강성 효과를 고려한 임의의 기하하적 형상을 갖는 철근 콘크리트 쉘을 해석하기 위하여 재료비선형 유한요소 프로그램을 작성하였다. 본 논문은 연속적인 컴퓨터 해석으로 탄성, 비탄성 및 극한 범위에서의 철근과 콘크리트의 응력은 물론, 하중-변위 응답과 균열전파를 추적할 수 있었다. 골재억물림과 철근의 다울작용을 포함하는 유효전단계수를 평가하기 위하여 균열상태의 전단유지계수를 도입하였다. 콘크리트는 인장에서는 취성으로 압축에서는 탄소성으로 가정하였다. 콘크리트의 소성거동은 Drucker-Prager 항복기준과 결합유동법칙에 따르는 것으로 가정하였다. 철근은 Von Mises 항복기준으로 가정하였으며 등가의 두께를 가지는 철근층으로 모델화 하였다. 수치해석을 위하여는 증분형접선강성도 방법을 사용하였다. 수치예제를 제시하여 본 연구결과를 Hedgren의 실험 결과와 Lin의 수치해석과 비교하였다.

• 대한기계학회논문집B
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• 제20권12호
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• pp.4013-4026
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• 1996

A numerical simulation has been carried out for the jet impinging on a flat plate and a semi-circular concave surface. In this computation finite volume method was employed to solve the full Navier-Stokes equation based on a non-orthogonal coordinate with non staggered variable arrangement. The standard k-.epsilon. turbulent model and low Reynolds number k-.epsilon. model(Launder-Sharmar model) with Yap's correction were adapted. The accuracy of the numerical calculations were compared with various experimental data reported in the literature and showed good predictions of centerline velocity decay, wall pressure distribution and skin friction. For the jet impingement on a semi-circular concave surface, potential core length was calculated for two different nozzle(round edged nozzle and rectangular edged nozzle) to consider effects of the nozzle shape. The result showed that round edged nozzle had longer potential core length than rectangular edged nozzle for the same condition. Heat transfer rate along the concave surface with constant heat flux was calculated for various nozzle exit to surface distance(H/B) in the condition of same jet velocity. The maximum local Nusselt number at the stagnation point occurred at H/B = 8 where the centerline turbulent intensity had maximum value. The predicted Nusselt number showed good agreement with the experimental data at the stagnation point. However heat transfer predictions along the downstream were underestimated. This results suggest that the improved turbulence modeling is required.

• Advances in aircraft and spacecraft science
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• 제1권2호
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• pp.233-251
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• 2014

Each aircraft have to be certified for a specified level of impact energy, for assuring the capability of a safe flight and landing after the impact against a bird at cruise speed. The aim of this research work was to define a scientific and methodological approach to the study of the birdstrike phenomenon against several windshield geometries. A series of numerical simulations have been performed using the explicit finite element solver code LS-Dyna, in order to estimate the windshield-surround structure capability to absorb the bird impact energy, safely and efficiently, according to EASA Certification Specifications 25.631 (2011). The research considers the results obtained about a parametric numerical analysis of a simplified, but realistic, square flat windshield model, as reported in the last work (Grimaldi et al. 2013), where this model was subjected to the impact of a 1.8 kg bird model at 155 m/s to estimate the sensitivity of the target geometry, the impact angle, and the plate curvature on the impact response of the windshield structure. Then on the basis of these results in this paper the topic is focused about the development of a numerical simulation on a complete aircraft windshield-surround model with an innovative configuration. Both simulations have used a FE-SPH coupled approach for the fluid-structure interaction. The main achievement of this research has been the collection of analysis and results obtained on both simplified realistic and complete model analysis, addressed to approach with gained confidence the birdstrike problem. Guidelines for setting up a certification test, together with a design proposal for a test article are an important result of such simulations.

• 한국구조물진단유지관리공학회 논문집
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• 제18권3호
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• pp.10-19
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• 2014

파형강판은 제형, 정현형 등의 형상으로 얇은 강판을 주름지게 가공한 것으로 두꺼운 평판을 대신하여 사용하여도 높은 면외방향의 강성을 확보할 수 있다. 또한, 아코디언효과로 축방향 강성이 거의 없어 플레이트거더의 웨브에 적용할 경우 웨브가 전단력만을 부담하는 방법으로 쉽게 설계할 수 있다. 그러나 파형강판의 전단좌굴은 평판과는 달리 국부좌굴과 전체좌굴 외에도 이들의 연성에 의해서도 좌굴이 발생하는 매우 복잡한 특성이 있으며, 이러한 연성좌굴에 대한 원인과 특성의 규명은 정현형의 경우 제형보다 연구결과가 부족한 실정이다. 따라서 본 연구에서는 정현형 파형강판의 전단좌굴 특성과 연성좌굴이 발생하는 경향에 대해서 연구하였다. 전단좌굴강도를 계산하기 위해서는 유한요소프로그램을 이용하였고 해석결과를 정해와 비교하였다. 또한, 주름의 두께와 형상 파라메타에 따른 좌굴응력 변화의 특성과 좌굴모드형상의 변화를 분석하였으며, 이들의 결과를 이론식의 결과와 비교하여 좌굴양상의 변화시점에 대해서 분석하였다.

• 대한조선학회논문집
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• 제51권5호
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• pp.380-387
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• 2014

Piper Alpha disaster drew attention to the damage likely to arise from explosions and fires on an offshore platform. And great concerns have been increased to prevent these hazards. Blast wall is one of the passive safety systems; it plays a key part of minimizing the consequences. However, a buckling due to explosion loads is a factor which can reduce the strength of blast wall. The buckling often occurs between web and flange at the center of blast wall. This study aims to find a solution for reinforcing its strength by installing a flat plate at the spot where the buckling occurs. First of all, ANSYS finite element method is adopted to numerically compute the structural resistance characteristic of blast wall by using a quasi-static approach. Sequentially, the impact response characteristics of blast wall are investigated the effect on thickness of flat plate by using ANSYS/LS-DYNA. Finally, pressure-impulse diagrams (P-I diagram) are presented to permit easy assessment of structural response characteristics of stiffened blast wall. In this study, effective use is made to increase structural intensity. of blast wall and acquired important insights have been documented.

• 콘크리트학회논문집
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• 제21권3호
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• pp.347-358
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• 2009

최근에 들어서 국내에서도 무량판 구조 (flat plate slab)가 적용될 수 있는 여건이 마련되어가고 있다. 그러나 무량판 구조는 보가 없는 구조이기 때문에 일반적인 라멘구조형식에 비하여 처짐 제어가 어려우며, 포스트텐션 (post-tension) 공법은 이러한 문제점을 극복하기 위한 매우 효율적인 방법이다. 포스트텐션 구조를 적용하면 슬래브 두께의 증가 없이도 효율적으로 슬래브의 처짐을 제어 할 수 있다. 그러나, 이러한 장점에도 불구하고, 국내에서 포스트-텐션의 적용은 비용증가, 기술적인 문제, 경험부족 등으로 인하여 그 적용이 매우 제한적이다. 따라서 전구간 포스트텐션 (full-PT)에 대한 부담을 줄이고 나아가 기존 포스트텐션 구조형식의 시공성을 향상하기 위하여 본 연구에서는 슬래브 내부에서 긴장작업을 수행할 수 있는 상향긴장식 부분PT공법을 제안하였다. 이러한 상향긴장방식은 정착구를 필요에 따라 다양한 위치에 설치할 수 있기 때문에 처짐 효율에 대한 분석이 필요하며, 정착구 후면에서 인장응력을 야기시키는 문제점이 있다. 따라서, 본 연구에서는 상향긴장식 부분PT공법 적용할 때 정착구 위치에 따른 처짐효율분석, 유한요소해석 및 스트럿-타이를 이용한 인장응력 또는 인장력 해석 등을 실시하였으며, 상향긴장식 부분PT공법을 실제로 현장에 적용하고, 계측결과를 해석결과와 비교 분석함으로써 현장적용성을 알아보았다. 상향긴장식 부분PT공법은 처짐 또는 인장응력이 크게 발생되는 부분 구간에만 선택적으로 적용하면 적은 비용증가로 큰 처짐효율을 얻어낼 수 있음을 확인하였다.

• 대한조선학회논문집
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• 제48권6호
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• pp.528-538
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• 2011

As a forming method for curved hull plates more efficient than the flame bending, mechanical bending using multi point press forming and die-less forming is discussed in this paper. the mechanical forming is a flexible manufacturing system for automatically forming of hull parts. It is especially suited to varied curved parts. This paper discusses a multiple point pressing machine composed of a pair of reconfigurable punches in order to achieve the rapid forming of curved hull plates using division forming and presents how forming information is obtained from the given design surface. Although the mechanical forming can be efficient in the metal forming, spring back after pressing is a phenomenon which must be carefully considered when quantifying the process variables. If the spring back is not accurately controlled, the fabricated shell plate cannot meet assembly tolerance. This paper describes the principles to calculate the proper stroke of each punch at the divided areas. the strokes are determined by an iterative process of sequential pressing and spring back compensation from an unfolded flat shape to its given design surface. FEA(finite element analysis) is used to simulate the spring back of the plate and the IDA(iterative displacement adjustment) method adjusts the offset of pressing punches from the deformation results and the design surface. The shape deviations of two surfaces due to spring back are compensated by integrated system using FEA and IDA method. For the practical application, It is aimed to develop an integrated system that can automatically perform the compensation process and calculate strokes of punches of the double sides' reconfigurable multiple-press machine and some experimental results obtained with mechanical bending are presented.

• 대한기계학회논문집B
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• 제21권9호
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• pp.1149-1164
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• 1997

In this study, the applicability of the RNG k-.epsilon. model to the analysis of the complex flows is studied. The governing equations based on a non-orthogonal coordinate formulation with Cartesian velocity components are used and discretized by the finite volume method with non-staggered variable arrangements. The predicted results using the RNG k-.epsilon. model of three complex flows, i.e., the flow over a backward-facing step and a blunt flat plate, the flow around a 2D model car are compared to these from the standard k-.epsilon. model and experimental data. That of the unsteady axisymmetric turbulent flow within a cylinder of reciprocating model engine including port/valve assembly and the spray characteristics within a chamber of direct injection model engine are compared to these from the standard k-.epsilon. model and experimental data. The results of reattachment length, separated eddy size, average surface pressure distribution using the RNG k-.epsilon. model show more reasonable trends comparing with the experimental data than those using the modified k-.epsilon. model. Although the predicted rms velocity using the modified k-.epsilon. model is lower considerably than the experimental data in incylinder flow with poppet valve, predicted axial and radial velocity distributions at the valve exit and in-cylinder region show good agreements with the experimental data. The spray tip penetration predicted using the RNG k-.epsilon. model is more close to the experimental data than that using the modified k-.epsilon. model. The application of the RNG k-.epsilon. model seems to have some potential for the simulations of the unsteady turbulent flow within a port/valve-cylinder assembly and the spray characteristics over the modified k-.epsilon. model.

• 대한기계학회논문집 C: 기술과 교육
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• 제3권3호
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• pp.183-191
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• 2015

본 논문에서는 헬리콥터 로터 시스템의 진동과 소음을 저감시키기 위해 개발이 진행 중인 능동거니플랩(AGF, Active Gurney Flap)에 대해 유한요소법을 이용하여 수행된 동특성 해석결과를 소개하였다. 거니플랩은 평판의 형태로 블레이드 하부 표면에 수직인 방향으로 전개되며, 블레이드 뒷전(T/E, Trailing Edge) 부위에 장착된다. 거니플랩 조립체는 전기모터와 L-형 링키지 및 플랩 등의 부품들로 구성되어 블레이드 내부에 장착되며, 고정프레임에서의 진동 성분들을 감소시키기 위해 3~5/rev 범위로 능동적인 제어가 필요하다. 따라서 외연적 시간적분법을 통해 로터 회전에 의한 원심력과 제어입력이 적용되고 있는 상황에서 거니플랩의 동적 응답특성을 분석하였으며, 해석 결과를 통해 거니플랩의 하향변위 요구도를 만족시킬 수 있음을 확인하였다.