• Journal of Korean Society of Steel Construction
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• v.8 no.4 s.29
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• pp.105-113
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• 1996

본 연구에서는 철골모멘트골조의 패널존변형을 명시적으로 고려한 탄성층 간변위의 근사해석 방법을 제안하였다. 본 방법은 고전적 포탈법의 가정 및 D 치법에 기반한 해석적 접근법이다. 즉 포탈법의 가정에 따라 횡력을 받는 골조를 보-기둥 부분 골조로 분해한 후 대표적 내부 부분골조의 보, 기둥 및 패널존에서 기인하는 모든 횡변위 성분을 해석적으로 계산한다. 이때에 필요한 모든 내력(가령 패널존 전단변형 산정을 위한 보의 불균형모멘트)의 결정에 D 치법을 이용한다. 구조바닥의 강막작용을 고려하면 위의 과정을 통하여 산출된 대표적 내부 부분골조의 횡변위는 전체 골조의 횡변위와 거의 동일할 것으로 기대할 수 있다. 본 방법의 타당성 여부는 반강절 접합요소를 사용한 해석적 엄밀해와 비교하여 검증하였으며 만족스런 결과를 주는 것을 확인하였다. 본 연구의 방법에 의해 컴퓨터해석에 의하지 않고도 철골모멘트골조의 탄성층간변위를 실용성있는 정확도로서 신속하게 산정할 수 있으므로 본 연구의 결과는 예비적 횡강성 평가에 유용하게 사용될 수 있다. 또한 본 방법의 적용과정에서 해석자는 철골모멘트골조의 횡변위 기동에 관한 물리적 감각을 증진시킬 수 있을 것으로 사료된다.

• Journal of the Earthquake Engineering Society of Korea
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• v.4 no.3
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• pp.35-44
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• 2000

전편의 실험적 연구에 이어서, 기 수행된 4개의 외부 접합부 시험체에 현존하는 여러 강도 예측식을 사용하여 콘크리트 기둥-강재 보 접합부의 내진 성능을 결정하는 패널 전단 및 지압 강도를 평가하였다. 또한, 접합부 패널지역의 변형특성을 묘사할 수 있는 일련의 스프링을 사용한 macro 형태의 해석모델이 논의되었으며, 이에 따라 Drain-2DX 및 IDARC 등의 상용프로그램을 사용하여 접합부의 패널전단 및 지압 파괴형태의 변형을 포함하는 단순해석이 수행되었다. 강도 예측결과에 의하면 본 연구에서 제시하는 수정된 내부 콘크리트 패널 전단 강도식을 포함하고 있는 ASCE 방법이 실험결과에 가장 근접한 것으로 나타났으며, 본 연구에서 검토된 패널지역 변형을 고려한 단순해석모델은 향후 전체 건물해석에 사용할수 있는 것으로 판단되었다.

• Composites Research
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• v.33 no.3
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• pp.140-146
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• 2020

The purpose of this paper is to examine the possibility of weight reduction by changing the partition panel of vehicle from an existing aluminum material to carbon fiber reinforced plastics. Three weaving methods (plain, twill and satin) were used in the manufacture of composite materials, and they were produced and tested to derive their material properties. The analysis model of composite partition panel for torsional conditions was developed and the structural stability and system stiffness were evaluated according to Tsai-Hill failure criteria. With design variables for fiber orientation angles and stacking sequence, evolutional optimal algorithm was performed and as the results, the optimal composite partition panel was designed. In addition, the structural analysis results for strength and specific stiffness were compared with aluminum partition panels and composite partition panels to verify the possibility of weight reduction.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.33 no.2
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• pp.103-111
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• 2020

Recently, the use of transfer slab system has increased greatly. However, several construction problems are being encountered owing to its excessive thickness. Therefore, in this study, a transfer slab system that uses a reverse drop panel, which can utilize the facility space of the pit floor by reducing the transfer slab thickness, was considered. To investigate the shear behavior of transfer slab system that uses the reverse drop panel, the two-way shear strength of transfer slab-column connection with the reverse drop panel was analyzed using nonlinear FE analysis. In addition, the two-way shear strength evaluations of transfer slab with the reverse drop panel conducted using the existing evaluation methods were verified by comparing the strengths predicted by those methods with the results of nonlinear FE analysis.

• Journal of the Society of Naval Architects of Korea
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• v.37 no.4
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• pp.1-10
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• 2000

A panel method based on the raised panel approach is developed for the nonlinear ship wave problem of practical hull forms. For the validation of the present numerical scheme. the developed method is first applied to Series 60 hull for which the extensive experimental data are available. As practical applications. the developed method is applied to KRISO 3600 TEU container ship and KRISO 300K VLCC. With the primary emphasis on the nonlinear effects of the global wave pattern generated by the two commercial ships. the calculated wave patterns are compared and verified with the experiments of KRISO. It is found that the calculated results of the present method are quite satisfactory compared with the linear methods like Dawson's approach and Neumann-Kelvin solution.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.15 no.2
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• pp.315-327
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• 2002

The main objective of this study is to develop an discrete optimization algorithm of plane steel frames with rigid using second-order-elastic-plastic hinge analysis which is considering panel zone. Conventional analyses of steel frame are usually tarried out without considering the effect of panel zone deformation on frame behavior The validity of this model is established by comparison without panel zone on joint models is analyzed numerically to demonstrate the importance of using realistic models in steel frame analysis. The objective function is taken as Weight of steel frames and the constraints we formulated based on AISC-LRFD(1994). The validity of the developed algorithm we demonstrate by comparing the result with those of SAP2000. The result of the study indicates that the optimal design algorithm considering of panel zone behavior more economic design than simple steel frame design methods.

• Journal of the Society of Naval Architects of Korea
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• v.39 no.1
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• pp.8-15
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• 2002

A two-dimensional higher order panel method using B-splines has been developed to overcome the disadvantages of the low order panel method and to obtain more accurate solution. The sources and the normal dipoles are distributed on both the body and the free surface. Instead of applying the upwind finite difference schemes to satisfy the linearized free surface and the radiation condition, the derivatives of the basis functions of the B-splines are directly applied to the linearized free surface condition. Numerical damping in the Dawson's method are avoided in the Present computations. In order to validate the present method, numerical computations are carried out for a submerged cylinder and a two-dimensional hydrofoil steadily moving beneath a free surface. The numerical results show that fast convergence and better accuracies have been achieved by the present method.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.12
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• pp.92-100
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• 2005

An aircraft wing or fuselage panel of skin-stringer assembly can fail in a variety of instable modes under compression loads. Instability modes can be buckling of the panel, local buckling of the stringer, flexure, torsion, wrinkle and combined flexural/torsional buckling of the panel assembly. Although researches on these buckling behaviors have been carried out for a long time, there are some difficulties to apply to the practice because of complex theoretical and empirical equations. Accordingly, It is well known that leading aerospace companies are using their own in-house programs for the convenience of practical usage, but our domestic situation is that no such program has been ever developed. In this study a comprehensive program has been developed, which can identify the instability modes and the magnitude of reserve factor of the modes for the skin/stringer panel assembly under compression load. The developed program is based on the theory manual of the Airbus program APA114. For the verification, calculation of the instable reserve factors for the A320 wing panel and A380 low wing panel sections were carried out and compared with results by APA114.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.1-8
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• 2005

Civil aviation regulation such as FAR and loads analysis procedure based on this was explained, and loads analysis procedure and results for Smart UAV was presented for application case. For loads analysis, applicable regulations and loads conditions should be prepared in advance, and modeling for aerodynamics, weight, and structure should be performed. Panel method is usually adopted for aircraft loads analysis to obtain aerodynamic loads. In this study, ARGON which is multidisciplinary fixed wing aircraft design software co-developed by KARI and TsAGI was used for loads analysis. ARGON can be utilized for flutter and stress analysis as well as for flight and ground loads analysis. In this paper, flight loads analysis of 4-seater canard airplane was performed with ARGON and that results were presented.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.7
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• pp.655-660
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• 2007

A canard-leading edge flap deflection scheduling laws have been established to enhance the maneuverability of the canard type fighter class aircraft. These scheduling laws are the relation of canard-leading edge flap deflections and flight conditions to maximize the lift-drag ratio. For these purposes, the corrected supersonic panel method has been used to predict the lift-drag characteristics due to canard-leading edge flap deflections. In addition, the high speed wind tunnel test has been conducted with 1/20 scale model to validate the predicted scheduling laws. Good agreements have been obtained compared with the results of high speed wind tunnel test. Based on the results obtained from the experimental and numerical studies, the corrected supersonic panel method has shown to be useful to establish the canard-leading edge flap deflection scheduling law for the aerodynamic design of canard type fighter class aircraft.