• Computers and Concrete
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• 제30권6호
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• pp.433-443
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• 2022

In the current paper, the nonlinear resonance response of functionally graded graphene platelet reinforced (FG-GPLRC) beams by considering different boundary conditions is investigated using the Euler-Bernoulli beam theory. Four different graphene platelets (GPLs) distributions including UD and FG-O, FG-X, and FG-A are considered and the effective material parameters are calculated by Halpin-Tsai model. The nonlinear vibration equations are derived by Euler-Lagrange principle. Then the perturbation method is used to discretize the motion equations, and the loadings and displacement are all expanded, so as to obtain the first to third order perturbation equations, and then the asymptotic solution of the equations can be obtained. Then the nonlinear amplitude-frequency response is obtained with the help of the modified Lindstedt-Poincare method (Chen and Cheung 1996). Finally, the influences of the distribution types of GPLs, total GPLs layers, GPLs weight fraction, elastic foundations and boundary conditions on the resonance problems are comprehensively studied. Results show that the distribution types of GPLs, total GPLs layers, GPLs weight fraction, elastic foundations and boundary conditions have a significant effect on the nonlinear resonance response of FG-GPLRC beams.

• Advances in materials Research
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• 제11권3호
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• pp.171-190
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• 2022

In this paper, the problem of interfacial stresses in steel cantilever beams strengthened with bonded composite laminates is analyzed using linear elastic theory. The analysis is based on the deformation compatibility approach, where both the shear and normal stresses are assumed to be invariant across the adhesive layer thickness. The original study in this paper carried out an analytical solution to estimate shear and peel-off stresses, as, interfacial stress analysis concentration under the uniformly distributed load and shear lag deformation. The theoretical prediction is compared with authors solutions from numerous researches. This phenomenon of deformation of the members, which gives probably approach on the study of interface of the reinforced structures, is called "shear lag effect". The resolution in this paper shows that the shear stress and the normal stress are significant and, are concentrated at the end of the composite plate of reinforcement, called "edge effect". A parametric study is carried out to show the effects of the variables of design and the physical properties of materials. This research is helpful for the understanding on mechanical behaviour of the interface and design of such structures.

• Advances in aircraft and spacecraft science
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• 제9권5호
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• pp.377-400
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• 2022

The aim of this work is a numerical comparison (FEM) between lattice pyramidal-core panel and honeycomb core panel for different core thicknesses. By evaluating the mid-span deflection, the shear rigidity and the shear modulus for both core types and different core thicknesses, it is possible to define which core type has got the best mechanical behaviour for each thickness and the evolution of that behaviour as far as the thickness increases. Since a specific base geometry has been used for the lattice pyramidal core, the comparison gives us the opportunity to investigate the unit cell strut angle giving the higher mechanical properties. The presented work considers a detailed FEM modelling of a standard 3-point bending test (ASTM C393/C393M Standard Practice). Detailed FEM modelling addresses to detailed discretization of cores by means of beam elements for lattice core and shell elements for honeycomb core. Facings, instead, have been modelled by using shell elements for both sandwich panels. On lattice core structure, elements of core and facings are directly connected, to better simulate the additive manufacturing process. Otherwise, an MPC-based constraint between facings and core has been used for honeycomb core structure. Both sandwich panels are entirely built of Aluminium alloy. Prior to compare the two models, the FEM sandwich panel model with lattice pyramidal core needs to be validated with 3-point bending test experimental results, in order to ensure a good reliability of the FEM approach and of the comparison. Furthermore, the analytical validation has been performed according to Allen's theory. The FEM analysis is linear static with an increasing midspan load ranging from 50N up to 500N.

• Advances in concrete construction
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• 제15권4호
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• pp.215-228
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• 2023

The vibrational behavior of nanoelements is critical in determining how a nanostructure behaves. However, combining vibrational analysis with stability analysis allows for a more comprehensive knowledge of a structure's behavior. As a result, the goal of this research is to characterize the behavior of nonlocal nanocyndrical beams with uniform and nonuniform cross sections. The nonuniformity of the beams is determined by three distinct section functions, namely linear, convex, and exponential functions, with the length and mass of the beams being identical. For completely clamped, fully pinned, and cantilever boundary conditions, Eringen's nonlocal theory is combined with the Timoshenko beam model. The extended differential quadrature technique was used to solve the governing equations in this research. In contrast to the other boundary conditions, the findings of this research reveal that the nonlocal impact has the opposite effect on the frequency of the uniform cantilever nanobeam. Furthermore, since the mass of the materials employed in these nanobeams is designed to remain the same, the findings may be utilized to help improve the frequency and buckling stress of a resonator without requiring additional material, which is a cost-effective benefit.

• 한국항해항만학회지
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• 제37권5호
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• pp.481-486
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• 2013

본 연구에서는 18미터급 쌍동형 선형의 선수벌브 유무에 따른 운동응답특성을 선형 스트립이론에 기초한 상용코드(Seakeeper)를 이용하여 추정하였다. 계산조건으로는 ITTC 파스펙트럼에 기초한 뷰포트 풍력계급 3 ($\bar{T}=2.98s$, $H_{1/3}$ =0.6m), 4 ($\bar{T}=3.85s$, $H_{1/3}$ =1m) 및 5 ($\bar{T}=5.44$, $H_{1/3}$ =2m)의 파스펙트럼을 산출하였고, 조우각은 선수파, 선수사파 및 횡파를 적용하여 종동요의 선체운동응답스펙트럼을 해석하였다. 선수벌브가 적용된 쌍동선 선형은 선수파와 선수사파에서 최대 20%의 종동요 응답이 감소하는 효과를 나타냈다.

• 대한기계학회논문집
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• 제17권6호
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• pp.1381-1388
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• 1993

본 연구에서는 구조계와 제어계가 결합된계에 대하여, 성능 평가함수의 구조 설계변수에 대한 감도를 Riccati방정식으로부터 직접 해석할 수 있는 효율적인 방안을 제시하여 동시최적설계가 가능토록한다. 그리고 유색잡음의 불규칙 노면입력을 받는 차체탄성을 고려한 Hac의 2륜 차량의 모델에 LQG제어를 행한 경우에 대하여, 본 연구 방법을 적용시켜 동시 최적화를 수행한 제어성능 특성을 종래의 최적제어만에 의한 제어성능과 비교, 검토 한다. 구조설계변수로는 현가장치의 강성특성, 감쇠특성 및 현가장치 지지점의 위치로 선정한다.

• 대한조선학회논문집
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• 제39권3호
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• pp.64-74
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• 2002

선체 휘핑 해석 전용 프로그램은 모멘텀 슬래밍 이론을 사용하여 비선형 유체충격력을 추정하였으며, Timoshenko 보이론에 기초하여 선체 hull girder를 탄성체로 모델링하고 있다. 개발된 프로그램에 대하여 슬래밍 충격력의 효과, 유탄성해석의 효과 그리고, 선속, 파고, 파장 등 각종 설계 변수가 미치는 효과 등에 관한 검증 계산을 수행하였고, 실제 선박 설계에의 적용 예를 보임으로써 본 프로그램의 설계 활용성을 확인하였다. 본 프로그램은 각종 입출력자료의 GUI 처리 및 선박 운동에 대한 시뮬레이션 제공 등 다양한 기능과 특성을 가지고 있다.

• 한국항공우주학회지
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• 제39권4호
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• pp.297-305
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• 2011

본 논문에서는 비정상 공기력을 모델링하기위해 Peters-He의 동적유입류모델을 고려한 2차원 준정상 공기력 이론을 적용하여 회전익기 전진비행에 대한 공탄성 해석을 수행하였다. 또한, 공력탄성학적 안정성 해석을 수행하기 위하여, 전진비행 시 주기적인 특성을 갖는 비선형 정적 트림 해를 얻기 위해 동체 평형을 고려한 연계 트림 해석을 통한 완전 유한요소 방정식을 이용하였다. 동적유입류모델의 공력과 구조 특성을 검증하기 위해 유도 유입류와 깃끝에서의 구조변형을 타 수치해석결과와 비교하였다. 또한, 공탄성 안정성을 검증하기 위해 두 모델의 래그 감쇠값을 비교하였다.

• 콘크리트학회논문집
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• 제18권6호
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• pp.819-825
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• 2006

본 연구의 목적은 휨과 전단에 지배받는 철근콘크리트 보에서 아치작용에 의한 전단기여성분을 평가하기 위한 새로운 해석 모델의 적용성을 검증하기 위한 것이다. 새로운 모델은 전단력은 휨모멘트의 변화율이라는 관계식을 기초로, 분산트러스 이상화 기법을 이용하여 횡단면에서 베르누이(Bernoulli) 휨 평면으로부터 전단변형적합조건을 새롭게 유도하였으며, MCFT와 분산트러스 이상화를 통해 전단흐름에 의한 복부전단요소의 전단곡률을 일치시키는 전단변형적합조건을 수립하였다. 전단변형적합조건을 이용하면, 보 전단거동은 타이드아치작용과 보작용의 두 성분으로 수치적 분해 될 수 있다. 이러한 분리 접근법의 유효성은 기존 문헌에 수록된 활용 가능한 실험 자료를 통해 검증하였다. 수행 결과 실제 측정 전단강도와 비교하였을 때 복부가 분담하는 전단강도는 훨씬 일정하며, 역학적 복부철근비와 훌륭한 선형 상관관계에 있는 것으로 나타났다. 새로운 해석 모델은 철근콘크리트 부재의 전단 거동에 영향을 미치는 각 변수나 메커니즘을 합리적으로 설명할 수 있는 모델이라고 할 수 있겠다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2007년도 춘계학술대회논문집
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• pp.859-865
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• 2007

This paper presents a method to analyze the unbalance response of a high speed polygon mirror scanner motor supported by sintered bearing and flexible supporting structures by using the finite element method and the mode superposition method. The appropriate finite element equations for polygon mirror are described by rotating annular sector element using Kirchhoff plate theory and von Karman non-linear strain, and its rigid body motion is also considered. The rotating components except for the polygon mirror are modeled by Timoshenko beam element including the gyroscopic effect. The flexible supporting structures are modeled by using a 4-node tetrahedron element and 4-node shell element with rotational degrees of freedom. Finite element equations of each component of the polygon mirror scanner motor and the flexible supporting structures are consistently derived by satisfying the geometric compatibility in the internal boundary between each component. The rigid link constraints are also imposed at the interface area between sleeve and sintered bearing to describe the physical motion at this interface. A global matrix equation obtained by assembling the finite element equations of each substructure is transformed to a state-space matrix-vector equation, and both damped natural frequencies and modal damping ratios are calculated by solving the associated eigenvalue problem by using the restarted Arnoldi iteration method. Unbalance responses in time and frequency domain are performed by superposing the eigenvalues and eigenvectors from the free vibration analysis. The validity of the proposed method is verified by comparing the simulated unbalance response with the experimental results. This research also shows that the flexibility of supporting structures plays an important role in determining the unbalance response of the polygon mirror scanner motor.