• Structural Engineering and Mechanics
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• 제83권2호
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• pp.273-282
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• 2022

In this paper, we propose a new concept for error estimation in finite element solutions, which we call mode-based error estimation. The proposed error estimation predicts a posteriori error calculated by the difference between the direct finite element (FE) approximation and the recovered FE approximation. The mode-based FE formulation for the recently developed self-updated finite element is employed to calculate the recovered solution. The formulation is constructed by searching for optimal bending directions for each element, and deep learning is adopted to help find the optimal bending directions. Through various numerical examples using four-node quadrilateral finite elements, we demonstrate the improved predictive capability of the proposed error estimator compared with other competitive methods.

• 대한기계학회논문집
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• 제13권5호
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• pp.820-830
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• 1989

본 논문에서는 타이어의 각 부분의 물성치 계산을 위한 식을 유한요소법에 적용할 수 있도록 제안하였다. 이 식은 강철 코드의 굽힙효과를 고려 하였으며, 특히 각 요소에서 전단변형이 일어나는 동안의 굽힘효과를 고려하였다. 유한요소 공식화는 가상일의 원리에 의하여 평형 방정식으로부터 유도하였고, Updated refer- ence coordinate에 대해 증분해석을 적용하여 Updated Lagrangian공식화를 하였다. 그리고 차량하중에 의하여 타이어가 노면에 접지될때의 응력상태를 게산할 수 있도록 접촉문제 공식화를 유한요소 공식화에 첨가 하였다.

• 한국소음진동공학회논문집
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• 제22권5호
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• pp.480-488
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• 2012

The aircrafts with high aspect ratio wings made by a composite material have been developed, which enable high energy efficiency and long-term flight by reducing air resistance and structural weight. However, they have difficulties in securing the aeroelastic stability such as the flutter because of their long and flexible wings. The flutter is unstable self-excited-vibration caused by interaction between the structural dynamics and the aerodynamics. It should be verified analytically prior to first flight test that the flutter does not happen in the range of flight mission. Normally, the finite element model is used for the flutter analysis. So it is important to construct the finite element model representing dynamic characteristics similar to those of a real aircraft. Accordingly, in this research, to acquire dynamic characteristics experimentally the modal test of the aircraft with high aspect ratio composite wings was conducted. And then the modal parameters from the finite element analysis(FEA) were compared with those from the modal test. To make analysis results closer to test results, the finite element model was updated by means of the sensitivity analysis on variables and the optimization. Finally, it was proved that the updated finite element model is reliable as compared with the results of the modal test.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 추계학술대회논문집A
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• pp.486-491
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• 2000

In this study, finite elements addition and removal method by stress range is applied to optimize shapes in structures, without using classical and numerical optimization methods and search methods. The program based on this algorithm is developed and compared to theoritial results with considerable accuracy. Classical methods need mesh generation for finite element analysis for every iteration, the developed method needs updated mesh data such as coordinates of nodes, elements connectivity, and loads on nodes. And other tools of finite element analysis can be in use as a black box to interface with this program.