• Journal of Korean Society of Steel Construction
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• v.16 no.4 s.71
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• pp.479-492
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• 2004

When U-ribs of steel deck plates are connected at the field, overhead welding should be done with backing strips. Misalignments may occur and lead to eccentric moments as well as high stress concentrations at welded joints. In this study, stress analyses and fatigue tests were carried out. Stress analyses for U-ribs' welded joints with backing strips were performed with different misalignments, root shapes, root gaps, and backing strip sizes. From the stress analyses, the stress concentration factors increased with increasing misalignments and root gaps. With the fixed misalignments and root gaps, the stress concentration factors obtained in the case of the semi-circle root shape were lower than those in the case of the right-angle root shape. It was verified that backing strip sizes have little influence on stress concentration factors. The fatigue tests for U-ribs' welded joints with backing strips indicated that increased misalignments shorten fatigue life drastically and cracks usually initiate at the root of the base metal and are propagated to the weld bead surface. Based on the results of the stress analyses, root-shape control methods were developed to mitigate stress concentration by changing welding condition control, radius curvature, and flank angle.

• Composites Research
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• v.37 no.4
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• pp.310-315
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• 2024

An auxetic structure with negative Poisson's ratio exhibits distinctive mechanical properties in contrast to conventional structures, garnering interest in various fields. However, current research has predominantly focused on the design and optimization of auxetic structures, with limited exploration of their practical applications. In this study, we utilized 3D printing technology to fabricate a soft auxetic structure with triangular shaped perforations, examining the mechanical properties based on geometric structure. Additionally, by inserting shape memory alloys into the fabricated soft auxetic structure, we achieved active two-dimensional deformations and confirmed its selective object permeability. This technology holds the potential to have far-reaching implications across a broad spectrum of industries.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.14-15
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• 2002

기체역학 이론에 의하면, 노즐의 공급압력과 노즐의 상세형상이 주어지는 경우에 추진 노즐로부터 방출되는 제트유동의 추력을 예측할 수 있으며, 최대추력은 노즐 출구에서 유동이 적정팽창 상태로 될 때 얻어진다. 실제의 추진 로켓에서나 다른 비상체에서는 추력의 예측뿐만 아니라, 얻어지는 추력의 방향을 적절하게 조절하여 제어하는 것이 요구된다. 종래 추력벡터 제어를 위해서 많은 연구들이 수행되었다. 일례로 추진노즐 내부에 베인(vane) 등을 삽입하여, 추력벡터를 조절하거나, 추진 노즐을 가변(movable nozzle)으로 하는 방법, 그리고 노즐내부에 2차 유동을 분사(secondary flow injection)하여 평균 추력벡터를 제어하는 방법 등이 제안되어 응용되어 왔다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1996.11a
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• pp.683-689
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• 1996

5축 가공기는 가공중의 공구자세 변화를 요구하는 복잡한 산업형상의 가공, 혹은 경사 가공을 통한 표면조도 향상등의 목적으로 채용되는 첨예의 공작기계로서 이를 지원하는 CAM연구가 활발히 이루어지고 있다. 그러나, 산업현장에서 흔히 5축 가공기로 일컬어지는 상당수의 5축 가공기는 기구축은 5축을 가지나, 동기제어 축수는 3측인 “선택적 3/5축 가공기”의 형태로서 진정한 의미의 5축가공기와는 근본적으로 다르다. 5축 동기제어를 지원하는 CAM연구는 부분적으로 연구 개발된 상태이나, 선택적 3/5축을 지원하는 CAM 이론은 연구된 바 없으며, 이에 따라 현장에서는 공작물의 셋업을 변경시키는 소위 자동 인덱싱 방식으로 활용하고 있는 실정이다. 본 연구팀에서는 선택적 3/5축 가공기에서 5축 가공을 실현할 수 있는 공구경로 산출 및 제어알고리즘을 개발하고 있으며, 본 논문에서는 (5축 가공 대비) 선택적 3/5축 가공문제의 이론적 특성과 경사가공을 수행하기 위한 알고리즘을 소개하고 시뮬레이션을 통하여 유효성을 보인다.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.28 no.1
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• pp.47-51
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• 2015

In this paper, feasibility of dynamic characteristics recovery of delaminated composite structure is numerically studied by using active control algorithm and piezoelectric actuator. Macro-fiber composite(MFC), which has great flexibility and high actuating force, is considered as an actuator in this work. After construction of finite element model for delaminated composite structure based on improved layerwise theory, modal characteristics are investigated and changes of natural frequencies and mode shapes, caused by delamination, are observed. Then, active control algorithm is realized and implemented to system model and control performances are numerically evaluated. Dynamic characteristics of delaminated composite structure are effectively recovered to those of healthy composite structure.

• Journal of Institute of Control, Robotics and Systems
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• v.10 no.2
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• pp.112-124
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• 2004

A neural network based adaptive reconfigurable flight controller is presented for a class of discrete-time nonlinear flight systems in the presence of variations of aerodynamic coefficients and control effectiveness decrease caused by control surface damage. The proposed adaptive nonlinear controller is developed making use of the backstepping technique for the angle of attack, sideslip angle, and bank angle command following without two time separation assumption. Feedforward multilayer neural networks are implemented to guarantee reconfigurability for control surface damage as well as robustness to the aerodynamic uncertainties. The main feature of the proposed controller is that the adaptive controller is developed under the assumption that all of the nonlinear functions of the discrete-time flight system are not known accurately, whereas most previous works on flight system applications even in continuous time assume that only the nonlinear functions of fast dynamics are unknown. Neural networks learn through the recursive weight update rules that are derived from the discrete-time version of Lyapunov control theory. The boundness of the error states and neural networks weight estimation errors is also investigated by the discrete-time Lyapunov derivatives analysis. To show the effectiveness of the proposed control law, the approach is i]lustrated by applying to the nonlinear dynamic model of the high performance aircraft.

• Journal of Institute of Control, Robotics and Systems
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• v.9 no.4
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• pp.329-339
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• 2003

A neural network based adaptive controller design method is proposed for reconfigurable flight control systems in the presence of variations in aerodynamic coefficients or control effectiveness decrease caused by control surface damage. The neural network based adaptive nonlinear controller is developed by making use of the backstepping technique for command following of the angle of attack, sideslip angle, and bank angle. On-line teaming neural networks are implemented to guarantee reconfigurability and robustness to the uncertainties caused by aerodynamic coefficients variations. The main feature of the proposed controller is that the adaptive controller is designed with assumption that not any of the nonlinear functions of the system is known accurately, whereas most of the previous works assume that only some of the nonlinear functions are unknown. Neural networks loam through the weight update rules that are derived from the Lyapunov control theory. The closed-loop stability of the error states is also investigated according to the Lyapunov theory. A nonlinear dynamic model of an F-16 aircraft is used to demonstrate the effectiveness of the proposed control law.

• Journal of Korean Society of Steel Construction
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• v.15 no.2
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• pp.175-185
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• 2003

The extended tangent stiffness matrices and force-deformation relations of the elastic catenary element were initially derived through the addition of the unstrained length of cables to unknown nodal displacements. A beam-column element was then introduced to model the deck and pylon of cable-stayed bridges. The conventional geometric nonlinear analysis, initial force method, and TCUD method were summarized, with an effective method combining two methods presented to determine the initial shapes of cable-stayed bridges with dead loads. In this combined method, TCUD method was applied to eliminate vertical and horizontal displacements at cable-supported points of decks and on top of pylons, respectively. The initial force method was also adopted to eliminate horizontal and vertical displacements of decks and pylons, Finally, the accuracy and validity of the proposed combined method were demonstrated through numerical examples.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1993.10a
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• pp.171-176
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• 1993

초정밀 공작기계의 구조물은 Sub-micron의 운동정밀도를 갖추어야 초정밀기계로서의 기능이 유지된다. 특히 가공기의 베드구조물은 구동요소간의 상대 위치를 정.동적으로 규정 해주는 중요한 기본구조물이므로 고강성, 고쇠감성,열안정성, 경년변화에 대한 치수의 안정성등의 성능이 요구되며, 이를위해 공간적인 형상 설계 및 구조재의 선정에 고도의 기술이 필요하다. 따라서 본 연구는 낮은 고유진동수의 특성을 갖으면서 하중의 설치높이의 변화에서도 고유진동수가 일정히 유지되고 또한 구조물의 중심변화에 대한 수평조절이 가능하면서 자동제어가 가능한 공기스프링을 초정밀 가공기의 방진시스템으로 활용방안에 대하여 연구하였다.

• Journal of Korean Association for Spatial Structures
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• v.11 no.2
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• pp.119-127
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• 2011

The purpose of this study is to propose damper system which is easy to design, which can ensure against risks, and to verify earthquake response characteristics. For this study, the pseudo dynamic earthquake response tests carried out for steel frames with metallic damper. As a result, in case of using the metallic damper as a vibration control device proposed by this study, the damper having higher stiffness than main-structure turned to the state of plasticity by little displacement has been proved to be able to absorb earthquake energy.