• Proceedings of the Computational Structural Engineering Institute Conference
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• 2009.04a
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• pp.30-33
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• 2009

본 논문에서는 형상기억합금의 특징적인 거동을 모사하기위한 구성방정식을 제안한다. 제안되는 구성방정식은 기존의 소성모델을 기초로 하는 현상학적인 모델로, 소성 경화이론에서 사용되는 항복곡면에 대응되는 상변이 곡면을 정의하여 형상기억합금의 비선형 거동을 모사한다. 단, 상변이 곡면이 1개만 존재하는 소성모델과는 다르게, 오스테나이트에서 마르텐사이트로의 정방향 상변이와 마르텐사이트에서 오스테나이트로의 역방향 상변이를 각각 해석하기위해 독립적인 2개의 상변이 곡면을 정의해주게 된다. 기계적 하중만이 아닌 열적 하중의 변화에도 비선형 거동을 보이는 형상기억합금의 특성을 반영하기위해 상변이 곡면은 응력과 온도의 함수로 정의되며, 이렇게 정의된 상변이 곡면을 바탕으로 리턴 매핑 알고리즘을 적용하여 열적하중과 기계적하중의 변화에 따른 형상기억합금의 거동을 모사하는 구성방정식을 제안하였다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1997.10a
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• pp.596-599
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• 1997

In this study, the flow control system with shape memory alloy in jet engine inlet was suggested to adjust the shock boundary layer interact~on for supersonic flight system. It consisted of the flap with shape memory alloy, spar with steel, and fixing device with aluminum alloy. The advantages of itself are a simple configuration, a passive air circulation by using the flap deflection due to pressure difference, and no need to be required the auxiliary devices. Finite element analysis was conducted to predict the thenno-mechanical behavlor of the flap system with shape memory alloy. The user-defined subroutine UMAT was implemented with ABAQUS to accon~modate the thermo-mechanical constitutive relation of shape memory alloy.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.2
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• pp.265-270
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• 1989

The present study considers the thermal structure variation in a porous medium caused by changing the most important radiative property of porous medium, absorption coefficient, as well as altering the physical dimension of porous medium and the equivalence ratio of premixed gas mixture. The radiation model was introduced as an unsteady differential form using the two-flux gray radiation model. The role of the conductive heat transfer through both gas phase and porous medium was found to be almost insignificant compared with that of the radiative heat transfer. The reaction zone shifted upstream and the flame thickness decreased as either the geometrical length of porous medium increased or the absorption coefficient decreased.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.10
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• pp.875-887
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• 2015

The optimal layout design is used in the development of various areas of industry. In the field of space systems, components must be placed properly in the limited space of spacecraft by considering mechanical, thermal and electrical interfaces. When applying optimal layout design, a proper, even ideal placement of components is possible in the limited space of a satellite platform. Through the optimal placement design, the minimized moment of inertia enhances efficient attitude control, rapid maneuver and mission performance of the satellite. This paper proposes 3D optimal layout design that minimizes the spacecraft's moment of inertia and effect of thermal dissipation between inner components as well as interference between inner components based on a cubic-structure satellite platform. This study proposes the new genetic algorithm for 3D optimal layout design of the satellite platform.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.8
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• pp.1519-1529
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• 1992

A stepped specimen which is subjected to step loading is modeled to study the initiation and growth of adiabatic shear band using explicit time integration finite element code. The material model for specimen includes effects of thermal softening, strain hardening and strain rate hardening. Various mesh sizes are tested to check whether they are small enough to model highly localized discontinuous phenomena reasonably well. It is shown that the number of adiabatic shear band depends on impact velocity and it is also shown that the initiation and growth of adiabatic shear band inversely depends on prescribed velocity at the top of specimen.

• Composites Research
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• v.16 no.3
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• pp.1-8
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• 2003

Densification occurs by the inelastic flow of the matrix materials during the consolidation processes at high temperature for MMCs, and the results depend on many process conditions such as applied pressure, temperature and volume fraction of fiber and matrix materials. This is particularly important in titanium matrix composites since material failure may occur by either the applied conditions or microstructural parameters through the processes, and thus a generic model based on micro-mechanical approaches enabling the evolution of density over time to be predicted has been developed. The mode developed is then implemented into FEM so that practical process simulation has been carried out. Further the experimental investigation of the consolidation behavior of SiC/Ti-6Al-4V composites using vacuum hot pressing has been performed, and the results obtained are compared with the model predictions.