• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.3
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• pp.8-14
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• 2003

A cooling performance analysis has been made in the 8-channel calorimeter based on sub-scale KSR-III engine. Three-dimensional heat transfer analysis in cooling channels has been performed using the heat flux distribution through the chamber wall predicted from axi-symmetric compressible flow inside the combustion chamber. The heat flux distribution is verified against the published literature. Presented for the development and operation of the calorimeter are the coolant pressure drop, coolant temperature rise and the maximum chamber wall temperature. Required coolant flow rate is determined for given chamber pressure. Cooling performance is also predicted for temperature dependant coolant properties.

• Tunnel and Underground Space
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• v.23 no.2
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• pp.141-149
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• 2013

The thermal analysis is carried out for a geological disposal system developed for the final disposal of a ceramic high-level waste from pyroprocessing of PWR spent fuel. The horizontal disposal tunnel type is considered with the distance of 2 m between the disposal canisters and the tunnel spacing of 25 m. The temperature distributions around the disposal canisters are calculated for the horizontal tunnel based on the conceptual design. The thermal performance analysis is carried out using a FEM program, ABAQUS. The performance analysis shows that the peak temperature in a disposal system outside the disposal canister is lower than $100^{\circ}$, which meets the thermal criterion of the disposal system. According the analysis, the peak temperature for the disposal canister located boundary of the disposal system is lower by $3^{\circ}$ than that for the canister at the central area. This implies the disposal density can be improved by locating more disposal canisters along the boundary.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.59-59
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• 2003

과학위성 1호는 고도 685 km 태양동기궤도에서 운용되는 소형인공위성으로 지구 그림자에 의한 주기적인 온도변화, 태양과 지구로부터의 자외선복사, 진공환경과 같은 가혹한 우주환경에서 정상적으로 임무를 수행해야 한다. 이러한 가혹한 우주환경에서 위성 각 시스템의 온도를 허용범위 내에서 조절하고 구조적인 열변형을 최소화하기 위하여 열제어 시스템이 필요하며, 위성개발과정에서 상세한 열설계 요구조건을 도출하고 반영하여 과학위성 1호의 열제어 시스템을 설계하였다. 열제어 시스템은 위성의 내\ulcorner외부에서 위성외부로부터의 열유입을 최소화하고 위성내부에서 발생한 열을 효과적으로 방출하는 역할을 한다. 열제어 시스템의 성능을 검증하기 위하여 다양한 임무와 궤도를 고려한 궤도열해석이 수행되었으며, 주기적인 온도변화와 진공환경을 모사하는 열진공시험을 통하여 예상되는 우주환경에서 위성 각 시스템의 정상동작 여부가 검증되었다. 본 연구는 과학위성 1호의 열설계 결과와 효과적인 열설계를 위한 궤도열해석 과정 그리고 위성 시스템의 신뢰성 검증을 위한 열진공시험결과를 다룬다.

• Journal of Aerospace System Engineering
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• v.17 no.4
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• pp.18-27
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• 2023

In this paper, the structural-thermal-optical performance analysis of the mirror was performed by setting the laser heat source as the boundary condition of the thermal analysis. For the laser heat source model, the Beer-Lambert model considering semi-transparent optical material based on Gaussian beam was selected as the boundary condition, and the mechanical part was not considered, to analyze the performance of only the mirror. As a result of the thermal analysis, thermal stress and thermal deformation data due to temperature change on the surface of the mirror were obtained. The displacement data of the surface due to thermal deformation was fitted to a Zernike polynomial to calculate the optical performance, through which the performance of the mirror when a high-energy laser was incident on the mirror could be predicted.

• Journal of Energy Engineering
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• v.9 no.4
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• pp.328-333
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• 2000

이 연구의 목적은 액정법을 이용하여 주름형상 판형 열 교환기에서의 내부유동과 열 전달 성능의 특성을 파악하는데 있으며 공기를 작동유체로 사용하였다. 과거에는 실험이 주로 판형 열 교환기의 입·출구에서의 열 전달 성능에만 관심이 집중되었다. 그러나 이 실험에서는 액정법을 이용하여 판형열교환기 셀 표면 위에서의 국소 누셀트수의 분포를 연구하였다. 레이놀즈수가 증가할수록 열 전달 성능은 증가하였으나 마찰계수는 감소하였다. 주름각이 증가할수록 열 전달 성능과 마찰계수는 모두 증가하였다. 국소 누셀트수 분포로부터 열 전달이 잘 일어나는 부분은 주름을 타고 넘어 들어온 두 유동이 만나는 곳이며 또한, 셀의 가운데 부분은 셀의 수직단면적이 커서 셀 표면과 유동의 접촉이 약하므로 작은 누셀트수를 가지는 것을 알 수 있다.

• Journal of Korean Society of Steel Construction
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• v.27 no.4
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• pp.387-397
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• 2015

The domestic fire resistance performance test is conducted as a prescriptive design method such as quality test. In quality test there are 2 methods, unloaded fire resistance test and fire resistance test under load. In realistic, these tests, however, have problems with expense, time and diversity of structure. This study reviewed fire resistance performance of H-beam flexural member by thermal stress analysis using finite element ABAQUS program. This research is for the performance-based design reviewing applicability of domestic standard. As a result of this study, limit temperatures per each load ratio provied for proper performance of fire resistancy.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.76-82
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• 2003

To guarantee the proper functions of a satellite in the extreme space environment, the several test models are developed generally. There are advantages that the design and the analysis of Flight Model(FM) can be validated through these test models, and the functional reliabilities can be increased by reflecting the modifications on the final design of FM. The integration and test of Structure & Thermal Model(STM) of KOMPSAT, being currently developed, have been completed. In this paper, the processes of design and analysis of the STM propulsion system, one of the KOMPSAT modules, are described.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.1008-1015
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• 2015

Thermal vacuum test should be performed prior to launch to verify satellites' functionality in extremely cold/hot temperatures and vacuum conditions. A thermal vacuum chamber used to perform the thermal vacuum tests of a satellite system and its components. A cryogenic blower is a core component of the gaseous nitrogen (GN2) closed loop thermal control system for thermal vacuum chambers. A final goal of this research is development of cryogenic blower. Design requirements of a blower are 150 CFM flow rate, 0.5 bara pressure difference, hot and cold temperatures. This paper describes the performance analysis of impeller by 1D, CFD commercial software, the design of the thermal protection interface between the driving part and the fluid part. The performance of the cryogenic blower is confirmed by test at the standard air condition and is verified by on the thermal vacuum chamber at the real operating condition.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1222-1228
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• 2008

A small satellite, DubaiSat-1 FM(Flight Model), which is based on SI-200 standard bus platform and scheduled to be launched in 2008, is being developed by Satrec Initiative and EIAST(Emirates Institution for Advanced Science and Technology). The TCS(Thermal Control Subsystem) of DubaiSat-1 FM has been designed to mainly utilize passive thermal control in order to minimize power consumption, but the active control method using heaters has been applied to some critical parts. Also, thermal analysis has been performed for DubaiSat-1's mission orbit using a thermal analysis model. The thermal design is modified and optimized to satisfy the design temperature requirements for all parts according to the analysis result. The thermal control performance of DubaiSat-1 FM is verified by thermal vacuum space simulation, consisting of thermal cycling and thermal balance test. Also, to validate the thermal modeling of DubaiSat-1 FM, comparison of test results with analysis has been performed and model calibration has been completed.

• 전기의세계
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• v.45 no.2
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• pp.17-24
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• 1996

차단기의 개발과정은 크게 모의시험, 설계 및 제작, 성능시험 3가지로 나누어 볼 수 있다.이 중에서 모의 시험은 일반적으로 해석기술에 의해 주로 이루어지며, 차단기에 적용되는 해석기술은 1) 차단부 전계해석 2) 차단부 냉가스 유동해석 3) 차단부 열가스 유동해석(차단성능해석) 4) 차단기 동작특성해석 5) 차단기 응력해석 및 구조해석으로 대별할 수 있다. 상기의 해석기술은 적용하는 해석방법에 따라 다소 차이가 있지만, 1992년부터 당 연구팀이 개발중인 800kV 40kA 4000A 차단부를 개발하는 과정에 적용한 해석수법을 중심으로 살펴보기로 한다.