• Industry Promotion Research
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• v.9 no.2
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• pp.37-44
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• 2024

This study selected the worst-case scenario for fireball and vapor cloud explosion (VCE) of a styrene monomer storage tank installed in a petrochemical production plant and performed damage prediction and accident impact analysis. The range of influence of radiant heat and overpressure due to fireball and vapor VCE during the abnormal polymerization reaction of styrene monomer, the main component of the mixed residue oil storage tank, was quantitatively analyzed by applying the e-CA accident damage prediction program. The damage impact areas of radiant heat and explosion overpressure are analyzed to have a maximum radius of 1,150m and 626m, respectively. People within 1,150m of radiant heat of 4kW/m2 may have their skin swell when exposed to it for 20 seconds. In buildings within 626m, where an explosion overpressure of 21kPa is applied, steel structures may be damaged and separated from the foundation, and people may suffer physical injuries. In the event of a fire, explosion or leak, determine the risk standards such as the degree of risk and acceptability to workers in the work place, nearby residents, or surrounding facilities due to radiant heat or overpressure, identify the hazards and risks of the materials handled, and establish an emergency response system. It is expected that it will be helpful in establishing measures to minimize damage to workplaces through improvement and investment activities.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.25-25
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• 1999

응답 함수는 추진제의 연소 불안정성을 예측하는데 사용되는 중요한 측정 방법중 하나이다. 복사 열속과 압력은 연소 불안정을 일으키는 주요인으로 알려져 있다. 최근에는 레이저 기술의 발달로 비접촉 방식으로 외부에서 연소장을 교란하여 불안정성을 판단하는 실험 연구가 많이 이뤄지고 있다. 이러한 실험 연구에 대한 해석 및 예측을 위하여 많은 연구자들이 이론 응답 함수를 구하려는 노력들을 하고 있다. De Luca 등이 복사열에 대한 응답 함수를 제안한데 이어 Brewster 등은 QSHOD 가정과 추진제 내부로의 복사열 흡수비를 고려하여 응답 함수를 구하였다 Lee 등은 ZN 방법을 사용하여 Brewster의 응답 함수를 재계산 하였다. 이와 같은 이론 응답 함수들은 연소 불안정성에 대한 유용한 정보들을 제공하였음에도 불구하고, 현상을 너무 단순화하였다는 한계를 가지고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.507-514
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• 2012

In the present research, NASA LRB plume radiation models are reconstructed with Thermal Desktop software, where the radiation to vehicle base environment can be calculated. The calculation shows the similar radiation heat compared to NASA prediction. Based on LRB plume radiation model, a KSLV-II thermal radiation model is proposed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.92-98
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• 2006

An 1 lbf of NASA standard monopropellant thruster, MRE-1, is used for KOMPSAT (Korea Multi-Purpose Satellite) which is launched in 2006 and provides reliable and cost-effective means for attitude and maneuvering control system. The monopropellant thruster obtains required thrust by thermal decomposition process of propellant through catalyst bed. During firing, the decomposition plays a role of a heat source that may occur an excessive radiation heat transfer to peripheral structures and electronics in relatively low temperature condition.Therefore, the radiation heat shield is needed to prevent the critical radiative heat exchange between thruster and satellite during firing. This paper summarizes an overall development process of radiation heat shield from the design engineering up to the manufacturing.

• Journal of Ocean Engineering and Technology
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• v.33 no.4
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• pp.330-339
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• 2019

Radiant heat shields are normally installed on offshore oil and gas platforms to protect personnel, equipment, and structures from the thermal radiation emitted by a flare system. A heat shield should be individually designed to reduce the thermal radiation to the target level, and then manufactured and installed after the performance verification. However, in general, a heat shield is designed and manufactured by trial and error based on the performance test. For this reason, it is difficult to develop and design radiant heat shields in the Korean shipbuilding and marine equipment industry because of the lack of performance test data and limited experience. In the present study, the results of experiments conducted to verify the performances of radiant heat shields were analyzed, and the thermal radiation characteristics and performance characteristics of the radiant heat shields were investigated. The insights and conclusions developed in the present study will be useful in terms of the design and development of radiant heat shield, as well as in their performance verification tests.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.9
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• pp.737-744
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• 2012

The finite volume method for radiation is applied for the analysis of radiative base heating by SE and PE of the aircraft exhaust plume. The exhaust plume is considered as an absorbing, emitting, and scattering medium, while the base plane is assumed to be cold and black. The radiative properties of non-gray gases are obtained through the WSGGM, and the particle is modelled as spheres. The present method is validated by comparing the results with those of the backward Monte-Carlo method and then the radiative base heating characteristics are analyzed by changing such various parameters as particle concentration, temperature, and scattering phase function. The results show that the radiative heat flux coming into the base plane decreases with altitude and distance, but it increases as the particle temperature increases. The forward scattering of particles increases PE while it decreases SE.

• Korean Journal of Air-Conditioning and Refrigeration Engineering
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• v.5 no.4
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• pp.295-305
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• 1993

Thermal performance of test cell of model hot water Ondol house was simulated by equivalence heat resistence and heat capacity method. In this method wall was replaced by two equivalence and one heat capacity. This method enables to simulate the variation of temperature of each element of model house. The effect of pipe diameter, pitch of pipe and with or without consideration of inter-radiation between wall surfaces on the energy consumption rate were investgated. Results show that radiations between the ground surface of room and wall surfaces contribute to the heating of room air by reducing the convection heat loss through the wall surfaces.

• Proceedings of the Korea Water Resources Association Conference
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• 2023.05a
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• pp.44-44
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• 2023

지표면 위 에너지 수지, 즉 순 복사에너지가 어떤 비율로 지열, 현열, 잠열로 분할되는지를 이해하는 것은 매우 중요한 문제이지만, 에너지 분할과 주변 환경 변수 사이의 인과관계를 역학적으로 설명하는 것은 난제로 남아있다. 이 연구에서는 지표면 에너지 분할에서 어떠한 조건에서라도 보편적으로 발견되는 특성을 찾아서 다양한 식생 조건에서 관측된 복사에너지 및 열 플럭스 관측소의 자료를 토대로 각 에너지 항의 시간 변동성을 분석했다. 시계열 분석을 위해 공분산 기법을 통해 관측한 현열 및 잠열 자료를 제공하는 Fluxnet 자료를 사용했으며, International Geosphere-Biosphere Programme (IGBP) 구분법에 따라 낙엽수림, 상록수림, 농지 및 사바나에 위치한 관측소의 자료를 비교 분석했다. 모든 관측소에서 에너지 수지에서 현열과 잠열의 합이 전체 순 복사에너지에서 차지하는 비중은 시간에 따라 큰 변화를 보이지 않는다는 특성을 발견했다. 하지만, 현열 또는 잠열이 차지하는 비중은 큰 계절성을 보여주고 있었다. 이를 종합하면 현열과 잠열이 상호보완적으로 발생한다는 것을 의미한다. 한편 시간에 따른 두 열 플럭스의 움직임은 해당 관측소 근처에서 서식하는 식생 특성과 깊게 관련됐음을 확인했다.

• Journal of Astronomy and Space Sciences
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• v.23 no.2
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• pp.153-160
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• 2006

A Protomodel Space Infrared Cryogenic System (PSICS) cooled by a stirling cry-ocooler has been designed. The PSICS has an IR sensor inside the cold box which is cooled by a stirling cryocooler with refrigeration capacity of 500mW at 80K in a vacuum vessel. It is important to minimize the heat load so that the background thermal noise can be reduced. In order to design the cryogenic system with low heat load and to reduce the remained heat load, we have performed numerical analyses. In this paper, we present the design factors and the results obtained by the thermal analysis of the PSICS.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.12
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• pp.1079-1088
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• 2015

Parallelism and performance enhancement of calculating view factors in KSDS developed by KARI is introduced in this paper. View factor is an essential parameters of radiation thermal analysis for a spacecraft, and the amount of computation of them is not negligible. Especially, independent integration of view factors at each position of the orbit because the relative displace between solar panel and main body of a satellite varies with the position on the orbit. This paper introduces a range of parallelism of computing view factor and their performance, detection of obstructions by spatial search algorithm based on KD-Tree, and the reduction of the calculation of view factors of a satellite with relative motion between solar panel and main body, called updating fractional view factor matrix, for satellite thermal analysis.