• The Magazine of the Society of Air-Conditioning and Refrigerating Engineers of Korea
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• v.35 no.12
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• pp.16-32
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• 2006

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.12
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• pp.90-95
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• 2006

The wall of thermal vacuum chamber which is used for the satellite thermal balance test doesn't absorb satellite's IR emission perfectly and reflects some part of that. It is estimated that small thermal vacuum chamber has relatively larger wall effect than the big one. The small thermal vacuum chamber is required for the small satellite test to reduce the test cost. A quantitative analysis was carried out to investigate the chamber wall effect. As a result, temperature errors caused by chamber wall effect was calculated, and the temperature data acquired in the thermal balance test have been compensated. By defining the optimized area ratio between chamber surface and satellite surface area, the baseline to be able to determine the minimum size of thermal vacuum chamber was established to minimize the wall effect. Also, theoretical analysis about transparent material coating which can reduce the chamber wall effect is conducted.

• Analytical Science and Technology
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• v.22 no.3
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• pp.191-200
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• 2009

The aim of this study was to evaluate and establish of emission test method for liquid phase building materials such as paint, adhesive, sealant by emission cell. A small-scale emission chamber and emission cell were used to evaluate emission of TVOC from paint, adhesive, sealant. The quantity of TVOC emission were measured by a gas chromatography/mass spectrometry (GC/MS). Background concentration of TVOC was below $10{\mu}g/m^3$ in the emission chamber and cell. Air tightness and recovery in chamber and cell showed good results. The recovery of thermal desorber for toluene and n-dodecane were about 120%. The repeatability of response factor and retention time in GC/MS below 30%. The method detection limit of VOCs ranged 0.04~8.82 ng. The concentration of TVOC emission using emission cell was 1.35~1.41 times higher than emission chamber. The correlation of TVOC emission using chamber and cell method was significantly high (r=0.91~0.97).

• Proceedings of the Korean Vacuum Society Conference
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• 2015.08a
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• pp.69.1-69.1
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• 2015

우주환경은 고진공 환경과 태양 복사열에 의한 고온 환경 및 극저온이 반복되는 가혹한 환경으로 특징지어지는데, 위성체는 지상에서 발사되어 우주궤도에 진입한 순간부터는 계속해서 우주환경에 노출된다. 위성체가 이러한 가혹한 우주환경에 노출될 경우 주요부품에 기능장애가 초래되기도 하며 이는 결국 임무의 실패로 이어지도 한다. 따라서 위성체는 지상에서 우주환경시험을 거쳐 기능 및 작동상태를 점검해야 하며, 이를 위해서는 우주환경을 모사 할 수 있는 우주환경 모사장비가 필요하다. 우주환경모사장비라함은 우주환경의 주특징인 고진공상태와 극저온 및 고온 환경을 모사할 수 있는 지상장비를 말하며, 통상 열진공챔버라고 불린다. 한국항공우주연구원에서는 위성의 부품레벨에서부터 대형위성시스템의 열진공시험 수행을 위한 다양한 진공챔버를 보유하고 있으며, 그 직경이 0.7 m인 소형에서부터 직경 9 m, 길이 10 m급의 대형열진공챔버에 이른다. 대형 챔버의 경우 고기능화에 따라 대형화 되어 가는 위성의 국산화 개발을 위하여 순수 국내 기술로 제작된 우주환경모사용 챔버이다. 본 대형열진공챔버의 제작 및 유지 현황에 대해 논의한다.

• The Journal of the Korea Contents Association
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• v.15 no.12
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• pp.1-7
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• 2015

These anti-jamming GPS systems are verified using large anechoic chamber or field-test until now. When using a large anechoic chamber, Independent verification from external enviroments like noise is an advantage but high cost and availability of chamber are disadvantages. And in case of field test, verification under real propagation enviroment is an advantage but security problem of military equipments and problem of making same test condition are disadvantages. This paper presents an newly developed anti-jamming GPS test system. This test system mainly consists of small anechoic chamber, jamming divider, jamming signal generator and satellite simulator. The small anechoic chamber is installed many jamming antennas to transmit multi jamming signals and the jamming divider is newly developed to control multi jamming signals. According to self performance test and combined test with Anti-jamming GPS receiver, we verified our system's reliability.

• Air Cleaning Technology
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• v.17 no.1 s.64
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• pp.55-66
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.5
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• pp.407-415
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• 2021

The performance of satellite parts must be verified under the space orbit environment before the launch. This paper develops a model formula considering the thermal environment such as conduction, radiation, heat loss and internal heating between satellite parts and a small thermal vacuum chamber for thermal vacuum tests. System identification is carried out using test data from 20 recent thermal vacuum tests conducted by the Korea Aerospace Research Institute. It is verified that the model formula and the identification results are valid, except when the heating of the functional test of the test specimen is not constant.

• Journal of the Korean Solar Energy Society
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• v.26 no.3
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• pp.99-110
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• 2006

This study focused on the emission rate of the construction materials. The method of study is as follows. First, validation of small chamber method to determine emission rate of construction material was performed by CFD simulation. For the result of this study, uniform air velocity in small chamber was founded, and small chamber as a test material for emission rate was validated. Second, the construction materials were categorized by their feature and the emission rate of volatile organic compound was determined. Totally, VOCs emission rate of 49 materials were determined.

• Proceedings of the Korea Air Pollution Research Association Conference
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• 2004.11a
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• pp.495-496
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• 2004

• Proceedings of the Korea Air Pollution Research Association Conference
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• 2006.04a
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• pp.191-192
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• 2006