• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.50.1-50.1
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• 2009

광학탑재체 열제어 시스템(Cooling Unit)은 광학카메라가 우주환경 하에서 작동시 영상검출기(FPA)에서 발생하는 열을 효과적으로 발열하여 영상검출기의 온도를 최적으로 제어하는 시스템이다. 영상검출기(FPA)의 1회 orbit은 100분이며, 예열기간(Preheating) 최대 10분 동안 147W를 발열하고, 촬영기간(Imaging) 10분 동안 147W를 발열하여 1회 orbit 평균 32.6W를 발열하고, Parasitic heat load 15W를 고려하면 1회 orbit당 평균 총 50W를 발열 한다. 열제어 시스템은 50W를 효과적으로 발열하여 영상검출기의 온도를 $14^{\circ}C{\sim}26^{\circ}C$로 제어한다. 열제어 시스템은 Buffer Mass, Heat Pipe, Radiator로 구성된다. 열제에 시스템의 성능규격은 열주기시험, 열진공하 열전도시험 및 진동시험을 통하여 검증한다. 이 논문에서는 국내 기술로 개발되는 우주용 카메라 열제어 장치의 설계 및 해석, 제작현황 등을 소개하고자 한다.

• Proceedings of the Korean Nuclear Society Conference
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• 1995.05a
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• pp.525-530
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• 1995

최적 열수력 전산 코드인 CATHARE2 Vl.3u 코드를 이용하여 영광 3/4호기 midloop 운전중 잔열제거(RHR) 기능 상실사고를 해석하였다. 본 연구의 주된 목적은 사고시 계통에서 발생하는 열수력 현상의 이해 향상 및 증기발생기 열제거 능력 평가에 있다. 사고 복구 절차 관점에서 노심 비등, 노출 시점 및 계통압력 등이 중요한 인자이다. 본 계산 수행시 사용한 가정은 다음과 같다. 가) 초기 계통 수위는 고온관 중간에 위치하며 그 윗 부분은 질소 가스로 차 있다. 나) 3/4 인치 크기의 방출 밸브가 원자로 용기 상부 및 가압기 상부에 각각 설치되어 있으며, RHR 흡입구에 수위지시계가 설치되어 있다. 다) 증기발생기의 이차측은 U-튜브가 잠기도록 물로 차있다. 라) 두 증기발생기의 대기 방출 밸브(ADV)는 항상 열려 있어 사고시 이차측 압력을 대기압으로 유지하기에 충분하다. 사고는 원자로 정지 2일 후 발생하였다고 가정한다. 이와 같은 조건하에서 사고시 주된 계통 열제거 수단은 증기발생기 U-튜브내의 응축 작용이며 이는 전체 열제거량의 94%로 나타났다. 노심 비등 시점온 사고후∼300초 이후이며, 계통압력은 10,800초 이후에 최고 압력인 0.25MPa에 도달한 후 그 값을 계속 유지하고 있다. RHR 배관에 연결된 수위지 시계를 통해 10,200초 이후부터 냉각수가 방출되었다. 2개의 방출밸브 및 수위지시계를 통하여 방출된 유량에 근거하여 원자로 용기 냉각재 수위가 고온관 바닦까지 낮아지는 시점을 계산하면 사고 약 6.4 시간 이후가 된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.789-794
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• 2014

The FPGA is used to the high speed digital satellite communication on the Digital Signal Process Unit of the next generation GEO communication satellite. The high capacity FPGA has the high power dissipation and it is difficult to satisfy the derating requirement of temperature. This matter is the major factor to degrade the equipment life and reliability. The thermal control at the equipment level has been worked through thermal conduction in the space environment. The FPGA of CCGA or BGA package type was mounted on printed circuit board, but the PCB has low efficient to the thermal control. For the FPGA heat dissipation, the heat sink was applied between part lid and housing of equipment and the performance of heat sink was confirmed via thermal vacuum test under the condition of space qualification level. The FPGA of high power dissipation has been difficult to apply for space application, but FPGA with heat sink could be used to space application with the derating temperature margin.

• Journal of Veterinary Clinics
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• v.31 no.5
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• pp.461-465
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• 2014

A 3-year-old colt Thoroughbred horse was referred with obvious lameness (3/5G) and mild heat and pain on left hoof of forelimb. He was diagnosed with quarter cracks that have a typical conformation of sheared heel, which are a different length and height between medial/lateral heels. Various materials and techniques were carried out to repair quarter cracks by using many different kinds of clips, bar shoes on fifth times for about 10 months. It worked on him without pain and heat on the cracked hoof, and then he could retrain for racing from the 36th weeks beginning of therapeutic shoeing. We suggested that especially fiberglass reinforced plastic (FRP) material and therapeutic shoeing were a great help to treat quarter cracks induced by sheared heel.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.5
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• pp.430-436
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• 2014

The mission objective of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) classified as a pico-class satellite is to verify the technical effectiveness of payloads such as variable emittance radiator, SMA washer, oscillating heat pipe and MEMS based solid propellant thruster researched at domestic universities. In addition, the MEMS concentrating photovoltaic power system and the non-explosive holding and separation mechanism with the advantages of high constraint force and low shock level will be developed as the primary payloads for on-orbit verification. In this study, the feasibility of the mission actualization has been confirmed by the preliminary system design.

• Journal of Aerospace System Engineering
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• v.12 no.4
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• pp.75-80
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• 2018

The working principle of a satellite camera involves a focusing mechanism for controlling the focus of the optical system, which is essential for proper functioning. However, research on focusing mechanisms of satellite optical systems in Korea is in the beginning stage and developed technology is limited to a thermal control type. Therefore, in this paper, we propose a motor-driven focusing mechanism applicable to small satellite optical systems. The proposed mechanism is designed to generate z-axis displacement in the secondary mirror by a motor. In addition, three flexure hinges have been installed on the supporter for application of preload on the mechanism resulting in minimization of the alignment error arising due to manufacturing tolerance and assembly tolerance within the mechanism. After fabrication of the mechanism, the alignment errors (de-space, de-center, and tilt) were measured with LVDT sensors and laser displacement meters. Conclusively, the proposed focusing mechanism could achieve proper alignment degree, which can be applicable to small satellite optical system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.12
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• pp.1013-1019
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• 2014

Solid-liquid Phase Change Material(PCM) as a thermal control hardware for the electro-optical payload of low earth orbit satellite is numerically studied which can be substituted with Thermal Buffer Mass(TBM). The electro-optical module in LEO satellite is periodically work and high heat is dissipated during the imaging period, however, the design temperature range is very tight and sensitive. In order to handle this problem TBM is added and as a result the time constant of the module temperature increases. TBM is made of Al6010 and its mass directly affects the system design. To save the mass PCM is suggested in this study. The latent heat of melting or solidification is very high and small amount of PCM can play a role instead of TBM. The result shows that only 12% of TBM mass is enough to control the module temperature using PCM.

• Journal of Energy Engineering
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• v.26 no.3
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• pp.64-70
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• 2017

The concept of Hybrid Safety Injection Tank (Hybrid SIT) proposed by the Korea Atomic Energy Research Institute (KAERI) has been introduced for the purpose of application to the Advanced Power Reactor Plus (APR+). In this study, the SBO situation of the APR+ was analyzed by using the MARS-KS code in order to evaluate whether the operation of the Hybrid SIT has an effect on the cooling performance of the Reactor Coolant System (RCS). According to the analysis, when the actuation valve on the pressure balancing line (PBL) is opened, the Hybrid SIT's pressure rises rapidly, forming equilibrium with the RCS pressure; subsequently, a flow is injected from the Hybrid SIT into the reactor vessel through the direct vessel injection (DVI) line. The analysis showed that it is possible to keep the core temperature below melting temperature during the operation of a Hybrid SIT.