• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.113-121
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• 2009

Shaker system is used to simulate the vibration from the launch environment. The vibration tests are performed in the vertical and lateral direction. For the lateral vibration test, the slip table system is used with shaker system. For the latest large satellite, vibration test adaptor is made of the steel. But slip table of lateral vibration is made of magnesium, so there is big difference of thermal expansion ratio between slip table and vibration test adaptor. This paper encompasses the following items; verification process of thermal characteristics and overturning moment and a solution for lateral vibration test with steel vibration test adaptor.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.170-178
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• 2009

In order to develope a common ground system, a general procedure language that can be used in both EGSE and MCS is primarily needed. As the first step in developing a common test and integration procedure language, KARI's ATS for AIT and MCE for GS were compared to some of the most representative languages such as PLUTO regarded European standard, STOL and ELISA and PIL. Based on the analysis, design features of developing a common test and integration procedure language were presented.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2001.05a
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• pp.329-332
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• 2001

In this paper, it's shown that the saturable absorber Nd:LSB has a capability as a saturable absorber in Q-switching system. In the passively Q-switched 1.3${\mu}{\textrm}{m}$ Nd:YAG laser with saturable absorber, we theoretically investigated the optimized output mirror, peak power, output power, pulse width and output efficiency. The passively Q-switched Nd:YAG laser with saturable absorber Nd:LSB gives peak power of 30MW and pulse width of 6.23 ps at 30cm resonator length and output mirror reflectivity 98%. Consequently the output energies are 143, 200 and 209 $\mu$J at loss of 2.2%, 2.1% and 1.5%, respectively.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.08a
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• pp.38-38
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• 2010

낮은 세기의 레이저와 정지한 전자가 반응하면 전자는 레이저 전기장 세기에 비례하여 가속되며 레이저의 파장과 같은 파장의 빛을 낸다. 반면, 레이저의 세기가 일정 수준을 넘으면 전자의 속도가 빛의 속도에 가까워지게 되어 가속이 둔화되는 현상이 나타나며, 더 이상 전기장의 세기와 가속도가 비례하지 않게 된다. 이러한 비선형적인 전자의 운동이 레이저 기본 파장의 조화파(harmonic)를 발생시키는데, 이를 상대론적 비선형 톰슨 산란(relativistic nonlinear Thomson scattering, RNTS)이라고 한다. 단일 전자를 가정한 경우 RNTS에 의해 아토초($10^{-18}$ 초) 길이의 X선 펄스가 발생하는 것이 시뮬레이션 연구를 통해 잘 알려졌다. [1] 그러나, 실제 실험에서 적용할 수 있는 것은 단일 전자가 아니라 고체, 플라즈마, 전자 빔 등의 전자 덩어리이다. 전자덩어리를 구성하는 각각의 전자가 아토초 펄스를 발생시더라도 각각의 펄스 간에 결맞음(coherence) 조건이 맞지 않으면 아토초 펄스는 발생되지 않는다. 또한, 강한 세기의 펄스를 얻는데도 결맞음은 중요하다. 이 연구에서는 결맞음 조건으로 얇은 타깃에 대한 거울 반사 조건, 즉 레이저가 얇은 타깃에 입사되며 거울의 반사 조건을 만족하는 위치에 검출기(detector)를 위치시키는 방법을 제안하였다. 박막이 충분히 얇을 경우 각각의 전자에 대하여 레이저가 발사되어 타깃에 맞고 검출되기까지의 시간이 거의 일치하게 된다. 거울 반사 조건에 의한 아토초 펄스 발생은 particle-in-cell 방법을 통한 시뮬레이션으로 검증되었다. 결맞음 조건을 위한 얇은 타깃으로는 박막과 나노선 배열(nanowire array)을 사용하였다. 전자들 간의 쿨롱(Coulomb) 힘은 결맞음이 유지되는 것을 방해하는데, 박막에 비해 나노선 배열이 쿨롱 힘의 영향을 적게 받기 때문에 결맞음이 더 잘 유지된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.66-72
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• 2003

The cooling mechanism for a liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of both the regenerative and curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket en g i.ne could be improved.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.12
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• pp.1258-1263
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• 2009

This paper describes the design and test results of engineering qualification model(EQM) of mass memory unit(MMU) for STSAT-3. The MMU for STSAT-3 having 32Gb mass memory capacity is capable of receiving and transmitting the mission data from MIRIS(Multi-purpose IR Imaging System) and COMIS(Compact Imaging Spectrometer) at 100Mbps and 10Mbps. The performance of EQM MMU was verified by the tests of data receiving from two payloads and data transmission to the data receiving system. Moreover, the vibration and thermal vacuum test was performed to verify the launch vehicle and space environments.

• Journal of Satellite, Information and Communications
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• v.3 no.2
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• pp.43-47
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• 2008

COMS is the one of Korean hybrid geostationary satellite and is scheduled to be launched in 2009 by Arian V into $128^{\circ}$ E longitude. COMS is designed and manufactured for three main objectives which are Communications, Oceanographic, and Meteorological missions. It provides the weather monitoring, ocean monitoring, and Ka band satellite communication services by means of three different payloads. The Ka band communications payload was developed by Electronics and Telecommunications Research Institute (ETRI), and provides not only the digital transmission for the communication services against natural disaster but also digital transmission for the high speed multimedia services. This paper describes the overview of the electrical and mechanical design and measured performances of the Ka band communications transponder flight model (FM) for COMS.

• Journal of Astronomy and Space Sciences
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• v.20 no.1
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• pp.53-62
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• 2003

SPS(Space Physics Sensor) onboard the KOMPSAT-I, which was launched at 1999, had transmitted ionospheric plasma density and electron temperature during the solar maximum from June 2000 to August 2001, SPS IMS onboard KOMPSAT-I occasionally detected abrupt plasma density enhancement in low-latitude region, in which the plasma density abruptly increases in a narrow region. Statistical analysis of the data obtained during the entire operational period shows that the occurrence probability of these events has its peak value at the Atlantic region and at the Hawaiian region where the geomagnetic field strength is weak. And the occurrence frequency has no correlation with Dst index or F10.7 index. The correlation between plasma density and the electron temperature shows a wide variety, but the anti-correlated cases are dominant.

• The Bulletin of The Korean Astronomical Society
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• v.36 no.2
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• pp.126.2-126.2
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• 2011

MIRIS(Multipurpose InfraRed Imaging System)는 과학기술위성 3호의 주 탑재체이며 2012년 하반기 발사예정이다. MIRIS 우주관측 카메라는 0.9-2.0 ${\mu}m$ 영역에서 3.67 deg. x 3.67 deg. FOV로 우리 은하평면 survey 관측과 우주배경복사(CIB) 관측을 수행할 것이다. 현재 MIRIS는 비행모델 개발 마무리 단계에 있으며, 검교정 시험, 열-진공 시험, 진동 시험 등을 수행하고 나면 2011년 말 위성 본체와의 조립을 진행할 것이다. 망원경이 복사냉각(Passive Cooling)을 통해 200K 이하로 냉각되면, dewar에 설치된 소형 냉각기를 가동하여 적외선 센서를 90K 정도로 냉각한다. MIRIS 우주관측카메라에는 PICNIC($256{\times}256$ pixel) 센서를 사용하였고, 상온과 냉각된 상태에서의 노이즈 특성을 측정하였다. PICNIC 센서와 dewar내부를 냉각하기 위해 RICOR사의 K-508 micro stirling cooler를 사용하는데, cooler가 동작하면서 전자부에 영향을 주어 주된 잡음으로 나타남을 확인하였다. Cooler에서 발생하는 잡음을 최소화 하기위해 fanout B/D와 LVPS 부분을 개선하였으며, 본 발표에서는 잡음 측정 결과에 대해 논의 하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.3
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• pp.109-117
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• 2006

Hot firing performance test of hydrazine decomposition catalyst used for monopropellant thruster of satellite and launch vehicle was performed on the ground. A test equipment for hot firing performance measurement of catalyst test was developed in collaboration with Hanwha Corp., and the catalyst firing performance were tested with the equipment. After a reaction delay time, a catalyst activity and a granule stability were measured for 2 times, satisfactory results were obtained such as 25msec, 2%, $704^{\circ}C$ for each test items on the average. In addition, the current development status of domestic prototype catalyst and its decomposition performance test results are presented.