• Bulletin of the Korean Chemical Society
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• 제27권12호
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• pp.2002-2010
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• 2006

This study examined the quenching of ofloxacin (OFL) and flumequine (FLU) fluorescence by $Cuj^{2+}$, $Ni^{2+}$, $Co^{2+}$ and $Mn^{2+}$ in an aqueous solution. The change in the fluorescence intensity and lifetime was measured at various temperatures as a function of the quencher concentration. According to the Stern-Volmer plots, the fluorescence emission was quenched by both collisions (dynamic quenching) and complex formation (static quenching) with the same quencher but the effect of static quenching was larger than that of dynamic quenching. Large static and dynamic quenching constants for both OFL and FLU support significant ion-dipole and orbital-orbital interactions between fluorophore and quencher. For both molecules, the static and dynamic quenching constants by $Cu^{2+}$ were the largest among all the metal quenchers examined in this study. In addition, both the static and dynamic quenching mechanisms by $Cu^{2+}$ were somewhat different from the quenching caused by other metals. Between $Ni^{2+}$ and FLU, a different form of chemical interaction was observed compared with the interaction by other metals. The change in the absorption spectra as a result of the addition of a quencher provided information on static quenching. With all these metals, the static quenching constant of FLU was larger than those of OFL. The fluorescence of OFL was quite insensitive to both the dynamic and static quenching compared with FLU. This property of OFL can be explained by the twisted intramolecular charge transfer in the excited state.

• Journal of Astronomy and Space Sciences
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• 제34권4호
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• pp.289-302
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• 2017

The key risk analysis technologies for the re-entry of space objects into Earth's atmosphere are divided into four categories: cataloguing and databases of the re-entry of space objects, lifetime and re-entry trajectory predictions, break-up models after re-entry and multiple debris distribution predictions, and ground impact probability models. In this study, we focused on reentry prediction, including orbital lifetime assessments, for space situational awareness systems. Re-entry predictions are very difficult and are affected by various sources of uncertainty. In particular, during uncontrolled re-entry, large spacecraft may break into several pieces of debris, and the surviving fragments can be a significant hazard for persons and properties on the ground. In recent years, specific methods and procedures have been developed to provide clear information for predicting and analyzing the re-entry of space objects and for ground-risk assessments. Representative tools include object reentry survival analysis tool (ORSAT) and debris assessment software (DAS) developed by National Aeronautics and Space Administration (NASA), spacecraft atmospheric re-entry and aerothermal break-up (SCARAB) and debris risk assessment and mitigation analysis (DRAMA) developed by European Space Agency (ESA), and semi-analytic tool for end of life analysis (STELA) developed by Centre National d'Etudes Spatiales (CNES). In this study, various surveys of existing re-entry space objects are reviewed, and an efficient re-entry prediction technique is suggested based on STELA, the life-cycle analysis tool for satellites, and DRAMA, a re-entry analysis tool. To verify the proposed method, the re-entry of the Tiangong-1 Space Lab, which is expected to re-enter Earth's atmosphere shortly, was simulated. Eventually, these results will provide a basis for space situational awareness risk analyses of the re-entry of space objects.

• 한국항공우주학회지
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• 제42권10호
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• pp.870-877
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• 2014

정지궤도위성은 궤도상에서 다양한 궤도상 교란을 겪고 이로 인해 시간이 증가함에 따라 위성의 위치가 변화하게 되는데 이러한 위성의 위치변화를 제어하기 위해 추력기가 사용된다. 이를 위해 적정한 양의 액체추진제가 탑재되며 시간이 지남에 따라 이러한 추진제의 양은 감소된다. 이는 궤도상에서 운용되는 위성의 수명은 추진제 잔여량에 좌우됨을 의미한다. 그러므로, 정확한 잔여추진제량 측정은 때이른 수명종료로 야기되는 경제적 손실을 완화시킬 뿐만 아니라 후속위성의 대체나 위성망 운용계획 등에 매우 중요하다. 본 논문에서는 현재 정지궤도위성에서 사용되고 있는 잔여추진제 측정방법들과 실험실 수준에서 연구되고 있는 잔여추진제 측정방법들에 대해 소개하고자 한다.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2009년도 제38회 동계학술대회 초록집
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• pp.379-379
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• 2010

Recent technical advances in OLEDs (organic light emitting devices) requires more and more the improvement in low operation voltage, long lifetime, and high luminance efficiency. Inverted top emission OLEDs (ITOLED) appeared to overcome these problems. This evolved to operate better luminance efficiency from conventional OLEDs. First, it has large open area so to be brighter than conventional OLEDs. Also easy integration is possible with Si-based driving circuits for active matrix OLED. But, a proper buffer layer for carrier injection is needed in order to get a good performance. The buffer layer protects underlying organic materials against destructive particles during the electrode deposition and improves their charge transport efficiency by reducing the charge injection barrier. Hexaazatriphenylene-hexacarbonitrile (HAT-CN), a discoid organic molecule, has been used successfully in tandem OLEDs due to its high workfunction more than 6.1 eV. And it has the lowest unoccupied molecular orbital (LUMO) level near to Fermi level. So it plays like a strong electron acceptor. In this experiment, we measured energy level alignment and hole current density on inverted OLED structures for hole injection. The normal film structure of Al/NPB/ITO showed bad characteristics while the HAT-CN insertion between Al and NPB greatly improved hole current density. The behavior can be explained by charge generation at the HAT-CN/NPB interface and gap state formation at Al/HAT-CN interface, respectively. This result indicates that a proper organic buffer layer can be successfully utilized to enhance hole injection efficiency even with low work function Al anode.

• Journal of Astronomy and Space Sciences
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• 제36권3호
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• pp.213-223
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• 2019

This paper analyzes delta-Vs to maintain an extremely low altitude on the Moon and investigates the possibilities of performing a CubeSat mission. To formulate the station-keeping (SK) problem at an extremely low altitude, current work has utilized real-flight performance proven software, the Systems Tool Kit Astrogator by Analytical Graphics Inc. With a high-fidelity force model, properties of SK maneuver delta-Vs to maintain an extremely low altitude are successfully derived with respect to different sets of reference orbits; of different altitudes as well as deadband limits. The effect of the degree and order selection of lunar gravitational harmonics on the overall SK maneuver strategy is also analyzed. Based on the derived SK maneuver delta-V costs, the possibilities of performing a CubeSat mission are analyzed with the expected mission lifetime by applying the current flight-proven miniaturized propulsion system performances. Moreover, the lunar surface coverage as well as the orbital characteristics of a candidate reference orbit are discussed. As a result, it is concluded that an approximately 15-kg class CubeSat could maintain an orbit (30-50 km reference altitude having ${\pm}10km$ deadband limits) around the Moon for 1-6 months and provide almost full coverage of the lunar surface.

• 대한원격탐사학회지
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• 제15권3호
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• pp.227-238
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• 1999

발사 이전에 OSMI 모의 복사량을 산출함은 실제로 관측할 자료를 추정하고, 자료처리를 위한 준비에 매우 유용하다. 1999년 발사예정인 다목적 실용위성의 탑재체 중의 하나인 OSMI 자료처리 시스템은 SeaWIFS 자료처리 시스템을 OSMI에 맞추어 재개발된 것이다. 모의 복사량 계산은 OSMI 센서의 파장대역 및 스캔방식, 다목적 실용위성의 궤도에 관한 정보가 고려되어야 한다. 본 연구에서는 대양에서의 OSMI 모의 복사량을 산출하기 위해 CZCS에서 관측한 엽록소를 다목적 실용위성이 관측한다는 가정을 하게 되었다. 궤도 예측에는 수정된 Brouwer-Lyddane 모델이, water-leaving 복사량을 산출하기 위해 CZCS 엽록소 농도가, OSMI가 관측할 대기에 의한 복사량 계산에는 여러 가지 복사모델이 이용되었다. OSMI의 412, 443, 490, 555, 765, 865nm 6가시광선 파장대역에서 모의 복사량을 산출하였다. 예상대로, 총 복사량 중 water-leaving 복사량은 아주 작으며 (10% 미만), 태양해면반사에 의한 영향은 태양 적위 근처에서 관측된다. 그러므로 대기보정은 총 복사량으로부터 엽록소 농도를 계산하는데 매우 중요하다. 태양해면반사에 의해 영향을 받는 자료는 사용할 수 없으므로 OSMI 임무 기간내에 지속적인 전구 해양관측을 위해서는 체계적인 자료수집 계획이 요구된다.