• Journal of Astronomy and Space Sciences
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• 제30권3호
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• pp.133-140
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• 2013

Most of high energy cosmic rays (CRs) are thought to be produced by diffusive shock acceleration (DSA) at supernova remnants (SNRs) within the Galaxy. Fortunately, nonthermal emissions from CR protons and electrons can provide direct observational evidence for such a model and place strong constraints on the complex nonlinear plasma processes in DSA theory. In this study we calculate the energy spectra of CR protons and electrons in Type Ia SNRs, using time-dependent DSA simulations that incorporate phenomenological models for some wave-particle interactions. We demonstrate that the time-dependent evolution of the self-amplified magnetic fields, Alfv$\acute{e}$nic drift, and escape of the highest energy particles affect the energy spectra of accelerated protons and electrons, and so resulting nonthermal radiation spectrum. Especially, the spectral cutoffs in X-ray and ${\gamma}$-ray emission spectra are regulated by the evolution of the highest energy particles, which are injected at the early phase of SNRs. Thus detailed understandings of nonlinear wave-particle interactions and time-dependent DSA simulations of SNRs are crucial in testing the SNR hypothesis for the origin of Galactic cosmic rays.

• Nuclear Engineering and Technology
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• 제51권1호
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• pp.284-292
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• 2019

For the continuous operation of a nuclear reactor, burnt fuel needs to be replaced with fresh fuel, where appropriate (ex-vessel) fuel handling is required. Particularly for the Sodium-cooled Fast Reactor (SFR) refueling, its process has unique challenges due to liquid sodium coolant. The ex-vessel spent fuel transportation should concern several design features such as the radiation shielding, decay-heat removal, and inert space separated from air. This paper proposes a new design optimization methodology of cask shielding to transport the spent fuel assembly in a prototype SFR for the first time. The Particle Swarm Optimization (PSO) algorithm had been applied to design trade-offs between shielding and cask weight. The cask is designed as a double-cylinder structure to block an inert sodium region from the air-cooling space. The PSO process yielded the optimum shielding thickness of 26 cm, considering the weight as well. To confirm the shielding performance, the radiation dose of spent fuel removed at its peak burnup and after 1-year cooling was calculated. Two different fuel positions located during transportation were also investigated to consider a functional disorder in a cask drive system. This study concludes the current cask design in normal operations is satisfactory in accordance with regulatory rules.

• Journal of Astronomy and Space Sciences
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• 제13권2호
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• pp.149-162
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• 1996

1992년 8월에 발사된 한국의 첫번째 위성인 우리별 1호에는 저궤도 고에너지 입자환경를 관측하는 탑재체 cosmic ray experiment(CRE)가 실렸다. CRE는 크게 cosmic particle experiment(CPE)와 total dose esperiment(TDE) 두 시스템으로 구성된다. 이와 더불어 실험 탑재물은 아니지만, 프로그램 메모리와 램디스크(RAM disk)의 비트바뀜현상(SEU) 결과를 통해서 고에너지 입자환경에 대한 간접적인 정보를 얻을 수 있었다. 1993년 9월에 발사된 두 번재 위성 우리별 2호에는 OBCI인 KASCOM에서 프로그램 메모리와 램디스크 메모리에 대한 비트바뀜현상실험을 수행하였다. 우리별 1호와 2호는 그 구조는 비슷하지만 서로의 궤도가 다르기 때문에 두 위성의 실험결과를 분석해본다면 각 궤도에서의 고에너지 입자환경에 대한 비교연구할 수 있는 좋은 기회가 된다.

• Journal of Astronomy and Space Sciences
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• 제25권4호
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• pp.435-444
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• 2008

우주 방사선은 인공위성의 오동작을 유발하거나 수명을 단축하는 주된 요인 중 하나다. 반 알렌벨트라고 불리는 전하를 띤 고에너지 입자들이 지구 자기장에 포획된 공간은 이 지역에서 운용되는 인공위성뿐만 아니라, 지구 자기장을 따라 저고도까지 도달하므로 저궤도 위성들에게도 위협이 된다. 2003년 발사된 과학기술위성 1호에는 자세 제어를 위해 사용된 태양 센서가 탑재되었다. 태양 센서에는 빛을 감지하기 위한 검출기로 실리콘 태양 전지가 사용되었는데, 이 태양 전지의 합선 전류가 시간이 지남에 따라 감소하는 것이 관측되었다. 이 연구에서는 이러한 태양전지의 특성 변화가 어떠한 요인에 의해 발생하는지 지상에서의 방사능 실험을 통해 밝히고자 한다. 이를 위해 과학기술위성 1호에서 사용된 것과 동일한 태양 전지에 여러 에너지 대역의 고에너지 전자와 양성자를 조사하고 이 때 변하는 합선 전류를 측정하였다. 그리고 NOAA POES위성 데이터를 이용하여 과학기술위성 1호에 피폭되었을 방사선량을 예측하였다. 연구 결과, 과학기술위성 1호에 나타난 실리콘 태양 전지의 감쇠 현상은 700keV에서 1.5MeV의 에너지를 갖는 양성자에 의한 것으로 밝혀졌다. 이 연구 결과는 우주에서 태양 전지의 수명을 예측하기 위한 자료로 활용될 수 있다.

• Journal of Astronomy and Space Sciences
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• 제39권4호
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• pp.145-158
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• 2022

The dynamics of the outer zone radiation belt has received a lot of attention mainly due to the correlation between the occurrence of enhancing relativistic electron flux and spacecraft operation anomalies or even failures (e.g., Baker et al. 1994). Relativistic electron events are often observed during great storms associated with ultra low frequency (ULF) waves. For example, a large buildup of relativistic electrons was observed during the great storm of March 24, 1991 (e.g., Li et al. 1993; Hudson et al. 1995; Mann et al. 2013). However, the dominant processes which accelerate magnetospheric radiation belt electrons to MeV energies are not well understood. In this paper, we present observations of Pc5 ULF waves in the recovery phase of the Bastille day storm of July 16, 2000 and electron and proton flux simultaneously oscillating with the same frequencies as the waves. The mechanism for the observed electron and proton flux modulations is examined using ground-based and satellite observations. During this storm time, multiple packets of discrete frequency Pc5 ULF waves appeared associated with energetic particle flux oscillations. We model the drift paths of electrons and protons to determine if the particles drift through the ULF wave to understand why some particle fluxes are modulated by the ULF waves and others are not. We also analyze the flux oscillations of electrons and protons as a function of energy to determine if the particle modulations are caused by a ULF wave drift resonance or advection of a particle density gradient. We suggest that the energetic electron and proton modulations by Pc5 ULF waves provide further evidence in support of the important role that ULF waves play in outer radiation belt dyanamics during storm times.

• Journal of Astronomy and Space Sciences
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• 제31권1호
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• pp.25-31
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• 2014

There has been a rapid increase of the concern on the space radiation effect on pilots, crew and passengers at the commercial aircraft altitude (~ 10 km) recently. It is because domestic airline companies, Korean Air and Asiana Airlines have just begun operating the polar routes over the North Pole since 2006 and 2009 respectively. CARI-6 and CARI-6M are commonly used space radiation estimation programs which are provided officially by the U.S. federal aviation administration (FAA). In this paper, the route doses and the annual radiation doses for Korean pilots and cabin crew were estimated by using CARI-6M based on 2012 flight records. Also the modeling concept was developed for our own space radiation estimation program which is composed of GEANT4 and NRLMSIS00 models. The GEANT4 model is used to trace the incident particle transports in the atmosphere and the NRLMSIS00 model is used to get the background atmospheric densities of various neutral atoms at the aircraft altitude. Also presented are the results of simple integration tests of those models and the plan to include the space weather variations through the solar proton event (SPE) prediction model such as UMASEP and the galactic cosmic ray (GCR) prediction model such as Badhwar-O'Neill 2010.

• 한국시뮬레이션학회논문지
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• 제19권4호
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• pp.123-128
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• 2010

본 논문에서는 우주방사능 환경에서 우주방사능/총 누적 방사선량(TID) 및 이에 대한 시스템 영향과 정지궤도 위성 시스템 설계를 Spenvis 를 사용하여 분석하였다. 우주환경에서 정지궤도 위성 시스템이 겪게 될 우주방사선 환경을 포획된 입자, 태양 양성자 그리고 우주선으로 구분하여 각각 NASA AP8, JPL91 그리고 NRL CREME 모델을 사용하여 전산모사하였다. 임무수명기간 동안 전자부품에 계속적으로 피폭되는 전체 방사량을 알루미늄 차단두께의 함수로 나타내었으며, 이 값들은 디지털채널 처리부의 전자부품의 선택기준 및 위성체 또는 구성품의 구조물 두께를 설정할 수 있는 기준으로 제시한다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.347-350
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• 2004

A space radiation analysis has been used to evaluate an ability of electronic equipment boxes or spacecrafts to endure various radiation effects, so it helps design thicknesses of structure and allocate components to meet the radiation requirements. A comparison study of space radiation dose analysis programs SPENVIS Sectoring Tool (SST) and SIGMA II is conducted through some structure cases, simple sphere shell, box and representative satellite configurations. The results and a discussion of comparison will be given. A general comparison will be shown for understanding those programs. The both programs use the same strategy, solid angle sectoring with ray-tracing method to produce an approximate dose at points in representative simple and complex models of spacecraft structures. Also the particle environment data corresponding to mission specification and radiation transport data are used as input data. But there are distinctions between them. The specification of geometry model and its input scheme, the assignment of dose point and the numbers, the prerequisite programs and ways of representing results will be discussed. SST is a web-based interactive program for sectoring analysis of complex geometries. It may be useful for a preliminary dose assessment with user-friendly interfaces and a package approach. SIGMA II is able to obtain from RSICC (Radiation Safety Information Computational Center) as a FOR-TRAN 77 source code. It may be suitable for either parametric preliminary design or detailed final design, e.g. a manned flight or radiation-sensitive component configuration design. It needs some debugs, recompiling and a tedious work to make geometrical quadric surfaces for actual spacecraft configuration, and has poor documentation. It is recommend to vist RSICC homepage and GEANT4/SSAT homepage.

• Journal of Astronomy and Space Sciences
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• 제31권1호
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• pp.73-81
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• 2014

A package of space science instruments, dubbed the Instruments for the Study of Space Storms (ISSS), is proposed for the Next Generation Small Satellite-1 (NEXTSat-1), which is scheduled for launch in May 2016. This paper describes the instrument designs and science missions of the ISSS. The ISSS configuration in NEXTSat-1 is as follows: the space radiation monitoring instruments consist of medium energy particle detector (MEPD) and high energy particle detector (HEPD); the space plasma instruments consist of a Langmuir probe (LP), a retarding potential analyzer (RPA), and an ion drift meter (IDM). The space radiation monitoring instruments (MEPD and HEPD) measure electrons and protons in parallel and perpendicular directions to the geomagnetic field in the sub-auroral region, and they have a minimum time resolution of 50 msec for locating the region of the particle interactions with whistler mode waves and electromagnetic ion cyclotron (EMIC) waves. The MEPD measures electrons and protons with energies of tens of keV to ~400 keV, and the HEPD measures electrons with energies of ~100 keV to > ~1 MeV and protons with energies of ~10 MeV. The space plasma instruments (LP, RPA, and IDM) observe irregularities in the low altitude ionosphere, and the results will be compared with the scintillations of the GPS signals. In particular, the LP is designed to have a sampling rate of 50 Hz in order to detect these small-scale irregularities.

• Journal of Astronomy and Space Sciences
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• 제18권2호
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• pp.163-173
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• 2001

본 논문에서는 아리랑 2호가 운용될 궤도의 우주방사능 환경 및 single event 영향(SEE)에 관하여 분석하였다. 위성체 외부 및 내부 방사능 환경으로서 지구 자기장 내부에 포획되어 활동하는 포획된 양자, 태양 및 태양계 외부에서 전달되는 SEP(solar energetic particle) 및 GCR(galactic cosmic ray)고 에너지 입자에 대하여 양자와 중이 온으로 구분하여 그들의 스펙트럼을 분석하였다. 아리랑 2호 전자소자로 사용 예정인 Intel 계열 80386 마이크로 프로세서 CPU에 대한 SEU 및 SEL발생률을 추정하였다. 분석결과, 정상적인 조건에서 포획된 양자나 고 에너지 양자에 의한 SEU 영향은 아리랑 2호 위성이 운용되는 3년동안 발생하지 않을 것으로 추정된다. 반면에, GCR 중이온에 의한 SEU 발생은 운용 중에 수차례 발생할 수 있는 것으로 추정되었다. 아리랑 2호는 탑재 소프트웨어의 프로세서 CPU오류 감지기능을 이용하여 SEU발생에 대처할 수 있는 시스템 레벨의 설계를 반영하고 있다.