• Journal of Astronomy and Space Sciences
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• v.32 no.3
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• pp.257-268
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• 2015

Characteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the moon with a circular orbit at a 90 deg inclination and having 50, 100, 150, 200 km altitudes. Critical design parameters that are directly related to the success of the impactor mission are also analyzed including deploy directions, CubeSat flight time, impact velocity, and associated impact angles. Based on derived delta-V requirements, required thruster burn time and fuel mass are analyzed by adapting four different miniaturized commercial onboard thrusters currently developed for CubeSat applications. As a result, CubeSat impact trajectories as well as thruster burn characteristics deployed at different orbital altitudes are found to satisfy the mission objectives. It is concluded that thrust burn time should considered as the more critical design parameter than the required fuel mass when deducing the onboard propulsion system requirements. Results provided through this work will be helpful in further detailed system definition and design activities for future lunar missions with a CubeSat-based payload.

• Journal of the Ergonomics Society of Korea
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• v.32 no.1
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• pp.107-115
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• 2013

Objective: The aim of this study is to identify the training requirements of new nuclear power plant by a comprehensive literature review. Background: The design of instrumental and control systems for New NPP is applied fully digitalized systems. For example, soft-control, large display panels(LDP), and an advanced alarm system were applied to the APR-1400 or SMART. Method: The NUREG-0711 and international guideline of training program was analyzed from the following four phases of SAT(Systemic Approach to Training): Analysis, Design, Development, Implementation and Evaluation. Results: To identify the requirement of training program, 'Feedback' phase was considered and each phase of SAT was classified. Conclusion: A more systematic requirement of training program is needed which considers the computerized system was applied to the new NPP. Application: The results of the publishing can be useful for standardization of the systematic training program for the operators of NPP.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1222-1228
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• 2008

A small satellite, DubaiSat-1 FM(Flight Model), which is based on SI-200 standard bus platform and scheduled to be launched in 2008, is being developed by Satrec Initiative and EIAST(Emirates Institution for Advanced Science and Technology). The TCS(Thermal Control Subsystem) of DubaiSat-1 FM has been designed to mainly utilize passive thermal control in order to minimize power consumption, but the active control method using heaters has been applied to some critical parts. Also, thermal analysis has been performed for DubaiSat-1's mission orbit using a thermal analysis model. The thermal design is modified and optimized to satisfy the design temperature requirements for all parts according to the analysis result. The thermal control performance of DubaiSat-1 FM is verified by thermal vacuum space simulation, consisting of thermal cycling and thermal balance test. Also, to validate the thermal modeling of DubaiSat-1 FM, comparison of test results with analysis has been performed and model calibration has been completed.

• International Journal of Contents
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• v.10 no.3
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• pp.41-46
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• 2014

A cause-effect graph considers only the desired external behavior of a system by identifying input-output parameter relationships in the specification. When testing a software system with cause-effect graphs, it is important to derive a moderate number of tests while avoiding loss in fault detection ability. Pairwise testing is known to be effective in determining errors while considering only a small portion of the input space. In this paper, we present a new testing technique that generates pairwise tests from a cause-effect graph. We use a Boolean Satisbiability (SAT) solver to generate pairwise tests from a cause-effect graph. The Alloy language is used for encoding the cause-effect graphs and its SAT solver is applied to generate the pairwise tests. Using a SAT solver allows us to effectively manage constraints over the input parameters and facilitates the generation of pairwise tests, even in the situations where other techniques fail to satisfy full pairwise coverage.

• Journal of Aerospace System Engineering
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• v.6 no.4
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• pp.34-39
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• 2012

CubeSats classified as pico-class satellite require a ground station to track the satellite, transmit a command, and receive an on-orbit data such as SOH (State-of-Health) and mission data according to the operation plan. For this, ground station system has to be properly designed to perform a communication to with the satellite with enough up- and down-link budgets. In this study, a conceptual design of the ground station has been performed for the CubeSat named as STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project). The paper includes a ground station hardware interface design, link budget analysis and a ground station software realization. In addition, the operation plan of the ground station has been established considering the STEP Cube Lab. mission requirements.

• Journal of Astronomy and Space Sciences
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• v.37 no.4
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• pp.219-228
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• 2020

A CubeSat platform has become a popular choice due to inexpensive commercial off-the-shelf (COTS) components and low launch cost. However, it requires more power-efficient and higher-data rate downlink capability for space applications related to remote sensing. In addition, the platform is limited by the size, weight and power (SWaP) constraints as well as the regulatory issue of licensing the radio frequency (RF) spectrum. The requirements and limitations have put optical communications on promising alternatives to RF communications for a CubeSat platform, owing to the power efficiency and high data rate as well as the license free spectrum. In this study, we analyzed the performance of optical downlink communications compatible with CubeSat platforms in terms of data rate, bit error rate (BER) and outage probability. Mathematical models of BER and outage probability were derived based on not only the log-normal model of atmospheric turbulence but also a transmitter with a finite extinction ratio. Given the fixed slot width, the optimal guard time and modulation orders were chosen to achieve the target data rate. And the two performance metrics, BER and outage data rate, were analyzed and discussed with respect to beam divergence angle, scintillation index and zenith angle.

• Journal of IKEEE
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• v.25 no.2
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• pp.350-355
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• 2021

IGBT is a power semiconductor device that contains both MOSFET and BJT structures, and it has fast switching speed of MOSFET, high breakdown voltage and high current of BJT characteristics. IGBT is a device that targets the requirements of an ideal power semiconductor device with high breakdown voltage, low V_CE-SAT, fast switching speed and high reliability. In this paper, we analyzed Gate oxide thickness, Trench Gate Width, and P+Emitter width, which are the top process parameters of 1,200V Trench Gate Field Stop IGBT, and suggested the optimized top process parameters. Using the Synopsys T-CAD Simulator, we designed IGBT devices with electrical characteristics that has breakdown voltage of 1,470 V, V_CE-SAT 2.17 V, Eon 0.361 mJ and Eoff 1.152 mJ.

• Journal of Aerospace System Engineering
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• v.16 no.6
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• pp.81-89
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• 2022

This study measured the radio environment of 10 domestic institutions with CubeSat ground stations for 24 hours in three frequency bands (VHF/UHF/S-band) allocated by the International Telecommunication Union (ITU). The impact of the RF environment around the ground stations on CubeSat downlink frequencies was analysed and compared with acceptable interference noise requirements from the CubeSat RF link. The findings indicate that not only the selection of downlink frequency but also the configuration of RF communication link design and ground station system of CubeSat should consider the S-band RF environment around the ground station due to the presence of several wireless devices.

• Journal of Advanced Navigation Technology
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• v.27 no.6
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• pp.782-787
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• 2023

Korea augmentation satellite system (KASS) integration, verification, qualification (IVQ) activity is verification of requirements for KASS system and its sub-system that were performed based on the inspection, analysis, review of design, test (IART) method from factory acceptance test (FAT) to test readiness review (TRR) after critical design review (CDR) was closed. In the FAT phase, developed equipment was installed on the test platform and we were verified interfaces between sub-systems and coupling test with the kass control station (KCS). In the site aceeptance test (SAT) phase, on-site verification was conducted by installing equipment verified by FAT such as kass reference station (KRS), kass processing station (KPS), kass uplink station (KUS), KCS. However, considering the developed plan and status, SAT was divided into 3 phases and coupling test was performed. In the TRR phase, the KASS system verification was performed through FAT's test list and additional test list using the satellite based augmentation system (SBAS) broadcast signal from geostationary earth orbit (GEO) 1.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.37-42
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• 2015

The CubeSats is classified as a pico-class satellite which requires a ground station to track the satellite, transmit commands, and receive an on-orbit data such as SOH (State-of-Health) and mission data according to the operation plan. In order to this, the ground station system has to be properly designed to perform a communication to with the satellite with enough up- and down-link budgets. In this study, a conceptual design of the ground station has been performed for the CubeSat named as STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project). The paper includes a ground station hardware interface design, a link budget analysis and a ground station software realization. In addition, the operation plan of the ground station has been established considering the STEP Cube Lab. mission requirements.