Measurement of change in properties of PCB for the irradiation of Co-60 gamma-ray for space application of CCGA484 daisy chain FPGA device

Shin, Goo-Hwan; Seo, Jeong-Ki; Park, Hong-Yong; Ryu, Kwang‐Sun; Lee, In; Song, Jin-Hwan

doi:10.3938/jkps.63.1451

Cited by 3 publications

(2 citation statements)

References 5 publications

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“…The Interagency Operations Advisory Group (IOAG) had tried to communicate through relay communications at Mars via ultrahigh frequency (UHF) to explore the deep space (Edwards et al 2011) with the Astrophysics Laboratory (INTEGRAL) has provided an overview of the mission operations concept to obtain the science data, and is dedicated to the fine spectroscopy (Dreger et al 1999). In addition, the operational mode was considered with the space radiation effects on FPGA (Shin et al 2013). With the operational mode and concept, the required battery capacity and solar array capacity are calculated by the consumption of the electrical energy.…”

Section: Resultsmentioning

confidence: 99%

Operational Concept of the NEXTSat-1 for Science Mission and Space Core Technology Verification

Shin¹,

Chae²,

Lee³

et al. 2014

Journal of Astronomy and Space Sciences

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The next generation small satellite-1 (NEXTSat-1) program has been kicked off in 2012, and it will be launched in 2016 for the science missions and the verification of space core technologies. The payloads for these science missions are the Instrument for the Study of Space Storms (ISSS) and NIR Imaging Spectrometer for Star formation history (NISS). The ISSS and the NISS have been developed by Korea Advanced Institute of Science and Technology (KAIST) and Korea Astronomy and Space science Institute (KASI) respectively. The ISSS detects plasma densities and particle fluxes of 10 MeV energy range near the Earth and the NISS uses spectrometer. In order to verify the spacecraft core technologies in the space, the total of 7 space core technologies (SCT) will be applied to the NEXTSat-1 for space verification and those are under development. Thus, the operation modes for the ISSS and the NISS for space science missions and 7 SCTs for technology missions are analyzed for the required operation time during the NEXTSat-1's mission life time of 2 years. In this paper, the operational concept of the NEXTSat-1's science missions as well as the verification of space core technologies are presented considering constraints of volume, mass, and power after launch.

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Section: Resultsmentioning

confidence: 99%

Operational Concept of the NEXTSat-1 for Science Mission and Space Core Technology Verification

Shin¹,

Chae²,

Lee³

et al. 2014

Journal of Astronomy and Space Sciences

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“…In these missions, the satellite requires sufficient electrical power to satisfy the power requirements in orbit. The electrical power required for satellite operation comes from a solarcell array using high power-conversion efficiency that considers the radiation effects (Shin et al 2008(Shin et al , 2011(Shin et al , 2013. In the present work, we chose a 300-W solar-cell array using GaInP/GaAs/Ge solar cells to generate electrical power by photovoltaic conversion.…”

Section: Introductionmentioning

confidence: 99%

Analysis of Magnetic Dipole Moment for a 300-W Solar-Cell Array

Shin¹,

Kim²,

Kwon³

et al. 2019

Journal of Astronomy and Space Sciences

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The attitude information of spacecraft can be obtained by the sensors attached to it using a star tracker, three-axis magnetometer, three-axis gyroscope, and a global positioning signal receiver. By using these sensors, the spacecraft can be maneuvered by actuators that generate torques. In particular, electromagnetic-torque bars can be used for attitude control and as a momentum-canceling instrument. The spacecraft momentum can be created by the current through the electrical circuits and coils. Thus, the current around the electromagnetic-torque bars is a critical factor for precisely controlling the spacecraft. In connection with these concerns, a solar-cell array can be considered to prevent generation of a magnetic dipole moment because the solar-cell array can introduce a large amount of current through the electrical wires. The maximum value of a magnetic dipole moment that cannot affect precise control is 0.25 A·m2, which takes into account the current that flows through the reaction-wheel assembly and the magnetic-torque current. In this study, we designed a 300-W solar cell array and presented an optimal wire-routing method to minimize the magnetic dipole moment for space applications. We verified our proposed method by simulation.

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Communications Link Design and Analysis of the NEXTSat-1 for SoH File and Mission Data Using CAN Bus, UART and SerDesLVDS

Shin¹,

Chae²,

Min³

et al. 2014

Journal of Astronomy and Space Sciences

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Measurement of change in properties of PCB for the irradiation of Co-60 gamma-ray for space application of CCGA484 daisy chain FPGA device

Cited by 3 publications

References 5 publications

Operational Concept of the NEXTSat-1 for Science Mission and Space Core Technology Verification

Operational Concept of the NEXTSat-1 for Science Mission and Space Core Technology Verification

Analysis of Magnetic Dipole Moment for a 300-W Solar-Cell Array

Communications Link Design and Analysis of the NEXTSat-1 for SoH File and Mission Data Using CAN Bus, UART and SerDesLVDS

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