2022/04/06 更新

キム サンキュン
金 相均
KIM Sangkyun
Scopus 論文情報  
総論文数: 0  総Citation: 0  h-index: 4

Citation Countは当該年に発表した論文の被引用数

所属
先端研究・社会連携本部 革新的宇宙利用実証ラボラトリー
職名
特任准教授
研究室住所
福岡県北九州市戸畑区仙水町1-1
外部リンク

取得学位

  • 東京大学  -  博士(工学)   2009年09月

学内職務経歴

  • 2022年04月 - 現在   九州工業大学   先端研究・社会連携本部   革新的宇宙利用実証ラボラトリー     特任准教授

  • 2020年09月 - 2022年03月   九州工業大学   革新的宇宙利用実証ラボラトリー     特任准教授

  • 2020年04月 - 2020年08月   九州工業大学   革新的宇宙利用実証ラボラトリー     研究職員

  • 2019年04月 - 2020年03月   九州工業大学   大学院工学研究院   宇宙システム工学研究系     助教

  • 2017年10月 - 2019年03月   九州工業大学   大学院工学研究院   先端機能システム工学研究系     助教

  • 2016年05月 - 2017年09月   九州工業大学   宇宙環境技術ラボラトリー     助教

▼全件表示

論文

  • New star identification algorithm using labelling technique 査読有り

    Kim S., Cho M.

    Acta Astronautica   162   367 - 372   2019年09月

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    担当区分:筆頭著者   記述言語:英語   掲載種別:研究論文(学術雑誌)

    © 2019 IAA A new star identification algorithm is proposed for the attitude determination of a star sensor in the lost-in-space case, where prior attitude information is not available. The algorithm is based on a labelling technique, which uses label values to represent each group of stars. Using label values, multiple stars are simultaneously identified without repetition of search work. This labelling algorithm allows for a fast identification speed with efficiency, and provides the capability of more reliable identification by redundant confirmation. The proposed algorithm was verified by simulation study under various conditions.

    DOI: 10.1016/j.actaastro.2019.06.007

    Scopus

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  • AOBA VELOX-IV: 2U CubeSat for the technological demonstration of lunar horizon glow mission 査読有り

    Kim S., Orger N., Cordova-Alarcon J., Hernandez-Herrera M., Masui H., Yamauchi T., Toyoda K., Cho M., Duy Vu B., Vinh T., Seng L., Hiang C.

    Acta Astronautica   161   328 - 337   2019年08月

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    担当区分:筆頭著者   記述言語:英語   掲載種別:研究論文(学術雑誌)

    © 2019 IAA AOBA VELOX-IV is a 2U-sized CubeSat that has been developed by the Kyushu Institute of Technology and Nanyang Technological University for the technological demonstration of a future lunar mission. Decades ago, Surveyor and Apollo programs reported light scattering observations on the horizon of the Moon; however, only a limited number of investigations were performed after the Apollo program to observe the lunar horizon glow (LHG). It is still unknown what conditions produce the light glow on the horizon of the Moon. The lunar mission of the AOBA VELOX project is planning to send CubeSats to the Moon and to capture images of the LHG on the lunar orbit while determining the conditions that can support light scattering above the lunar horizon. Before the satellites go into the lunar orbit, the necessary technologies must first be confirmed in Earth orbit. AOBA VELOX-IV was launched to low earth orbit via a JAXA Epsilon rocket in 18th January 2019. This paper explains the LHG mission first, and presents an overview of AOBA VELOX-IV, its payloads, technical issues, and the flight model.

    DOI: 10.1016/j.actaastro.2019.05.046

    Scopus

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  • Analysis of lifetime extension capabilities for CubeSats equipped with a low-thrust propulsion system for Moon missions 査読有り

    Cordova Alarcon J., Orger N., Kim S., Cho M.

    Acta Astronautica   160   558 - 571   2019年07月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)

    © 2019 IAA In this paper, we analyze the mission lifetime extension capability for a CubeSat smaller than 3U in a circular lunar orbit at a 100-km altitude, assuming the utilization of a state-of-the-art low-thrust electric propulsion system such as pulsed plasma thrusters with an impulse bit (Ibit)and velocity change (ΔV)below 60 μNs and 120 m/s, respectively. Because of the non-spherical gravity field of the Moon and its strong influence on low-altitude lunar orbits, a long orbital lifetime is achievable only within a set of stable orbits which mainly depends on initial inclination and right ascension of the ascending node (RAAN); moreover, as a piggyback on a main mission, the deployment of CubeSats in those stable orbits is not guaranteed. For this reason, we propose an orbit correction strategy whose performance is constrained to the initial orbital parameters of the CubeSat (i.e., inclination and RAAN), its solar power generation capacity, its attitude control strategy, and its propulsion subsystem features, such as the thruster Ibit and budgeted ΔV. By analyzing the required time to perform the orbit correction maneuvers to extend the orbital lifetime and the minimum altitude achieved throughout the mission lifetime of the spacecraft, we demonstrated that a one-year mission can be achieved within initial orbital inclination values greater than 65°. For unstable orbits bounded by initial orbital inclination values smaller than 65°, the orbit lifetime can also be extended from a few days to up to one year. Better performance with our proposed orbit correction strategy can be achieved by using an electric propulsion system featuring Ibit and ΔV values greater than 40 μNs and 80 m/s, respectively. Our results show the feasibility of performing any orbit correction maneuver for the enhancement of the mission lifetime of a CubeSat, expanding the performance capabilities of CubeSats to any mission in a lunar orbit by reducing the limitation of deploying them in unstable orbits.

    DOI: 10.1016/j.actaastro.2018.11.040

    Scopus

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  • CubeSat bus interface with Complex Programmable Logic Device 査読有り

    Tumenjargal T., Kim S., Masui H., Cho M.

    Acta Astronautica   160   331 - 342   2019年07月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)

    © 2019 IAA A standardized interface for different CubeSat missions is one of the keys to reducing costs and delivery time. A backplane interface approach, proposed by the University of Würzburg in Germany as UWE-3, was implemented in three CubeSat projects at the Kyushu Institute of Technology (Kyutech) to shorten the development and assembly times. The backplane approach also helped to reduce the risk of workmanship errors associated with the harness. However, changes to the proposed standard interface board were necessary in every CubeSat project, to comply with the mission requirements. To obtain more flexibility, especially for data connections, this work introduces a novel idea of a software-configurable bus interface with a backplane board. A Complex Programmable Logic Device (CPLD) was used instead of hardware routing so that we can reconfigure the bus interface by reprogramming the CPLD. The concept was validated by a functional test with a breadboard module. A radiation test verified that the selected CPLD has enough strength to survive total ionization doses of more than 2 years in low Earth orbit. A new backplane board with CPLD has been integrated into the engineering model of the fourth CubeSat project at Kyutech, the BIRDS-3 project, and system level verification has been conducted.

    DOI: 10.1016/j.actaastro.2019.04.047

    Scopus

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  • Design, Analysis and Testing of Monopole Antenna Deployment Mechanism for BIRDS-2 CubeSat Applications 査読有り

    Zaki S., Azami M., Yamauchi T., Kim S., Masui H., Cho M.

    Journal of Physics: Conference Series   1152 ( 1 )   2019年03月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    © Published under licence by IOP Publishing Ltd. This paper presents an approach to design a feasible and reliable monopole antennae deployment mechanism for CubeSat applications. Nano-satellite has faced problems in designing antennae deployment system due to space and deployment mechanism constraints. In BIRDS-2 CubeSat, the nichrome wire burning release mechanism was used when activated, it will be heated up and thermally cut through fishing line, allowing the two monopole antennas to be deployed on +Y board and at +Z axis direction of the satellite. These antennae involved amateur radio frequencies in UHF and VHF bands due to its low cost and high accessibility by the end users. The UHF frequency band was used for command uplink, mission, telemetry, and CW beacon downlink whilst the VHF frequency band was used specifically for APRS-DP/S&F-RDC mission for both uplink and downlink. In order to achieve the effectiveness of the BIRDS-2 CubeSat communication system agreed with the link budget estimation, the dimensions of antennae on the CubeSat structure depend on the required gain and operating frequency. The paper discusses detailed results of mechanical and electrical interfaces of the two monopole antennas deployment mechanism with the satellite body and the nichrome wire burning release mechanism analysis. The tests results of the mechanism were analyzed particularly on the deployment time and the nichrome wire temperature differences.

    DOI: 10.1088/1742-6596/1152/1/012007

    Scopus

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  • BIRDS-2: A Constellation of Joint Global Multi-Nation 1U CubeSats 査読有り

    Azami M., Maeda G., Faure P., Yamauchi T., Kim S., Masui H., Cho M.

    Journal of Physics: Conference Series   1152 ( 1 )   2019年03月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    © Published under licence by IOP Publishing Ltd. BIRDS-2, the second generation of the Joint Global Multi-Nation Birds (JGMNB) project is a constellation of 1U CubeSats from Laboratory of Spacecraft Environment Interaction Engineering (LaSEINE), Kyushu Institute of Technology, Japan. The BIRDS-2 project consists of three identical 1U built by a group of students from four nations; Japan, Malaysia, Philippines, and Bhutan. It consists of 6 missions; Camera, Automatic Radio Packet Service-Digipeater (APRS-DP), Store and Forward (S&F), COTS GPS, Anisotropic Magneto Resistance Magnetometer (AMR-MM), and detection of single-event latch-up (SEL). The objective of BIRDS-2 is to provide an opportunity to learn the entire satellite system cycle, to lay down the foundation of the sustainable space program, and to create international networks of the ground station to assist the infant space program of the participating country. A total of 11 members learns the satellite development in a lean concept of 30m radius of the work area. The paper will describe the bus system of the BIRDS-2 CubeSats and the development process throughout the one year and three months of the project timeline. Completion of BIRDS-2 flight models remarks the successful design of the CubeSats bus system and waiting for the launch and deploy from International Space Station (ISS) around 3rd quarter of this year.

    DOI: 10.1088/1742-6596/1152/1/012008

    Scopus

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  • Ionosphere observation and 3D mapping mission via CubeSat constellation; in-orbit operation results of the SPATIUM-I CubeSat 査読有り

    Aheieva K., Rahmatillah R., Ninagawa R., Adebolu I., Kim S., Kakimoto Y., Nakayama D., Kishimoto M., Elmegharbel H., Yamauchi T., Masui H., Cho M., Lap C., Ying Z., Siu T., Holden L.

    Proceedings of the International Astronautical Congress, IAC   2019-October   2019年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. This paper will describe the progress in the SPATIUM satellite project, developed to do the global three-dimensional ionosphere mapping via CubeSat constellation equipped with an atomic clock and will show the result of the on-orbit operation of about 1 year of the first path-finder satellite SPATIUM-I. The SPATIUM-I satellite, launched in October 2018, validated the key technologies that are based on the clock-signal phase-shift sent from the satellite carried Chip-Scale Atomic Clock (CSAC). The satellite did the on-orbit demonstration of Chip Scale Atomic Clock (CSAC) as well as the evaluation of the signal time delay due to ionosphere and atmosphere. SPATIUM-I satellite on-orbit operation results will be presented. Knowing the precise satellite location and the signal delay from each satellite that transmits the signal with two UHF frequencies, by solving the inverse problem we can derive the ionosphere density and atmosphere water vapor. This data can be used to improve the accuracy of the earth and space weather forecast. This concept will then be implemented for the evaluation of Ionosphere Observation and Ionosphere 3D mapping via SPATIUM-II and SPATIUM-III projects. The SPATIUM project is under development by the Laboratory of Spacecraft Environmental Interaction Engineering (LaSEINE) of Kyushu Institute of Technology in collaboration with Nanyang Technological University, Singapore.

    Scopus

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  • How seven emerging nations entered the space age via BIRDS Projects 1 through 4 査読有り

    Maeda G., Cho M., Masui H., Kim S., Yamauchi T.

    Proceedings of the International Astronautical Congress, IAC   2019-October   2019年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. Operating on the basis that "one cannot learn how to build satellites by reading books", Kyushu Institute of Technology (Kyutech) launched its BIRDS Project in 2015 with Ghana, Bangladesh, Mongolia, Nigeria, and Japan. The main purpose was to help most of them launch their first satellites, and then somehow make satellite development sustainable in their own countries after the return of their students. Subsequently, Kyutech started BIRDS-2 in 2016, BIRDS-3 in 2017, and BIRDS-4 in 2018, involving the nations of Bhutan, Malaysia, Philippines, Nepal, Sri Lanka, and Paraguay. BIRDS-5 will start in October of 2019. In this paper we discuss the various capacity building results in these countries. We believe the seeds have been sown in these countries for sustained national space development via the activities of launching their first satellites - a crucial step. The seven nations who did (or are doing) their first satellites are: (1) Ghana, (2) Bangladesh, (3) Mongolia, (4) Bhutan, (5) Nepal, (6) Sri Lanka, and (7) Paraguay. Every nation participating in BIRDS pays its own way - there are no subsidies from Japan. They end up with their first space borne satellites but much more importantly they have engineers who know how to build a CubeSat.

    Scopus

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  • BIRDS-3 satellite project including the first satellites of Sri Lanka and Nepal 査読有り

    Chamika W.D., Cho M., Maeda G., Kim S., Masui H., Yamauchi T., Panawannege S., Shrestha S.B.

    Proceedings of the International Astronautical Congress, IAC   2019-October   2019年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. The Joint Global Multi-National Birds also known as BIRDS, is a multinational small satellite program led by Kyushu Institute of Technology (Japan). BIRDS program gives opportunity to non-space fairing nations to design, integrate, build, test, launch and operate their nation's first satellite. This paper focuses on BIRDS-3 which is the third batch under BIRDS program. BIRDS-3 is a constellation of three 1U CubeSats belonging to Japan (Uguisu), Nepal (NepaliSat-1: Nepal's first satellite) and Sri Lanka (Raavana-1: Sri Lanka's first satellite). BIRDS-3 has two members (students) from Nepal, three from Japan, and two from Sri Lanka and one from Bhutan. These students have been enrolled in Space Engineering International Course (SEIC) in Kyushu Institute of Technology. External dimensions of one satellite is 113.5mm x 100mm x 100mm and the weight is approximately 1.05kg. This constellation executes four missions: Imaging Mission (CAM), Attitude Determination and Control System mission (ADCS), LoRa Demonstration Mission (LDM), Software Configurable Backplane Board Mission (BPB). The CubeSats were deployed to the orbit on 17th June 2019 from International Space Station (ISS). After deployment CubeSats are being operated through BIRDS ground station network. This paper describes the background, missions, stakeholders and initial operational results after the deployment from International Space Station (ISS).

    Scopus

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  • Validation of double Langmuir probe in-orbit performance onboard a nano-satellite 査読有り

    Tejumola T., Zarate Segura G., Kim S., Khan A., Cho M.

    Acta Astronautica   144   388 - 396   2018年03月

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    記述言語:英語   掲載種別:研究論文(学術雑誌)

    © 2018 IAA Many plasma measurement systems have been proposed and used onboard different satellites to characterize space plasma. Most of these systems employed the technique of Langmuir probes either using the single or double probes methods. Recent growth of lean satellites has positioned it on advantage to be used for space science missions using Langmuir probes because of its simplicity and convenience. However, single Langmuir probes are not appropriate to be used on lean satellites because of their limited conducting area which leads to spacecraft charging and drift of the instrument's electrical ground during measurement. Double Langmuir probes technique can overcome this limitation, as a measurement reference in relation to the spacecraft is not required. A double Langmuir probe measurement system was designed and developed at Kyushu Institute of Technology for HORYU-IV satellite, which is a 10 kg, 30 cm cubic class lean satellite launched into Low Earth Orbit on 17th February 2016. This paper presents the on-orbit performance and validation of the double Langmuir probe measurement using actual on-orbit measured data and computer simulations.

    DOI: 10.1016/j.actaastro.2018.01.016

    Scopus

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  • Star selection algorithm for arcsecond pico star tracker 査読有り

    Muruganandan V., Park J., Lee S., Jeung I., Kim S., Ju G.

    AIAA Aerospace Sciences Meeting, 2018   ( 210059 )   2018年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. This paper describes the algorithm development of Arcsecond Pico Star Tracker (APST) at Seoul National University. The pico star tracker is developed using COTS because it’s affordable, and less development time. But COTS component decreases the overall performance. In APST, the lens distortion increases the measurement error which causes misidentification of stars and higher processing time for star identification. To overcome this, the relative star selection algorithm is developed which selects the stars with less measurement error and it’s compared with conventional bright star selection method. The selection algorithm is tested with 75-star constellation in the simulator and it has delivered 100% success rate and accuracy of 71 arcseconds in boresight with average processing time of 22 ms. Whereas the conventional bright star selection delivered low success rate of 28% because it selects the stars only based on brightness and processing time increases as a number of stars in the FOV increases. Hence the relative star selection algorithm is efficient for APST.

    DOI: 10.2514/6.2018-2199

    Scopus

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  • Design, development, testing and on-orbit performance results of a low-cost store-and-forward payload onboard a 1u cubesat constellation for remote data collection applications 査読有り

    Salces A., Zaki S., Kim S., Masui H., Cho M.

    Proceedings of the International Astronautical Congress, IAC   2018-October   2018年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    Copyright © 2018 by the International Astronautical Federation. As a technology demonstration mission of the three-member 1U CubeSat constellation of the joint global multi-nation BIRDS-2 Project, the store-and-forward (S&F) mission aims to demonstrate the potential use of a 1U CubeSat constellation for collecting data from ground sensor terminals deployed in remote or isolated sites. The three CubeSats are the first university CubeSats of Bhutan, Malaysia, and the Philippines. Their onboard S&F payloads collect various sensor data from experimental ground terminals deployed in respective home countries. Although a CubeSat constellation is an attractive platform for the said application - due to its substantially simpler design, lower cost, and faster development time - it also presents many technical challenges such as tight size, power, and communication link budgets. In this paper, first, the design considerations and implementation of our onboard S&F payload are discussed. The said payload operates in the VHF amateur band and consists of mostly very low-cost commercial-of-the-shelf components. Sensor data uplink is done at 1200 bps and gathered data downlink at 9600 bps through the UHF communication subsystem. Then, the investigation and test results are presented, including link budget analysis, communication tests, antenna deployment tests, and space environment tests. Finally, the initial on-orbit performance results within one month of satellites' operation in space are tackled.

    Scopus

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  • Project overview of SAPTIUM-I; a technology demonstration mission toward global three-dimensional ionosphere mapping via cubesat constellation equipped with an atomic clock 査読有り

    Aheieva K., Rahmatillah R., Ninagawa R., Adebolu I., Kim S., Kakimoto Y., Yamauchi T., Masui H., Cho M., Lap C., Ying Z., Siu T., Holden L.

    Proceedings of the International Astronautical Congress, IAC   2018-October   2018年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    Copyright © 2018 by the International Astronautical Federation. Many satellites already measured ionosphere density in LEO region and still this information is not enough to create a global 3D ionosphere map. The ionosphere constantly fluctuates in a global scale, which is a complication in the process of its re-creation. To improve and validate ionosphere numerical models, measurements taken by the individual satellite are used. To measure the total electron content (TEC), and have higher spatial and temporal resolution, higher accuracy and lower cost in comparison to Global Navigation Satellite System (GNSS), we propose a CubeSat constellation. With 1000 satellites on the different orbital planes in LEO, we can have spatial resolution of 15 km and a temporal resolution of 30 minutes. And the electron density distribution will be known by the solving the inverse problem from many observation provided by the constellation. The first pathfinder satellite, SPATIUM-I, is under development and will be launched in 2018. SPATIUM-I will validate the key technologies that are based on the clock-signal phase-shift sent from the satellite carried Chip-Scale Atomic Clock (CSAC). The project is under development by the Laboratory of Spacecraft Environmental Interaction Engineering (LaSEINE) of Kyushu Institute of Technology in collaboration with Nanyang Technological University, Singapore. This paper will present the status of SPATIUM-I development and the overview of the follow-on projects, SPATIUM-II and SPATIUM-III.

    Scopus

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  • Challenges for CubeSats safety design and verification to do lean satellite development 査読有り

    Cho M., Yamauchi T., Faure P., Kim S., Masui H.

    Proceedings of the International Astronautical Congress, IAC   2018-October   2018年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    © 2018 by the International Astronautical Federation (IAF). All rights reserved. Every satellite, regardless of its size, mission, value, capability or any other nature, shall comply with safety requirements. This statement applies even to a 1U or less CubeSat. The recent diversity in the CubeSat launch options, however, has brought complication in satellite design and verification. The safety requirements differ among the launch vehicles. The difference is particularly significant between the rocket launch and the ISS release. Satellite developers need to consider how to adapt their design to various safety requirements and how to verify their compliance from the early stage of satellite development, even before they decide on the launch option. Kyushu Institute of Technology (Kyutech) has operated Centre for Nanosatellite Testing (CeNT) in Laboratory of Spacecraft Environment Interaction Engineering (LaSEINE) since 2010. Those satellites that employed commercial-off-the-shelf (COTS) CubeSat components available on Internet had many safety-related issues to be resolved. Kyutech itself has developed 12 satellites that were launched by rockets or released from ISS and experienced various issues related to safety. The safety issues encountered by various CubeSats for various launch options are reviewed. How they were resolved with are introduced with suggestions on how to minimize the troubles that delay the satellite delivery time.

    Scopus

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  • CubeSat mission for ionosphere mapping and weather forecasting using chip-scale atomic clock 査読有り

    Aheieva K., Rahmatillah R., Ninagawa R., Adebolu I., Masui H., Yamauchi T., Kim S., Cho M., Chow C., Tse M., Li K.

    Progress in Electromagnetics Research Symposium   2017-November   761 - 766   2017年11月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    © 2018 Electromagnetics Academy. All rights reserved. The project SPATIUM (Space Precision Atomic-clock TIming Utility Mission) presents a new technique for ionosphere mapping using a constellation of CubeSats equipped with Chip Scale Atomic Clock (CSAC) to provide real-time three-dimensional mapping of ionosphere plasma density at the altitudes of electron density peak (200 to 400km above the Earth). This paper describes the principle of the ionosphere mapping and total electron content (TEC) determination using satellite signal transmission with a dual-frequency and signal shift determination at the Ground Station using the same referenced CSAC clock. The paper also describes reasons of RF signal delays/shifting due to atmosphere and ionosphere plasma conditions. A 2U CubeSat, SPATIUM-I, is introduced as a platform. The future plans for the project expansion are also given.

    DOI: 10.1109/PIERS-FALL.2017.8293237

    Scopus

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  • Development of the Arcsecond Pico Star Tracker (APST) 査読有り

    Muruganandan V., Park J., Lee S., Jeung I., Kim S., Ju G.

    Transactions of the Japan Society for Aeronautical and Space Sciences   60 ( 6 )   355 - 365   2017年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    © 2017 The Japan Society for Aeronautical and Space Sciences. The second-generation star tracker estimates pointing knowledge of a satellite without a-priori knowledge. But star trackers are larger in size, heavier, power hungry and expensive for nanosatellite missions. The Arcsecond Pico Star Tracker (APST) is designed based on the limitations of nanosatellites and estimated to provide pointing knowledge in an arcsecond. The APST will be used on the SNUSAT-2, Earth-observing nanosatellite. This paper describes the requirements of APST, trade-off for the selection of image sensor, optics, and baffle design. In addition, a survey of algorithms for star trackers and a comparison of the specifications of APST with other Pico star trackers are detailed. The field of view (FOV) estimation shows that 17° and 22° are suitable for APST and this reduces stray light problems. To achieve the 100% sky coverage, the FOV of 17° and 22° should able to detect the 5.85 and 5.35 visual magnitude of stars, respectively. It is validated by estimating the signal to noise ratio of APST and night sky test results. The maximum earth stray light angle is estimated to be 68° and a miniaturized baffle is designed with the exclusion angle of 27°.

    DOI: 10.2322/tjsass.60.355

    Scopus

    その他リンク: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85032748630&origin=inward

  • Aoba Velox-IV attitude and orbit control system design for a LEO mission applicable to a future lunar mission 査読有り

    Cordova-Alarcon J., Örger N., Kim S., Soon L., Cho M.

    Proceedings of the International Astronautical Congress, IAC   2016年01月

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    記述言語:英語   掲載種別:研究論文(国際会議プロシーディングス)

    Copyright © 2016 by the International Astronautical Federation (IAF). All rights reserved. Aoba VELOX-IV is a 2U-Cubesat which will serve as a platform for technology validation towards a future lunar mission for the observation of lunar horizon glow (LHG). LHG was first spotted in 1966 and 1968 by onboard cameras on Surveyor spacecraft after the sunset from the western horizon, and Apollo astronauts reported that they had seen the horizon glow. Even though the horizon glow was highly visible in the Apollo 15 sunset, Apollo 16 showed no traces of the horizon glow, proving that it is a highly varying phenomenon. Nanyang Technological University (NTU Singapore) is collaborating with Kyushu Institute of Technology (Kyutech), to build Aoba VELOX-IV, which will be launched by Japan's national agency, the Japan Aerospace Exploration Agency (JAXA) in 2018. Though its AOCS scheme is designed to meet the requirements for a low-Earth-orbit (LEO) mission, it can be directly applicable to a lunar mission. This paper is dedicated to the description of the design and analysis of a AOCS to meet these requirements. Because of dimension restrictions, the satellite attitude is two-axis controlled. The hardware of AOCS consists on Sun sensors, gyroscope, reaction wheels and pulsed plasma thrusters (PPT). Satellite position, velocity and time will be determined by a ground station and the satellite will propagate them until the next revisit. Based on PPT thrusters, the AOCS will desaturate RW during attitude control maneuvers for the pointing towards Earth horizon in such a way that the satellite can observe sunrise and sunset. In eclipse phase, the satellite is required to know its attitude by means of Kalman filtering to observe the sunrise. The geometry configuration of PPT will allow the extension of the satellite mission lifetime while desaturation of RW and while the satellite is visible to the ground station.

    Scopus

    その他リンク: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85016465553&origin=inward

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