論文 - 増井　博一

One Year On-Orbit Results of Improved Bus, LoRa Demonstration and Novel Backplane Mission of a 1U CubeSat Constellation 査読有り

MASKEY Abhas, LEPCHA Pooja, SHRESTHA Hari Ram, CHAMIKA Withanage Dulani, MALMADAYALAGE Tharindu Lakmal Dayarathna, KISHIMOTO Makiko, KAKIMOTO Yuta, SASAKI Yuji, TUMENJARGAL Turtogtokh, MAEDA George, KIM Sangkyun, MASUI Hirokazu, YAMAUCHI Takashi, CHO Mengu

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ( 一般社団法人 日本航空宇宙学会 )   65 ( 5 )   213 - 220   2022年01月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

<p>The BIRDS series from Kyushu Institute of Technology has deployed 1U CubeSat constellations from International Space Station since 2017. BIRDS-3 was deployed in June 2019. Lessons learnt from BIRDS-1 and BIRDS-2 have been used to improve the bus system of BIRDS-3. Improvements have been made in On-Board Computer, Electrical Power and Communication systems. BIRDS-3 has implemented novel Backplane Mission which uses SoftCIB; an in-house designed software defined backplane interface board. The mission has the potential to standardize interface and cut down on development time. BIRDS-3 project has placed a LoRa module to check its performance in space. The module has the potential for future low-cost, low-powered Store and Forward mission and CubeSat communication system. This paper provides detailed information on the improved BIRDS bus system, LoRa Demonstration and Backplane Mission designs, and on-orbit results since its deployment in June 2019. The results presented are based on cumulative operation time of three years for three satellites operating each for a year. The satellites are functional and will remain in orbit until summer of 2021.</p>

DOI： 10.2322/tjsass.65.213

CiNii Research

Application of Small Satellites for Low-Cost Remote Data Collection Using LoRa Transmitters 査読有り 国際誌

LEPCHA Pooja, KIM Sankyun, MASUI Hirokazu, CHO Mengu

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN ( 一般社団法人 日本航空宇宙学会 )   19 ( 2 )   224 - 230   2021年01月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

<p>The advancement of small satellites has greatly reduced the overall cost and development time of the satellite compared to conventional satellites fulfilling similar missions. Although there have been many developments on the satellite side, for missions like remote data collection the sensor nodes on the ground have been insubstantial because of its limitations in standalone operability and higher power consumption leading to higher cost and sparse area coverage. In this paper, we designed and developed a low power, low-cost remote sensor station with LoRa transmitters, which has the standalone operating capability. It is compact, mobile and it has a simple design. It is equipped with a self-sustaining power supply, LoRa transmitters, processors, antenna and sensors; mainly focusing on the weather monitoring parameters like humidity and temperature. The basic mechanism of data relay is to sense and transmit sensor data packets in real-time. The feasibility of the sensor station has been studied in terms of power budget, link budget, its operation outdoors and the overall development costs. The sensor station can be placed in areas where there are no ground infrastructures for communication.</p>

DOI： 10.2322/tastj.19.224

CiNii Article

CiNii Research

その他リンク： https://www.jstage.jst.go.jp/article/tastj/19/2/19_19.224/_pdf

Cubesat interface standardization to achieve faster delivery and mission success 査読有り

Cho M., Yamauchi T., Sejera M., Kim S., Masui H.

Proceedings of the International Astronautical Congress, IAC   2020-October   2020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 © 2020 by Mengu Cho. In 2019, a new project to standardize the CubeSat interface started. Discussion has been made utilizing various gathering opportunities of the CubeSat community. A survey on the CubeSat interface has been distributed the CubeSat community to collect the satellite developers' experience and desires regarding the interface, and the CubeSat vendors' reality and desires. A research work to identify the difficulties associated integrating CubeSat components from different vendors is on-going. Initial finding suggests that clear definition of interface related information, especially the digital data communication, in the user manual is really needed. A table of content of the standard has been drafted, which is mainly made of four parts. (1) Interface among components, (2) Interface between CubeSat bus (platform) and mission payloads, (3) Document specification to describe the information related to component interface, (4)Document specification to describe the information related to CubeSat bus (platform) interface. The project aims at submitting a new work item proposal to ISO/TC20/SC14 in summer 2021 and publish the standard by 2024.

Scopus

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Horyu-VI: International cubesat mission to investigate lunar horizon glow 査読有り

Orger N.C., Cho M., Iskender O.B., Lim W.S., Chandran A., Ling K.V., Holden K.H.L., Chow C.L., Bellardo J., Faure P., Santoni F., Circi C., Marzioli P., de Grossi F., Frezza L., Toyoda K., Masui H., Mariko T., Alarcon J.R.C., Yamauchi T., Kim S., Lim J.W.M., Potrivitu G., Laterza M.

Proceedings of the International Astronautical Congress, IAC   2020-October   2020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 © 2020 by International Astronautical Federation (IAF). All rights reserved. Interaction with the solar wind and UV/X-ray irradiation can cause the lunar dust to be electrostatically charged and mobilized all around the Moon, and light scattering by this dust cloud can be observed over the lunar terminator. This phenomenon, which has also been called the lunar horizon glow (LHG), still remains unexplained. The LHG observations using conventional lunar probes have limited observation opportunities and do not cover varying space weather conditions in cislunar environment such as strong upstream plasma flow and micrometeoroid flux that could enhance the lunar dust presence in the exosphere. The nanosatellite “HORYU-6” specialized in LHG observations will be put into lunar orbit to detect the light scattering above the lunar terminator. The proposed payload will perform multi-spectral imaging to monitor the lunar horizon several minutes before orbital sunrise or after orbital sunset for light scattering analysis. We show that we can obtain scientific results of lunar and planetary exploration using CubeSat at low cost and in a short period of time, and contribute to the development of lunar and planetary exploration in the future. The spacecraft will be developed jointly with universities in Singapore, the United States and Italy under the supervision of Kyushu Institute of Technology, with the aim of launching the SLS-2 rocket in the second half of 2022. Together with its own scientific objectives, the HORYU-6 mission will demonstrate the low thrust trajectory optimization by utilizing electric propulsion system together with other novel embedded technology demonstrations such as atomic clock, deep space navigation and communication with CubeSats.

Scopus

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SS27 Radiation protection and monitoring experiment on-board a 1U CubeSat and its ground verification 査読有り

Murase T., Masui H., Cho M., Wei S.

Proceedings - IEEE International Symposium on Circuits and Systems   2020-October   2020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）

Commercial-Off-The-Shelf(COTS) Integrated Circuits (ICs) are mostly sensitive to irradiations (e.g., protons, heavy-ions, etc.)in space, leading to various Single-Event Effects (SEEs). Among different SEEs, Single-Event Latch-up (SEL) is one of the most critical because it is detrimental and often damages ICs. This paper reports a circuit implementation that serves to provide protection for COTS ICs from SEL. The on-ground hardware verification on the basis of Californium 252 depicts that the circuit successfully cuts off the SEL current and subsequently resets the COTS IC. The reported circuit has been adopted in a 1U CubeSat that will be launched early 2020.

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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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

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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

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Demonstration of lean satellite (1U CubeSat) testing using PeTT vacuum chamber 査読有り

Bonsu B., Masui H., Cho M.

Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019   959 - 966   2019年06月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

© 2019 IEEE. There has been a high demand for low-cost thermal vacuum testing facility for Lean satellite (1U CubeSat) program in emerging space economies. Most often, CubeSat testing is performed in a complex and expensive thermal vacuum chamber equipped with for example shroud filled liquid nitrogen (boiling point is-195.7oC) for simulating the cold temperature environment as close to the cold heat sink of outer space in a simulated low pressure (>10-3 Pa) chamber environment. This paper introduces PeTT vacuum chamber as a low cost and easy access testing facility suitable for simulating cold temperature plateaus for performing a functional test of the internal subsystems of Lean satellite (1U CubeSat) functional test. Under ISO 19683: 'Design Qualification and Acceptance Test of Spacecraft and Units', the test requirement for cold temperature plateau is equal to-or more than-15oC. The PeTT vacuum chamber has been developed to achieve ISO 19683 test requirements. The PeTT vacuum chamber consists of a Peltier cooling device integrated inside a vacuum chamber. The Peltier cooling device consists of 4multi-stage Peltier elements sandwiched in-between a copper surface plate and water cooler has a mass of 3.4kg and size 152mm length × 127mm width × 40 mm height. The Peltier cooling device is targeted for performing 1U Cubesat functional test by conduction heat transfer. The Peltier cooling device has a total maximum exchange heat capability of 400W which runs by water cooling system and varying DC power supply. The vacuum chamber has an inner diameter of 55cm equipped with a rotary pump and diffusion pump to achieve a low pressure around 10-4 Pa. The main goal of this paper is to provide low cost and easy access testing technique for space activities in emerging space economies especially universities space research and development laboratories, to build their capacity in the installation and operation of a thermal vacuum testing facility. This paper provides details of the design and development of the PeTT vacuum chamber, cost, and results for testing 1U dummy CubeSat.

DOI： 10.1109/RAST.2019.8767775

Scopus

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Experimental investigation on silica dust lofting due to charging within micro-cavities and surface electric field in the vacuum chamber 査読有り

Orger N., Toyoda K., Masui H., Cho M.

Advances in Space Research   63 ( 10 )   3270 - 3288   2019年05月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

© 2019 COSPAR The charged dust particles can be mobilized electrostatically by the repulsion between the adjacent grains and the surface electric field due to the incoming electron current and the charge accumulation within the micro-cavities. In this study, the experimental results of the initial vertical launching velocities and the maximum dust heights are compared with the estimated values for the lofted spherical dust grains by the patch surface charging equations. Silica particles with the sizes between <6 and 45 µm in radius are loaded on a graphite plate, and they are exposed to the electron beam with 450 eV energy under 4 × 10 −3 Pa vacuum chamber pressure. During the first set of the experiments, the dust samples are tested without an initial compression process and an additional horizontal electric field. Second, the dust samples are compressed by two different weights in order to increase the packing density under approximately 780.7 Pa and 3780 Pa. Finally, the dust grains are placed between the two parallel aluminum plates to apply approximately 2000 V/m and 4800 V/m horizontal electric field. A high-speed camera is used to record the transportation of the dust grains together with a microscopic telescope, and the results point out that the patch surface dust-charging model estimations are in agreement with the first experiments. On the other hand, the dust particles from the compressed samples are lofted with higher velocities than the estimations, and the number of the dust lofting observations decreases significantly, which demonstrates the importance of the micro-cavities and the increased charging requirement to overcome the contact forces. When the horizontal electric field is present, the initial vertical launching velocities are measured to be lower than the other experiments, which can be attributed to the decreased charging requirement for the dust lofting as a result of inter-particle collisions and rolling motion. According to the experimental results, the electrostatic dust transportation can be controlled not only by the ambient plasma and the solar irradiation on the airless planetary bodies, but also by the surface properties such as the contact surfaces between the dust grains, the number of the micro-cavities related to the packing density, and the presence of the horizontal electric field contributing to the external forces by other particle motions.

DOI： 10.1016/j.asr.2019.01.045

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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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-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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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.O., Kim S., Kakimoto Y., Nakayama D., Kishimoto M., Elmegharbel H.A., Yamauchi T., Masui H., Cho M., Lap C.C., Ying Z., Siu T.M., Holden L.K.H.

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.

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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.

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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.

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Horyu-IV flight results of spacecraft plasma interaction experiments 査読有り

Fukuda H., Masui H., Iwata M., Toyoda K., 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）

© 2018 by the International Astronautical Federation (IAF). All rights reserved. HORYU-IV is a 30cm cubic satellite with an approximate mass of 11kg. The satellite was successfully launched by a H-IIA rocket to an orbit of 575km altitude with 31ºinclination on February 17, 2016. Since then, HORYU-IV has been conducting various flight experiments related to spacecraft plasma interaction. HORYU-IV implements HORYU-II, the previous satellite operated from 2012 to 2017, high voltage photovoltaic power generation technology and uses it to perform research on discharge phenomena. HORYU-IV's main mission is to acquire an arc current waveform by an onboard oscilloscope and capture its image by a camera triggered by the oscilloscope. In addition, HORYU-IV carries out scientific experiments on arc mitigation high voltage solar array, plasma measurement using a double Langmuir probe, vacuum arc thruster, photoelectron current measurement and polymer material degradation. HORYU-IV captured various discharge waveforms and images in space that can be categorized into several types. Ground experiments were carried out to compare the waveforms between the flight results and the ground results. The Double Langmuir probe was operated in space and its result was compared with the computer simulation results. Photoelectron emission yield was measured for several material for the first time in orbit. The overall results obtained in the past two and a half years from the spacecraft plasma interaction experiments will be presented.

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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.

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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

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Screening of nanosatellite microprocessors using californium single-event latch-up test results 査読有り

Tomioka T., Okumura Y., Masui H., Takamiya K., Cho M.

Acta Astronautica   126   334 - 341   2016年09月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

© 2016 IAA. A single-event latch-up (SEL) test using a252Cf radioisotope was carried out. The results were compared with those of a proton test and from observation in orbit. A radioisotope can reproduce phenomena observed in orbit that are caused by protons. Considering the inexpensive nature of the252Cf test, it is more suitable for nanosatellites that require low cost and fast delivery. A SEL occurrence rate of a commercial-off-the-shelf microprocessor was derived from the ground test results. The252Cf test provided a SEL rate approximately 1×106times greater than that in orbit. This data can be used to derive the minimum SEL occurrence rate in orbit and help satellite designers to evaluate the risk of SEL and take measures if necessary.

DOI： 10.1016/j.actaastro.2016.05.004

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