増井 博一 (マスイ ヒロカズ)

MASUI Hirokazu

写真a

職名

助教

研究室住所

福岡県北九州市戸畑区仙水町1-1

研究分野・キーワード

電気推進機,宇宙環境,超小型衛星,環境試験

出身大学 【 表示 / 非表示

  • 2001年03月   九州工業大学   工学部   機械知能工学科   卒業   日本国

出身大学院 【 表示 / 非表示

  • 2006年03月  九州大学  総合理工学研究科  先端エネルギー理工学専攻  博士課程・博士後期課程  修了  日本国

取得学位 【 表示 / 非表示

  • 九州大学 -  博士(工学)  2006年03月

学内職務経歴 【 表示 / 非表示

  • 2019年04月
    -
    継続中

    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  

  • 2014年04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  

  • 2010年08月
    -
    2014年03月

    九州工業大学   宇宙環境技術ラボラトリー   助教  

所属学会・委員会 【 表示 / 非表示

  • 2013年07月
    -
    継続中
     

    プラズマ・核融合学会  日本国

  • 2004年04月
    -
    継続中
     

    日本航空宇宙学会  日本国

 

研究経歴 【 表示 / 非表示

  • 超小型衛星の開発と環境試験

    超小型衛星,環境試験,試験標準  

    研究期間: 2010年04月  -  継続中

  • 宇宙機の帯電,放電に関する地上試験

    宇宙プラズマ,ESD,帯電,太陽電池  

    研究期間: 2006年04月  -  2010年03月

論文 【 表示 / 非表示

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

    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  [査読有り]

     概要を見る

    © 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 Scopus

  • CubeSat bus interface with Complex Programmable Logic Device

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

    Acta Astronautica    160   331 - 342   2019年07月  [査読有り]

     概要を見る

    © 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 Scopus

  • Demonstration of lean satellite (1U CubeSat) testing using PeTT vacuum chamber

    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  [査読有り]

     概要を見る

    © 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 Scopus

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

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

    Advances in Space Research    63 ( 10 ) 3270 - 3288   2019年05月  [査読有り]

     概要を見る

    © 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 Scopus

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

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

    Journal of Physics: Conference Series    1152 ( 1 )   2019年03月  [査読有り]

     概要を見る

    © 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 Scopus

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担当授業科目 【 表示 / 非表示

  • 2019年度  宇宙システム環境