HISAKI Project Team
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  2. Mariko Akiyama

Mariko Akiyama

  (秋山 茉莉子)

Profile Information

Affiliation
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
Degree
Ph.D (Engineering)(Mar, 2023, The University of Tokyo)
J-GLOBAL ID
202101009520910299
researchmap Member ID
R000015405

Research Interests

 4

Research Areas

 1

Research History

 2

Education

 3

Papers

 3
  • Keita Nishii, Mariko Akiyama, Hiroyuki Koizumi, Kimiya Komurasaki
    Combustion Science and Technology, 195(10) 1-17, Dec 28, 2021  
  • Mariko AKIYAMA, Keita NISHII, Yoshihito MANNAMI, Masaya MUROHARA, Hiroyuki KOIZUMI, Kimiya KOMURASAKI
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 64(4) 223-233, 2021  
  • Keita Nishii, Jun Asakawa, Kosei Kikuchi, Mariko Akiyama, Qihang Wang, Masaya Murohara, Yasuho Ataka, Hiroyuki Koizumi, Ryu Funase, Kimiya Komurasaki
    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 63(4) 141-150, 2020  
    The University of Tokyo has proposed a water resistojet thruster with a high certainty of liquid-vapor separation and low power consumption. In this propulsion system, liquid water is periodically vaporized in a pulsating manner to generate thrust. A vaporization chamber with a labyrinth-shaped flow path catches droplets using their surface tension to separate the liquid and vapor, and the droplets vaporize under normal temperature to reduce the input power by reusing the heat from the surrounding components. In this study, we designed and fabricated a flight model of the proposed propulsion system for 6U CubeSat and evaluated the performance of this propulsion system, including the control method. The results confirm the concept of the proposed liquid-vapor separation method and its low power consumption. Moreover, we revealed the relationships between the vaporizing duty cycle, input power, and thrust.

Presentations

 13
  • 秋山茉莉子, 西井啓太, 小泉宏之, 小紫公也
    宇宙科学技術連合講演会講演集(CD-ROM), 2021
  • 万浪義史, 西井啓太, 秋山茉莉子, 室原昌弥, 小泉宏之, 小紫公也
    宇宙科学技術連合講演会講演集(CD-ROM), 2020
  • MANNAMI Yoshihito, NISHII Keita, AKIYAMA Mariko, MUROHARA Masaya, KOIZUMI Hiroyuki, KOMURASAKI Kimiya
    令和元年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2019, Jan, 2020, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)
    Space Transportation Symposium FY2019 (January 16-17, 2020. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
  • Keita Nishii, Yoshihito Mannami, Mariko Akiyama, Masaya Murohara, Koizumi Hiroyuki, Kimiya Komurasaki
    AIAA Propulsion and Energy 2020 Forum, 2020
    The combustion of aluminum and magnesium is an attractive power source. Many practical tests have been conducted as a composite propellant of metal powder and water. However, because the safety and the ease of handling are required to be launched into space, it is desirable that nonpowder metal is used as fuel and stored separately from oxidizer. Heat loss has a significant impact on the combustion of bulk metals. Though combustion behavior of bulk metals differs from that of powders, little has been reported on the combustion of bulk metal with water. This study, first, considered two types of ignition method: Joule heating and induction heating and investigated their feasibility in the scale of small spacecraft. Then, two types of experiments were carried out. The former is the wire combustion experiment using Joule heating. This experiment revealed that the characteristics of millimeter scale bulk metal combustion with water vapor. The latter experiment is the induction heating of a magnesium rod as an initial test of the ignition system for centimeter scale fuel. This test demonstrated the heating of the metal and identified the rooms for improvement to ignite the fuel.
  • 室原 昌弥, 西井 啓太, 菊池 航世, 秋山 茉莉子, 王 啓航, 安宅 泰穂, 服部 旭大, 浅川 純, 小泉 宏之, 船瀬 龍, 小紫 公也
    Apr 18, 2019
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Professional Memberships

 1

Research Projects

 2

Industrial Property Rights

 1
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