On-orbit Performance Evaluation of AQUARIUS: a Water Resistojet Propulsion System during Initial Flight Operation of a 6U CubeSat EQUULEUS

DOI Web Site 30 References
  • SEKINE Hokuto
    Department of Aeronautics and Astronautics, The University of Tokyo
  • ATAKA Yasuho
    Department of Aeronautics and Astronautics, The University of Tokyo
  • MORIAI Isamu
    Department of Aeronautics and Astronautics, The University of Tokyo
  • FUJIMORI Aoma
    Department of Aeronautics and Astronautics, The University of Tokyo
  • AKIYAMA Mariko
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • MUROHARA Masaya
    Department of Aeronautics and Astronautics, The University of Tokyo
  • KOIZUMI Hiroyuki
    Department of Aeronautics and Astronautics, The University of Tokyo Department of Advanced Energy, The University of Tokyo
  • KAKIHARA Kota
    ArkEdge Space Inc.
  • SHIRASU Kento
    Department of Aeronautics and Astronautics, The University of Tokyo
  • TAKASAKI Daigo
    Department of Aeronautics and Astronautics, The University of Tokyo
  • MINEMATSU Ryo
    Department of Aeronautics and Astronautics, The University of Tokyo
  • MATSUURA Masayuki
    Department of Advanced Energy, The University of Tokyo
  • ARAI Ten
    Department of Advanced Energy, The University of Tokyo
  • TSUCHIYA Yuto
    Department of Aeronautics and Astronautics, The University of Tokyo
  • AIZAWA Naoto
    Department of Advanced Energy, The University of Tokyo
  • NOGUCHI Mizuki
    Department of Advanced Energy, The University of Tokyo
  • MATSUSHITA Shuhei
    Department of Aeronautics and Astronautics, The University of Tokyo ArkEdge Space Inc.
  • SHIBUKAWA Toshihiro
    ArkEdge Space Inc.
  • TOMA Kazuki
    Department of Aeronautics and Astronautics, The University of Tokyo
  • TAKASHIMA Kazuki
    Department of Aeronautics and Astronautics, The University of Tokyo
  • OGINO Kosuke
    Department of Aeronautics and Astronautics, The University of Tokyo
  • KUSANO Yuki
    Department of Aeronautics and Astronautics, The University of Tokyo
  • NAKAJIMA Shintaro
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • FUSE Ryota
    Department of Aeronautics and Astronautics, The University of Tokyo
  • MIYOSHI Kota
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • ISHIKAWA Akihiro
    Department of Aeronautics and Astronautics, The University of Tokyo ArkEdge Space Inc.
  • KAWABATA Yosuke
    Department of Aeronautics and Astronautics, The University of Tokyo
  • MOCHIZUKI Tomoki
    Department of Aeronautics and Astronautics, The University of Tokyo
  • CHIKAZAWA Takuya
    Department of Advanced Energy, The University of Tokyo
  • FUNASE Ryu
    Department of Aeronautics and Astronautics, The University of Tokyo Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

Search this article

Description

<p>A 6U CubeSat EQUULEUS (EQUilibriUm Lunar-Earth point 6U Spacecraft) successfully executed an orbit transfer using a water-propelled propulsion system in deep space for the first time using AQUARIUS (AQUA ResIstojet propUlsion System), a water resistojet propulsion system. We report on-orbit performance analysis of AQUARIUS in its initial flight operation. AQUARIUS employed a distinct water droplet vaporization structure for efficient gas-liquid separation and a power-saving strategy for the large latent heat of water. The time-averaged thrust observed in two on-orbit operations using two thruster heads was approximately 6.0 mN, with a specific impulse of 91.0 s and a power consumption of less than 14 W. The thrust-to-power ratio increased with the temperature difference between the vaporization chamber and the adjacent communication device. This indicates that the necessary power for the vaporization of the water was effectively compensated for by the heat from the surroundings owing to the appropriate thermal design of EQUULEUS. The thrust coefficient efficiency was found to be approximately 0.86, which was higher than in the ground test (∼0.66). This is possibly due to the extremely low back pressure on orbit that mitigates the nozzle efficiency reduction due to low Reynolds number flows.</p>

Journal

References(30)*help

See more

Keywords

Details 詳細情報について

Report a problem

Back to top