Engineering Model of the Miniature Ion Propulsion System for the Nano-satellite: HODOYOSHI-4

Koizumi, Hiroyuki; Komurasaki, Kimiya; Aoyama, Junichi; Yamaguchi, Koji

doi:10.2322/tastj.12.tb_19

Cited by 40 publications

(23 citation statements)

References 10 publications

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“…The propulsion system was named MIPS for a Miniature Ion Propulsion System. 208 It is the world-first miniature ion thruster operating on a microsatellite having a mass of less than 100 kg. 209 The other ion thruster was equipped on PROCYON, a 50-kg-class microspace probe orbiting around the sun.…”

Section: B Miniaturized Ion Thrusters On Microsatellitesmentioning

confidence: 99%

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Levchenko

Bazaka

Ding

et al. 2018

Applied Physics Reviews

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269

104

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Rapid evolution of miniaturized, automatic, robotized, function-centered devices has redefined space technology, bringing closer the realization of most ambitious interplanetary missions and intense near-Earth space exploration. Small unmanned satellites and probes are now being launched in hundreds at a time, resurrecting a dream of satellite constellations, i.e., wide, all-covering networks of small satellites capable of forming universal multifunctional, intelligent platforms for global communication, navigation, ubiquitous data mining, Earth observation, and many other functions, which was once doomed by the extraordinary cost of such systems. The ingression of novel nanostructured materials provided a solid base that enabled the advancement of these affordable systems in aspects of power, instrumentation, and communication. However, absence of efficient and reliable thrust systems with the capacity to support precise maneuvering of small satellites and CubeSats over long periods of deployment remains a real stumbling block both for the deployment of large satellite systems and for further exploration of deep space using a new generation of spacecraft. The last few years have seen tremendous global efforts to develop various miniaturized space thrusters, with great success stories. Yet, there are critical challenges that still face the space technology. These have been outlined at an inaugural International Workshop on Micropropulsion and Cubesats, MPCS-2017, a joint effort between Plasma Sources and Application Centre/Space Propulsion Centre (Singapore) and the Micropropulsion and Nanotechnology Lab, the G. Washington University (USA) devoted to miniaturized space propulsion systems, and hosted by CNR-Nanotec—P.Las.M.I. lab in Bari, Italy. This focused review aims to highlight the most promising developments reported at MPCS-2017 by leading world-reputed experts in miniaturized space propulsion systems. Recent advances in several major types of small thrusters including Hall thrusters, ion engines, helicon, and vacuum arc devices are presented, and trends and perspectives are outlined.

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Section: B Miniaturized Ion Thrusters On Microsatellitesmentioning

confidence: 99%

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Levchenko

Bazaka

Ding

et al. 2018

Applied Physics Reviews

Self Cite

269

104

View full text Add to dashboard Cite

show abstract

“…The components and structure of I-COUPS are based on the miniature ion propulsion system: MIPS [5][6][7] , which was developed for the 60 kg, LEO-satellite HODOYOSHI-4 [8][9][10] . Difference from the MIPS is the addition of CTU whose gas is extracted from the xenon GMU.…”

Section: I-coupsmentioning

confidence: 99%

Initial Flight Operations of the Miniature Propulsion System Installed on Small Space Probe: PROCYON

Koizumi

Kawahara

Yaginuma

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Initial flight operations of the miniature propulsion system I-COUPS (Ion Thruster and COld-gas Thruster Unified Propulsion System) are presented with problems found in space and its countermeasures for them. The I-COUPS was developed by the University of Tokyo and installed on a 70 kg space probe, PROCYON as main propulsion system to verify propulsive capability of the first micropropulsion in deep space. The PROCYON was successfully launched on December 3rd, 2014 and inserted into an orbit around the Sun. The PROYON project team started flight operation on the interplanetary orbit. Up to today, the cold-gas thrusters have successfully conducted unloading maneuvers since the launch. The ion thruster overcame several problems and achieved 223 hours operation with the averaged thrust of 346 μN. The I-COUPS will become the first electric propulsion and reaction control system operated on a small space probe (<100 kg) on an interplanetary orbit.

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“…For example, in the case of miniature ion propulsion system "MIPS" developed by the University of Tokyo, 45 % of the total propulsion system with a mass of 10 kg was occupied with high-pressure gas systems which did not contribute to thrust performance directly. 11) Chemical propulsion systems which use hydrogen or ADN are also conventional for large satellites. However, utilizing cost of toxic propellant including hardware, operation, ground support infrastructure and transportation will reach to more than $1M.…”

Section: Introductionmentioning

confidence: 99%

Fundamental Ground Experiment of a Water Resistojet Propulsion System: AQUARIUS Installed on a 6U CubeSat: EQUULEUS

Asakawa

Koizumi

Nishii

et al. 2018

AEROSPACE TECHNOLOGY JAPAN

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In this study, a water resistojet propulsion system, named AQUARIUS, is proposed and the breadboard model (BBM) test results and the engineering model (EM) design are described. AQUARIUS will be on-boarded the SLS EM-1 CubeSat: EQUULEUS, which is scheduled to be launch in 2019. AQUARIUS uses a storable, safe and non-toxic propellant: water, which allows for the design of all propulsion system below 100 kPa, reduction of dry mass ratio and simplification of feed line routing using soft tubes. AQUARIUS consists of three components as follows: a tank, a vaporization chamber and thruster head. BBM of the vaporization chamber, and the thruster head were designed and tested. The evaporation rate required heat and thrust performance were evaluated. Based on the BBM test results, the engineering model of AQUARIUS was designed.

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Engineering Model of the Miniature Ion Propulsion System for the Nano-satellite: HODOYOSHI-4

Cited by 40 publications

References 10 publications

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers

Initial Flight Operations of the Miniature Propulsion System Installed on Small Space Probe: PROCYON

Fundamental Ground Experiment of a Water Resistojet Propulsion System: AQUARIUS Installed on a 6U CubeSat: EQUULEUS

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