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Your search keyword '"Shigeyasu Iihara"' showing total 10 results
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10 results on '"Shigeyasu Iihara"'

1. Performance Evaluation of a Two-Kilowatt Magnetically Shielded Hall Thruster

Author

Kenichi Kubota, Kazuo Uematsu, Kenji Fuchigami, Gen Ito, Ikkoh Funaki, Shigeyasu Iihara, Yosuke Tashiro, Shinatora Cho, and Hiroki Watanabe

Subjects
Propellant, 020301 aerospace & aeronautics, Materials science, business.industry, Mechanical Engineering, Aerospace Engineering, 02 engineering and technology, 01 natural sciences, Thrust efficiency, 010305 fluids & plasmas, Hall effect thruster, law.invention, Magnetic field, Anode, Fuel Technology, 0203 mechanical engineering, Space and Planetary Science, law, 0103 physical sciences, Shielded cable, Electromagnetic shielding, Mass flow rate, Aerospace engineering, business
Abstract

A 2-kW-class magnetically shielded Hall thruster was developed, and its performance was evaluated. Additionally, the effects of the discharge channel length, thruster body potential, anode dielectr...

Published
2020
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2. FLOW FIELD AND HEAT TRANSFER ANALYSIS IN AMON/MMH BIPROPELLANT ROCKET ENGINE

Author

Yu Daimon, Hideyo Negishi, Hiroumi Tani, Shigeyasu Iihara, Yoshiki Matsuura, and Shinichi Takata

Subjects
chemistry.chemical_compound, Materials science, chemistry, business.industry, Heat transfer, General Materials Science, Rocket engine, Computational fluid dynamics, Aerospace engineering, business, Flow field, Monomethylhydrazine
Published
2017
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3. Hypergolic Propellant Ignition Phenomenon Associated with Two-Phase Oxidizer Flow Injection

Author

Yoshiki Matsuura, Shigeyasu Iihara, and Yosuke Tashiro

Subjects
Propellant, Jet (fluid), Materials science, Waste management, Mechanical Engineering, Evaporation, Aerospace Engineering, Hypergolic propellant, Injector, Mechanics, Combustion, law.invention, Ignition system, Boiling point, Fuel Technology, Space and Planetary Science, law
Abstract

During pulse-mode operation of a bipropellant engine that uses mixed oxides of nitrogen and monomethyl hydrazine as a propellant, a titanium alloy injector with an unlike-doublet impinging stream absorbs the heat from the injector face, which is heated to a high temperature during combustion. When the injector’s temperature exceeds the boiling point of the oxidizer under several operating conditions, evaporation will occur at the initial inflow of each pulse. This evaporation phenomenon causes an unsteady two-phase flow that affects ignition and combustion phenomena. In this paper, this abnormal ignition and combustion phenomenon associated with the two-phase flow is investigated through experiments with a single-element injector. Data analysis on the impinging stream instability and the ignition phenomenon reveals that the unsteady oxidizer jet caused by evaporation may act as a trigger for high-frequency instability.

Published
2014
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4. Laboratory Testing of Hall Thrusters for All-electric Propulsion Satellite and Deep Space Explorers

Author

Yosuke Tashiro, Kenichi Kubota, Ikkoh Funaki, Hiroki Watanabe, Kenji Fuchigami, Shinatora Cho, and Shigeyasu Iihara

Subjects
010302 applied physics, Physics, Electrically powered spacecraft propulsion, business.industry, 0103 physical sciences, Satellite, NASA Deep Space Network, Aerospace engineering, business, 01 natural sciences, Laboratory testing, 010305 fluids & plasmas, Hall effect thruster
Published
2016
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5. Study of Electron Transport in a Hall Thruster by Axial-Radial fully Kinetic Particle Simulation

Author

Hiroki Watanabe, Kenji Fuchigami, Kenichi Kubota, Shinatora Cho, Ikkoh Funaki, Kazuo Uematsu, and Shigeyasu Iihara

Subjects
Physics, Electron mobility, Anomalous diffusion, Oscillation, Electron, Mechanics, Electric current, Atomic physics, Diffusion (business), Condensed Matter Physics, Plasma oscillation, Magnetic field
Abstract

Accepted: 2015-10-20, 資料番号: SA1150315000

Published
2015

6. Parametric Kinetic Simulation of an IHI High Specific Impulse SPT-Type Hall Thruster

Author

Ikkoh Funaki, Hiroki Watanabe, Kazuo Uematsu, Shinatora Cho, Shigeyasu Iihara, Kenji Honda, Kenji Fuchigami, and Kenichi Kubota

Subjects
Bohm diffusion, Physics, Mass flow rate, Specific impulse, Mechanics, Plasma, Kinetic energy, Simulation, Anode, Voltage, Parametric statistics
Abstract

A 1 kW class magnetic layer type Hall thruster designed for high specific impulse operation by IHI Corporation, Japan was modeled by a fully kinetic particle code. The measured maximum performance of the thruster was 64% in anode efficiency and 3,200s (3.1kW, 800V) in anode specific impulse. The thruster performance, wall heat loss and erosion, and the plasma property distributions were numerically investigated for the operation conditions ranged from 300V to 700V in discharge voltage, and 2mg/s to 4mg/s in xenon mass flow rate. Simulations with two numerical models: with and without the Bohm diffusion assumption were performed for each thruster operation conditions to characterize the uncertainty caused by the Bohm diffusion model. The simulation results were compared with the measured results, and exhibited excellent agreement with the maximum performance error of 20% for both models. It is suggested that as engineering tools, with and without Bohm simulations can be respectively used as the worst and best case analysis for the performance, heat load, and erosion.

Published
2014
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7. Particle Simulation of High Specific Impulse Operation of Low-Erosion Magnetic Layer Type Hall Thrusters

Author

Shinatora Cho, Ikkoh Funaki, Kenichi Kubota, Kenji Fuchigami, Kazuo Uematsu, Hiroki Watanabe, and Shigeyasu Iihara

Subjects
010302 applied physics, Physics, Particle simulation, Hall Thruster, business.industry, High-Specific Impulse, Electrical engineering, 01 natural sciences, 010305 fluids & plasmas, Hall effect thruster, Kinetic Particle Simulation, Erosion, 0103 physical sciences, Magnetic layer, Specific impulse, Aerospace engineering, business
Abstract

資料番号: SA1160202000

Published
2016
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8. Hall Thruster Development for Japanese Space Propulsion Programs.

Author

Yushi HAMADA, Junhwi BAK, Rei KAWASHIMA, Hiroyuki KOIZUMI, Kimiya KOMURASAKI, Naoji YAMAMOTO, Yusuke EGAWA, Ikkoh FUNAKI, Shigeyasu IIHARA, Shinatora CHO, Kenichi KUBOTA, Hiroki WATANABE, Kenji FUCHIGAMI, Yosuke TASHIRO, Yuya TAKAHATA, Tetsuo KAKUMA, Yusuke FURUKUBO, and Hirokazu TAHARA

Subjects
PROPULSION systems, THRUST -- Aerodynamics, ELECTRIC propulsion, FORCE & energy, MAGNETIC field effects
Abstract

Three different types of high power Hall thrusters--anode layer type, magnetic layer type with high specific impulse, and magnetic layer type with dual mode operation (high thrust mode and high specific impulse mode)--have been developed, and the thrust performance of each thruster has been evaluated. The thrust of the anode layer type thruster is in the range of 19-219 mN, with power in the range of 325-4500 W. The thrust of the high specific impulse magnetic layer type thruster was 102 mN, with specific impulse of 3300 s. The thrust of the bimodal operation magnetic layer thruster was 385mN with specific impulse of 1200 s, and 300mN with specific impulse of 2330 s. The performance of these thrusters demonstrates that the Japanese electric propulsion community has the capability to develop a thruster for commercial use. [ABSTRACT FROM AUTHOR]

Published
2017
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9. Visualization for a Voided Catalyst Bed of Hydrazine Thruster in Microgravity

Author

Fumihiro Ueno, Shigeyasu Iihara, Kenichi Kajiwara, Daisuke Goto, Toshiro Fujimori, Ryouji Imai, Hideshi Kagawa, and Youichi Marutani

Subjects
Engineering, chemistry.chemical_compound, chemistry, business.industry, Hydrazine, Mechanical engineering, Aerospace engineering, Propulsion, business, Visualization
Abstract

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit(11-14 July 2004), Fort Lauderdale, Florida, 資料番号: ARDS04015000, レポート番号: AIAA 2004-4153

Published
2004
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10. Study of electron transport in a Hall thruster by axial-radial fully kinetic particle simulation.

Author

Shinatora Cho, Hiroki Watanabe, Kenichi Kubota, Shigeyasu Iihara, Kenji Fuchigami, Kazuo Uematsu, and Ikkoh Funaki

Subjects
ELECTRON transport, PARTICLES (Nuclear physics), MAGNETIC fields, PLASMA kinetic theory, NUMERICAL analysis, PREDICTION models
Abstract

Electron transport across a magnetic field in a magnetic-layer-type Hall thruster was numerically investigated for the future predictive modeling of Hall thrusters. The discharge of a 1-kW-class magnetic-layer-type Hall thruster designed for high-specific-impulse operation was modeled using an r-z two-dimensional fully kinetic particle code with and without artificial electron-diffusion models. The thruster performance results showed that both electron transport models captured the experimental result within discrepancies less than 20% in thrust and discharge current for all the simulated operation conditions. The electron cross-field transport mechanism of the so-called anomalous diffusion was self-consistently observed in the simulation without artificial diffusion models; the effective electron mobility was two orders of magnitude higher than the value obtained using the classical diffusion theory. To account for the self-consistently observed anomalous transport, the oscillation of plasma properties was speculated. It was suggested that the enhanced random-walk diffusion due to the velocity oscillation of low-frequency electron flow could explain the observed anomalous diffusion within an order of magnitude. The dominant oscillation mode of the electron flow velocity was found to be 20 kHz, which was coupled to electrostatic oscillation excited by global ionization instability. [ABSTRACT FROM AUTHOR]

Published
2015
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