Development of Propulsion System for Microsatellite Based on Effective COTS, and Its Demonstration in S-310-36 Sounding Rocket Experiment

Sahara, Hironori; Nakasuka, Shinichi

doi:10.2322/jjsass.55.579

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

2007

DOI: 10.2322/jjsass.55.579

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Development of Propulsion System for Microsatellite Based on Effective COTS, and Its Demonstration in S-310-36 Sounding Rocket Experiment

Hironori Sahara¹,

Shinichi Nakasuka²

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Cited by 3 publications

References 10 publications

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[Special Issue of In-Space Flight Experiments of Electrodynamic Tether] Development of Inflatable Extension Boom and Its Demonstration in S-520-25 Sounding Rocket

宏典¹,

武夫²,

秋人³

et al. 2012

AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL

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This paper reports a development and demonstration of inflatable extension boom in the experiments of the ISAS/JAXA sounding rocket, S-520-25. The inflatable extension boom developed by the authors is the longest in ones with conductive part to work as an electrode for collection of electrons surrounding the rocket. S-520-25 sounding rocket was launched in August 31, 2010, and 5 experiments including an extension of the inflatable boom were conducted. The inflatable extension boom and its system worked very well with no problem to form 4-m-long electrode in space.

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[Special Issue of In-Space Flight Experiments of Electrodynamic Tether] Development of Inflatable Extension Boom and Its Demonstration in S-520-25 Sounding Rocket

宏典¹,

武夫²,

秋人³

et al. 2012

AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL

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Antenna Design Method for Low Power Miniaturized Microwave Discharge Ion Engines

Koizumi¹,

Kuninaka²

2009

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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In this study, we succeeded to develop a very low power miniaturized ion engine powered by microwave discharge. The accomplished performance was ion production cost of 240 W/A and propellant utilization efficiency of 39% by input microwave power 1.0 W and mass flow rate of 0.15 sccm. In order to realize this very low power operation, we have proposed an antenna design method for miniaturized microwave ion engines. The effectiveness of this method was verified by plasma observation inside the discharge chamber and ion beam extraction characteristics of the engine. Based on this method, antenna of the engine was designed and improved. As a result we have achieved to our goal.

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Effect of the Thruster Configurations on a Laser Ignition Microthruster

Koizumi¹,

Hamasaki²,

Kondo³

et al. 2010

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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:Research and development of small spacecraft have advanced extensively throughout the world and propulsion devices suitable for the small spacecraft, microthruster, is eagerly anticipated. The authors proposed a microthruster using 1-10-mm-size solid propellant. Small pellets of solid propellant are installed in small combustion chambers and ignited by the irradiation of diode laser beam. This thruster is referred as to a laser ignition microthruster. Solid propellant enables large thrust capability and compact propulsion system. To date theories of a solid-propellant rocket have been well established. However, those theories are for a large-size solid propellant and there are a few theories and experiments for a micro-solid rocket of 1-10 mm class. This causes the difficulty of the optimum design of a micro-solid rocket. In this study, we have experimentally investigated the effect of thruster configurations on a laser ignition microthruster. The examined parameters are aperture ratio of the nozzle, length of the combustion chamber, area of the nozzle throat, and divergence angle of the nozzle. Specific impulse dependences on those parameters were evaluated. It was found that large fraction of the uncombusted propellant was the main cause of the degrading performance. Decreasing the orifice diameter in the nozzle with a constant open aperture ratio was an effective method to improve this degradation.

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Development of Propulsion System for Microsatellite Based on Effective COTS, and Its Demonstration in S-310-36 Sounding Rocket Experiment

Cited by 3 publications

References 10 publications

[Special Issue of In-Space Flight Experiments of Electrodynamic Tether] Development of Inflatable Extension Boom and Its Demonstration in S-520-25 Sounding Rocket

[Special Issue of In-Space Flight Experiments of Electrodynamic Tether] Development of Inflatable Extension Boom and Its Demonstration in S-520-25 Sounding Rocket

Antenna Design Method for Low Power Miniaturized Microwave Discharge Ion Engines

Effect of the Thruster Configurations on a Laser Ignition Microthruster

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