Keiichi Hori

Japan Aerospace Exploration Agency

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Co-Authors

Yutaka Wada

Ebara (Japan)

Nobuji Kato

Rachid Amrousse

Chouaib Doukkali University

Yo Kawabata

Fukuoka University

Toshiyuki Katsumi

Nagaoka University of Technology

Ryo Nagase

Chiba Institute of Technology

Hiroto Habu

Japan Aerospace Exploration Agency

Kiyokazu Kobayashi

Japan Aerospace Exploration Agency

Katsuya Hasegawa

Institute of Space and Astronautical Science

Makihito Nishioka

University of Tsukuba

Cooperative Institutions

The University of Tokyo

Japan Aerospace Exploration Agency

Institute of Space and Astronautical Science

Osaka University

Kyoto University

Tohoku University

Nagoya University

Mitsubishi Heavy Industries (Germany)

Mitsubishi Heavy Industries (Japan)

Kyushu University

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Effect of hydrostatic pressure on sterilization and preservation of freshly-squeezed, non-pasteurized citrus juice.

Nippon Nōgeikagaku Kaishi (1989)

Hiroshi Ogawa Kazuma Fukuhisa Haruji Fukumoto Keiichi Hori Rikimaru Hayashi

種々の柑橘類の無殺菌果汁を23°Cで1～6 kbar, 10分間の加圧処理を行い,果汁成分の変化,微生物の殺菌および酵素失活を調べた. (1) 6 kbarまでの加圧処理による果汁成分の変化はほとんどみられず,加圧処理を行った伊予柑果汁は,無加圧の対照果汁と同じ新鮮な香味を有するものであった. (2) 加圧処理後の細菌および酵母・カビの生菌数を調べたところ, 3～4 kbarの加圧でこれらの殺菌ができた.ただし,耐熱性の細菌胞子は生存した.また,加圧時の温度を45°Cとしたり,あるいは加圧時間を30分にすることにより,より低圧で殺菌効果が認められた. (3) 果汁中のペクチンエステラーゼ活性は,処理圧力が高いほど失活したが, 6 kbarの加圧においても一部活性が残存した.ペルオキシダーゼは,これより耐圧性があった.酵素の場合も,45°Cの加温を組み合せると両酵素の失活を高めることができた. 以上の結果より,柑橘類の無殺菌果汁は高庄処理により天然の風味を保持したまま殺菌を行えると判断した.

Pasteurization

Sterilization

Hydrostatic pressure

Orange juice

Hydrostatic equilibrium

10.1271/nogeikagaku1924.63.1109

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Citations (18)

Development Study on A Micro-Solid Propellant Rocket Array Thruster

The proceedings of the JSME annual meeting (2002)

Shinichiro Tokudome Ryuichiro Hosokawa Syuji TANAKA Keiichi Hori Hirobumi Saito

The authors have developed the practical prototype of a micro-solid propellant rocket array thruster for attitude control of a 10kg class micro-spacecraft. a target of this activity is to build the array thruster with 10000 of solid propellant micro-rockets arrayed on a 100×100mm substrate. The prototype with the Φ0.8 micro-rockets arrayed at a pitch of 1.2mm on a 20×30mm substrate has built and tested so far. Boron/potassium nitrate (NAB) propellant is used with/without initiator of lead rhodanide/potassium chlorate/nitrocellulose (RK). Impulse thrust was measured by means of a pendulum method. The experimental results show that the prototype has proper ignition characteristics and further experimental studies are needed to evaluate and to control the impulse thrust with accuracy. We are planning to conduct the thrust measurement test under vacuum condition.

Specific impulse

Solid-fuel rocket

Rocket (weapon)

10.1299/jsmemecjo.2002.1.0_337

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Citations (1)

Engineering aspects of HDTV systems: the nonbroadcast applications of HDTV

Keiichi Hori

A broad range of nonbroadcast applications can be foreseen for HDTV. Some of them have already been implemented and have proved to be attractive and promising. A list of such applications is given and several of them are briefly analyzed. These applications consist of movie production; theaters; electronic publishing; TV commercials; catalog TV displays; telemedicine; medical still picture files; medical education; museums and zoos; educational applications related natural science and the arts, and HDTV lectures; computer-aided design; and observation and surveillance systems.< >

10.1109/tencon.1990.152693

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Small Rocket Launch Experiment using Low Melting Point Thermoplastic Fuel/N2O Hybrid Rocket

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference (2013)

Yutaka Wada Ryuichi Kato Nobuji Kato Keiichi Hori

Hybrid rocket using Low Melting Temperature Thermoplastics (LT) fuel as a solid fuel has been studied. The LT fuel has higher regression rate than classical inert polymer fuel such as a Hydroxyl-Terminated-PolyButadiene (HTPB), and an excellent mechanical property as same as solid propellants. Efforts has been paid successfully to enhance the adhesion property against metallic casing and linear material, and thus, the fuel looks promising for the application to large scale motors. As the first step, small hybrid rocket was launched by LT/N2O hybrid combination on the basis of the experimental data of regression rate using a lab. scale hybrid rocket motor. In this paper, the detailed discussion of this successful launch is presented.

Rocket (weapon)

Rocket propellant

10.2514/6.2013-4050

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Citations (8)

PREFACE: "ADVANCED ENERGETIC MATERIALS AND TECHNIQUES FOR ROCKET PROPULSION" IN HONOR OF PROF. KENNETH KUAN-YUN KUO

International Journal of Energetic Materials and Chemical Propulsion (2017)

Luigi T. DeLuca Keiichi Hori J.F. Zevenbergen

All memorial issues

Honor

Rocket (weapon)

10.1615/intjenergeticmaterialschemprop.v16.i1.10

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COMBUSTION CHARACTERISTICS OF A MICRO-SOLID PROPELLANT ROCKET ARRAY THRUSTER

한국추진공학회 학술대회논문집 (2004)

Kazuyuki Kondo Shuji Tanaka Hiroto Habu Shinichiro Tokudome Keiichi Hori

Solid-fuel rocket

Rocket propellant

Rocket (weapon)

Liquid-propellant rocket

Source

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Chemical engineering study for hydroxylammonium nitrate monopropellant decomposition over monolith and grain metal-based catalysts

Reaction Kinetics Mechanisms and Catalysis (2013)

Rachid Amrousse Toshiyuki Katsumi Ahmed Bachar Rachid Brahmi Mohamed Bensitel

Monolith

Monopropellant

10.1007/s11144-013-0626-6

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Citations (27)

A STUDY ON THE COMBUSTION MECHANISM OF HYDROXYLAMMONIUM NITRATE

International Journal of Energetic Materials and Chemical Propulsion (2015)

Toshiyuki Katsumi Rachid Amrousse Yosui Niboshi Keiichi Hori

The reaction mechanism of catalytic decomposition of hydroxylammonium nitrate (HAN) aqueous solutions was investigated to understand the catalytic decomposition and to develop the thruster using a HAN-based monopropellant. It is important to understand the catalytic decomposition because the chemical reaction of the monopropellant is activated by a catalyst in the existing monopropellant thruster. Previously, several researchers investigated the thermal decomposition and the combustion characteristics of HAN-based solutions. However, catalytic decomposition of HAN-based monopropellant has not been well understood. In this study, in order to clarify the reaction mechanisms of catalytic and thermal decompositions, differential thermal analysis and thermogravimetric analysis of HAN aqueous solution and product gas analysis were conducted in the cases of catalytic and thermal decompositions. These analyses show that the Ir-based catalyst was effective to reduce the onset temperature of HAN decomposition and that the difference in product gas species was not obvious between catalytic and thermal decompositions. Based upon these results, a reaction mechanism of catalytic decomposition was discussed. It was found that the reaction mechanism of catalytic decomposition is almost the same as that of thermal decomposition. Furthermore, nitric acid (HNO3) was generated at lower temperature in the case of catalytic decomposition than that of thermal decomposition. Therefore, Ir-based catalyst cannot change the reaction mechanism but can activate the reaction path of HNO3 generation.

Monopropellant

Thermogravimetric analysis

10.1615/intjenergeticmaterialschemprop.2015011535

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Citations (22)

Combustion Characteristics of ADN (Ammonium Dinitramide) Based Solid Propellants

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES AEROSPACE TECHNOLOGY JAPAN (2012)

Koji Fujisato Hiroto Habu Hidefumi Shibamoto Xiuchao Yu Atsumi Miyake

Ammonium perchrolate (AP) is the most useful oxidizer for the solid rocket motors (SRMs) under the present situation, however it is also the source of the environmental pollution close to the launch site. It is well known that HCl is exhausted through the firing of SRMs and its concentration reaches approximately 10 to 20 mole percent of the total exhaust. 'Environmentally friendly' and 'High performance' are required for the next-generation SRMs. In this study, ammonium dinitramide (ADN), which has recently attracted attentions as a halogen-free oxidizer was employed for a substitution of AP and the combustion properties of the composite propellants were investigated. Thermoplastic elastomer (TP) and hydroxyl-terminated butadiene polymer (HTPB) were used as a binder for this research. Pyrotechnic sensitivity analysis was conducted to estimate the safety of TP/ADN propellants. Strand burning tests were also carried out for all samples and the burning rate and temperature profile were obtained through these experiments. It was found that the burning rate characteristics of ADN-based propellants were influenced by the binders.

Thermoplastic elastomer

10.2322/tastj.10.pa_89

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Citations (3)

Pyrolysis–gas chromatography of hybrid rocket fuel comprising low-melting-point thermoplastics

Journal of Analytical and Applied Pyrolysis (2023)

Michiya Fujita Ayana Banno Yutaka Wada Yuji Mishima Nobuji Kato

Solid fuel

10.1016/j.jaap.2023.106294

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