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公开(公告)号：JPH02211333A
公开(公告)日：1990-08-22
申请号：JP2767089
申请日：1989-02-08
Applicant: NAT AEROSPACE LAB , ISHIKAWAJIMA HARIMA HEAVY IND
Inventor： CHINZEI NOBUO , MASUTANI GORO , KOMURO TOMOYUKI , KUDO KENJI , MURAKAMI JUNRO , TANI KOICHIRO , WAKAMATSU YOSHIO , KARITA TAKESHI , SATO YUKINORI , SAYAMA MASAMI , OWAKI KATSURA , TSUCHIYA KAZUYUKI
Abstract: PURPOSE:To enable a combustion promoting effect to be as high as possible by constituting a plasma jet ignition system of an ignition nozzle body, a working fluid supply means, an arc generating electrode and a plasma accelerating means. CONSTITUTION:Working fluid containing supplied oxygen is set to the plasma state by an arc generating electrode 8 of an ignition nozzle body 6 and accelerated sufficiently by a plasma accelerating means 9 to be jetted deeply into a combustor 1. This jetted plasma injection promotes the combustion of burnt fluid flowing in the combustor with supersonic speed by the thermal and kinetic energy and chemical reaction promoting effect along with active group generation to enable ignition. Also, since the working fluid provides plasma by the arc generating electrode 8 having a negative metal electrode 12 for promoting the formation of a high melting point oxidized film, the negative electrode 12, when the working fluid containing oxygen is used, promotes the formation of the high melting point protective oxidized film on the surface without being damaged by the arc so that stable plasma jet can be injected for a long time.
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公开(公告)号：JPH068896A
公开(公告)日：1994-01-18
申请号：JP16909592
申请日：1992-06-26
Applicant: NAT AEROSPACE LAB , NAT RES INST METALS , MIYAMOTO YOSHIO , HITACHI LTD
Inventor： SHINNO MASAYUKI , WAKAMATSU YOSHIO , MORO AKIO , SHIODA KAZUMICHI , MIYAMOTO YOSHIO , CHIKAZAKI MITSUO , ASHIDA AKIRA , WADA YUKIHIKO
Abstract: PURPOSE:To provide a cosmos synthetic energy conversion system for the shallow and deep cosmos spheres which is small-sized and lightweight and secures the high energy conversion efficiency. CONSTITUTION:The solar energy is utilized effectively and efficiently by arranging the light/electricity converters 3, 9, and 16 on the obverse surfaces and arranging the heat/electricity converters 4, 10 and 17 on the reverse surfaces of the concaved surface reflective mirrors 2, 8, and 15 for converging the solar beams to the heat collectors 5, 11, and 18 by the first-fourth power generation systems 1, 7, and 14, and the solar energy which is strong in the shallow cosmos is stored in the form of electricity and heat, and used as the energy source in the shadow part of the sun and in the deep cosmos. Since the hydrogen and oxygen of thrust generators 29 and 30 are generated through the electrolysis of water, the device can be made small-sized and lightweight, and the thrust is increased by heating hydrogen, and the efficiency of the heating of hydrogen and the heating of water in the electrolysis is increased through the direct heating by the heat of the heat collectors 6 and 19. A radioactive ray source 32 using the self-supplied energy source in the deep cosmos is mounted, and the radioactive rays radiated from the radioactive ray source 32 is converted to the thermal energy and electricity by the nuclear heat converters 33 and 35 and a thermal converter 37.
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公开(公告)号：JPH0579933B2
公开(公告)日：1993-11-05
申请号：JP5417490
申请日：1990-03-06
Applicant: NAT AEROSPACE LAB
Inventor： MURAKAMI JUNRO , KOMURO TOMOYUKI , KUDO KENJI , TANI KOICHIRO , MASUTANI GORO , CHINZEI NOBUO , WAKAMATSU YOSHIO , KARITA TAKESHI
IPC: G01M9/04
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公开(公告)号：JPH04271996A
公开(公告)日：1992-09-28
申请号：JP3285891
申请日：1991-02-27
Applicant: NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
Inventor： KUMAGAI TATSUO , SAITO TOSHIHITO , WAKAMATSU YOSHIO , SHINNO MASAYUKI , TOGAWA MORIHITO
Abstract: PURPOSE:To provide a high speed flight body applied with the diamond coating having the high heat conductivity at the top edge, in order to efficiently disperse the aerodynamic heating. CONSTITUTION:A high speed flight body having the high relative speed for air such as a space shuttle and aircraft has the diamond coating which is characterized by the application on the top edge surface.
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公开(公告)号：JPH0712708A
公开(公告)日：1995-01-17
申请号：JP15230193
申请日：1993-06-23
Applicant: NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
Inventor： SAKURANAKA NOBORU , WAKAMATSU YOSHIO , SHINNO MASAYUKI , ADACHI NAOTO
Abstract: PURPOSE:To evaluate a heat-resistant material and a cooling structure test specimen in severer aerodynamic heating environment by generating a hotter high-speed gas flow. CONSTITUTION:In a hot gas flow evaluation test device in which a fuel 2 is burned with oxidizing agent 3 in a combustor 1 to generate hot gas, the gas is led to a nozzle as it is and accelerated to a supersonic speed, and a test specimen 6 is set in a high temperature and high speed gas flow 5 to make various types of evaluations, an arc heating device 11 is set in the downstream side from the combustor 1, and a hot gas generated by combustion of the fuel 2 and oxidizing agent 3 in the combustor 1 is further heated.
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Patent Agency Ranking
公开(公告)号：JPH03258958A
公开(公告)日：1991-11-19
申请号：JP5417390
申请日：1990-03-06
Applicant: NAT AEROSPACE LAB
Inventor： KUDO KENJI , MURAKAMI JUNRO , KOMURO TOMOYUKI , TANIKOU ICHIROU , MASUTANI GORO , CHINZEI NOBUO , WAKAMATSU YOSHIO , KARITA TAKESHI
Abstract: PURPOSE:To maintain the efficient working condition over a wide range of the number of mat without a complex mechanism and a control circuit by mixing the combustion inhibitor and the combustion accelerator in the fuel for scram jet, and adjusting a mixing quantity of the both to control the progress of the combustion in a scram jet combustor, and controlling the working condition. CONSTITUTION:The combustion inhibitor 4 and/or the combustion accelerator 5 are mixed in the fuel 2 for scram jet, and a mixing quantity of the both is adjusted to control the progress of the combustion in a scram jet combustor 1, and the working condition is controlled with control valves 6 - 8. At this stage, halone, carbon dioxide, alkali metal compound powder and water or the like is used as the combustion inhibitor 4, and silane, alkyl aluminium and hydrazine or the like is used as the combustion accelerator 5.
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公开(公告)号：JPH09229025A
公开(公告)日：1997-09-02
申请号：JP6385496
申请日：1996-02-27
Applicant: NAT AEROSPACE LAB
Inventor： KARITA TAKESHI , ONO FUMIE , SAITO TOSHIHITO , WAKAMATSU YOSHIO , SUNAMI TETSUHARU
Abstract: PROBLEM TO BE SOLVED: To restrain pressure from increasing after reflection of shock wave by forming a secondary flow layer through application of injection or the like of secondary flow along a wall surface onto a part where the shock wave generated in a supersonic flow field reaches the wall surface. SOLUTION: A rocket engine 1 is provided with a secondary flow injection port 3 formed circularly which injects a secondary flow along the upstream to the downstream wall surface so that a secondary flow layer is formed, at a part where shock wave 6 of nozzle skirt 2 is reflected. A downstrem stage is formed at a circumferential wall and the port 3 is made open at the stepped wall. In the Fig. numerals 5, 7 denote a combustion unit and swelling wave, respectively. The engine 1 is so constituted in this way. Pressure increase after the reaction is restrained and the shock wave 6 after the reaction can be weakened by making a secondary flow layer reflect the shock wave 6, the secondary flow layer being formed by injecting the secondary flow, especially subsonic gas, along the wall surface, to a part where the shock wave 6 is incident to the wall surface.
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公开(公告)号：JPH07243350A
公开(公告)日：1995-09-19
申请号：JP5256994
申请日：1994-02-28
Applicant: NAT AEROSPACE LAB
Inventor： KAN AKIO , KATOU SHIYUUTOKU , WAKAMATSU YOSHIO , KARITA TAKESHI
Abstract: PURPOSE:To enable both increase in large propulsion force required at launching and specific impulse after rising despite of one engine without changing nozzles and propellants. CONSTITUTION:A combined cycle rocket engine is provided with a circuit for supplying liquid oxygen LOX and liquid hydrogen LH to a main combustion chamber 9 of an engine by a pump 12, a circuit for supplying a part of these propellants to a gas generator 13 for driving a turbine and discharging gas from an auxiliary nozzle 10 after driving the turbine 11 by generation gas, and a circuit for supplying liquid hydrogen which is vaporized after fed to the main combustion chamber and the nozzle by the pump for cooling so as to drive the turbine, to the main combustion chamber. Gas generator cycle and expander cycle are thus changed by valves 1-8 provided in respective circuits so that at first when it is launched, the gas generator cycle is used and after rising, the expander cycle is used.
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公开(公告)号：JPH0510854A
公开(公告)日：1993-01-19
申请号：JP16437991
申请日：1991-07-04
Applicant: NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
Inventor： KUMAGAI TATSUO , SAKURANAKA NOBORU , UEDA SHUICHI , SAITO TOSHIHITO , KUSAKA KAZUO , WAKAMATSU YOSHIO , SHINNO MASAYUKI , ADACHI NAOTO , NAGATA SATOSHI , SAKAMOTO AKIRA
Abstract: PURPOSE:To enable a large heat-resistance material and a sample such as a cooling structure to be heated for achieving an evaluation test by allowing a high-temperature high-speed gas to be discharged by receiving supply of a fuel and an oxidizer and this gas flow to be directed toward the sample. CONSTITUTION:A high-temperature high-speed gas is generated by allowing a fuel f to be combusted in a combustion equipment 10 and a gas flow is accelerated in a nozzle 11, thus forming a field of a high-temperature high-speed gas flow h. Then, a heat-resistance material, a sample 12 in cooling structure, etc., are installed within the field of this flow h and is heated, thus enabling them to be evaluated. Since this structure is based on a rocket-engine structure. a flow rate of a high-temperature gas can be set to a high level. thus enabling a test device to be large, especially an exit diameter of the nozzle 11 to be large. This increase in size allows a field of a large gas flow h to be formed, thus enabling the large heat-resistance material and the sample such as a cooling structure to be heated and evaluation test to be performed.
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公开(公告)号：JPH03255329A
公开(公告)日：1991-11-14
申请号：JP5417490
申请日：1990-03-06
Applicant: NAT AEROSPACE LAB
Inventor： MURAKAMI JUNRO , KOMURO TOMOYUKI , KUDO KENJI , TANI KOICHIRO , MASUTANI GORO , CHINZEI NOBUO , WAKAMATSU YOSHIO , KARITA TAKESHI
IPC: G01M9/04
Abstract: PURPOSE:To change the cross sectional area of a diffuser throat autonomously by moving the wall surfaces of the diffuser in response to the difference in pressure distributions in the vicinity of the diffuser throat before and after the diffuser throat. CONSTITUTION:First movable walls 2 and 2 are provided on a diffuser throat 4 in a diffuser (a). Second movable walls 3 and 3 constituting the throat 4 are provided at the downstream side of the walls 2 and 2. The throat 4 is kept at a specified interval with a spring system which is set in response to the inner pressure at the upstream side of the throat 4 before starting of the diffuser. When the steady-state operating state is obtained after the starting and the inner pressure at the upstream side of the throat 4 is decreased, the movable walls 2 and 2 are pushed inward with the spring system by the amount corresponding to the decreased amount of the inner pressure. The tips of the movable walls 3 and 3 are also pushed in response and moved inward. Thus, the cross sectional area of the throat 4 is decreased. Therefore, the throat 4 is expanded before the starting and contracted after the starting autonomously.
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