ES2194820T3 - Sistema de obturacion para un orificio de un conducto, asi como estatorreactor y misil comprendiendo dicho sistema. - Google Patents
Sistema de obturacion para un orificio de un conducto, asi como estatorreactor y misil comprendiendo dicho sistema.Info
- Publication number
- ES2194820T3 ES2194820T3 ES01402054T ES01402054T ES2194820T3 ES 2194820 T3 ES2194820 T3 ES 2194820T3 ES 01402054 T ES01402054 T ES 01402054T ES 01402054 T ES01402054 T ES 01402054T ES 2194820 T3 ES2194820 T3 ES 2194820T3
- Authority
- ES
- Spain
- Prior art keywords
- shutter
- hole
- statorreactor
- projectile
- introduction path
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 230000006378 damage Effects 0.000 abstract 3
- 239000011521 glass Substances 0.000 abstract 3
- 238000007789 sealing Methods 0.000 abstract 3
- 238000002485 combustion reaction Methods 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/978—Closures for nozzles; Nozzles comprising ejectable or discardable elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Re-Forming, After-Treatment, Cutting And Transporting Of Glass Products (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
- Jet Pumps And Other Pumps (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
- Testing Of Engines (AREA)
- Toys (AREA)
- Motor Or Generator Cooling System (AREA)
Abstract
Sistema de obturación para un orificio (8) de una vía de introducción de aire (7) de una cámara de combustión (5) de un estatorreactor (2), comportando dicho sistema de obturación (16): - al menos un obturador (15) de cristal susceptible de obturar completamente dicho orificio (8); y - al menos un dispositivo de destrucción (17) susceptible de destruir dicho obturador (15) de cristal de manera que se abra dicho orificio (8), comprendiendo dicho dispositivo de destrucción (17) al menos un proyectil (18) y un medio de proyección (19) accionable, que es susceptible de proyectar dicho proyectil (18) y que está dispuesto fuera de dicha vía de introducción de aire (7) aunque orientado de manera que se pueda proyectar dicho proyectil sobre dicho obturador (15), caracterizado porque dicho obturador está situado encima de la vía de introducción de aire en el sentido (F) de flujo del aire en dicha vía de introducción de aire (7), y porque dicho proyectil (18) es susceptible de destruir dicho obturador (15) de cristal cuando es proyectado sobre este último de modo que, después de la destrucción del obturador (15), sea eyectado directamente fuera del estatorreactor.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0010983A FR2813344B1 (fr) | 2000-08-28 | 2000-08-28 | Systeme d'obturation pour un orifice d'un conduit, en particulier pour un orifice d'une voie d'introduction d'air dans la chambre de combustion d'un statoreacteur |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| ES2194820T3 true ES2194820T3 (es) | 2003-12-01 |
Family
ID=8853761
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ES01402054T Expired - Lifetime ES2194820T3 (es) | 2000-08-28 | 2001-07-30 | Sistema de obturacion para un orificio de un conducto, asi como estatorreactor y misil comprendiendo dicho sistema. |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US6557339B2 (es) |
| EP (1) | EP1184559B1 (es) |
| AT (1) | ATE242427T1 (es) |
| CA (1) | CA2356308C (es) |
| DE (1) | DE60100330T2 (es) |
| ES (1) | ES2194820T3 (es) |
| FR (1) | FR2813344B1 (es) |
| RU (1) | RU2209330C2 (es) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2819556B1 (fr) * | 2001-01-12 | 2003-04-04 | Aerospatiale Matra Missiles | Systeme d'obturation pour un orifice d'un conduit, en particulier pour un orifice d'une voie d'introduction d'air dans la chambre de combustion d'un statoreacteur |
| FR2840029B1 (fr) * | 2002-05-27 | 2004-08-13 | Mbdam | Systeme d'obturation pour un orifice d'un conduit, en particulier pour un orifice d'une voie d'introduction d'air dans la chambre de combustion d'un statoreacteur |
| US7506839B2 (en) * | 2005-11-30 | 2009-03-24 | United Technologies Corporation | Engine airframe J-seal damper |
| RU2325544C2 (ru) * | 2006-06-22 | 2008-05-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Интегральный ракетно-прямоточный двигатель (ирпдт) |
| US8056319B2 (en) * | 2006-11-10 | 2011-11-15 | Aerojet—General Corporation | Combined cycle missile engine system |
| DE102008017962B4 (de) * | 2008-04-08 | 2012-09-06 | Eurocopter Deutschland Gmbh | Vorrichtung zur Zuführung von Verbrennungsluft zu einem Triebwerk eines Luftfahrzeuges |
| US9032737B2 (en) | 2009-12-30 | 2015-05-19 | Rolls-Royce North American Technologies, Inc. | Combustor added to a gas turbine engine to increase thrust |
| FR2966127B1 (fr) * | 2010-10-15 | 2013-06-14 | Airbus Operations Sas | Nacelle d'aeronef incorporant au moins une cloison radiale entre deux conduits |
| US10077669B2 (en) | 2014-11-26 | 2018-09-18 | United Technologies Corporation | Non-metallic engine case inlet compression seal for a gas turbine engine |
| CN109339948B (zh) * | 2018-11-23 | 2021-01-08 | 江西洪都航空工业集团有限责任公司 | 弹用燃气涡轮发动机进气装置 |
| RU191818U1 (ru) * | 2019-02-19 | 2019-08-23 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Воздухозаборное устройство со сбрасываемой заглушкой воздушно-реактивного двигателя |
| RU2714462C1 (ru) * | 2019-02-19 | 2020-02-17 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Воздухозаборное устройство со сбрасываемой заглушкой воздушно-реактивного двигателя |
| RU197364U1 (ru) * | 2019-10-31 | 2020-04-23 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Воздухозаборное устройство со сбрасываемой заглушкой беспилотного летательного аппарата с воздушно-реактивным двигателем |
| RU2733640C1 (ru) * | 2019-11-13 | 2020-10-05 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Сбрасываемый пиропривод с заглушкой для воздухозаборных устройств беспилотных летательных аппаратов с воздушно-реактивным двигателем |
| CN113202655B (zh) * | 2021-06-07 | 2022-05-24 | 北京理工大学 | 一种固液冲压组合发动机 |
Family Cites Families (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3038303A (en) * | 1958-01-02 | 1962-06-12 | Robert O Gose | Thrust termination in solid propellant rockets |
| US3768255A (en) * | 1967-03-06 | 1973-10-30 | Texaco Inc | Inlet port covers for reaction vehicle |
| DE1626069B1 (de) * | 1967-10-18 | 1970-10-08 | Messerschmitt Boelkow Blohm | Kombinationstriebwerk |
| GB1378079A (en) * | 1972-05-22 | 1974-12-18 | Ici Ltd | Bursting disc assembly |
| US3901028A (en) * | 1972-09-13 | 1975-08-26 | Us Air Force | Ramjet with integrated rocket boost motor |
| US3938764A (en) * | 1975-05-19 | 1976-02-17 | Mcdonnell Douglas Corporation | Frangible aircraft floor |
| US4028886A (en) * | 1975-10-23 | 1977-06-14 | Mcdonnell Douglas Corporation | Passive chamber wall fragmenter |
| US4441312A (en) * | 1979-06-22 | 1984-04-10 | The United States Of America As Represented By The Secretary Of The Air Force | Combined cycle ramjet engine |
| DE3003004C2 (de) | 1980-01-29 | 1982-06-03 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Deckel aus leicht zerstörbarem Material zum Verschließen der in die Brennkammer von kombinierten Staustrahl-Raketentriebwerken einmündenden Lufteinlauföffnungen, und Schlagvorrichtung zum Zerstören des Deckels |
| DE3002977C2 (de) * | 1980-01-29 | 1982-11-11 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Deckel aus leicht zerstörbarem Material zum Verschließen der in die Brennkammer von Staustrahl-Raketentriebwerken einmündenden Lufteinlauföffnungen, mit pyrotechnisch funktionierender Schlagvorrichtung zum Zerstören des Deckels |
| FR2549146B1 (fr) * | 1983-07-11 | 1987-12-24 | Europ Propulsion | Ensemble propulsif pour missile statoreacteur a propulseur d'acceleration integre |
| GB2165338B (en) * | 1984-10-06 | 1988-11-02 | Rolls Royce | Integral rocket and ramjet engine |
| JPH079216B2 (ja) * | 1989-07-24 | 1995-02-01 | 防衛庁技術研究本部長 | ラムロケット |
| FR2736684B1 (fr) * | 1995-07-12 | 1997-09-12 | Aerospatiale | Statoreacteur pour aeronef a vol supersonique et/ou hypersonique |
| FR2736685B1 (fr) * | 1995-07-13 | 1997-09-12 | Aerospatiale | Statoreacteur pour aeronef a vol supersonique et/ou hypersonique |
| FR2745606B1 (fr) * | 1996-03-01 | 1998-04-30 | Aerospatiale | Statoreacteur a geometrie evolutive pour aeronef |
| FR2755182B1 (fr) * | 1996-10-30 | 1998-12-31 | Aerospatiale | Systeme d'obturation pour un orifice d'entree d'air dans la chambre de combustion d'un statoreacteur |
| US5784877A (en) * | 1996-11-08 | 1998-07-28 | Atlantic Research Corporation | Rocket-ramjet engine casing port closure |
-
2000
- 2000-08-28 FR FR0010983A patent/FR2813344B1/fr not_active Expired - Lifetime
-
2001
- 2001-07-30 ES ES01402054T patent/ES2194820T3/es not_active Expired - Lifetime
- 2001-07-30 AT AT01402054T patent/ATE242427T1/de not_active IP Right Cessation
- 2001-07-30 DE DE2001600330 patent/DE60100330T2/de not_active Expired - Lifetime
- 2001-07-30 EP EP20010402054 patent/EP1184559B1/fr not_active Expired - Lifetime
- 2001-08-09 US US09/924,457 patent/US6557339B2/en not_active Expired - Lifetime
- 2001-08-27 RU RU2001123824A patent/RU2209330C2/ru active
- 2001-08-27 CA CA 2356308 patent/CA2356308C/fr not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| US6557339B2 (en) | 2003-05-06 |
| EP1184559A1 (fr) | 2002-03-06 |
| RU2209330C2 (ru) | 2003-07-27 |
| DE60100330D1 (de) | 2003-07-10 |
| US20020023428A1 (en) | 2002-02-28 |
| FR2813344A1 (fr) | 2002-03-01 |
| FR2813344B1 (fr) | 2002-11-29 |
| CA2356308A1 (fr) | 2002-02-28 |
| DE60100330T2 (de) | 2004-05-13 |
| CA2356308C (fr) | 2008-09-23 |
| EP1184559B1 (fr) | 2003-06-04 |
| ATE242427T1 (de) | 2003-06-15 |
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