ATE242427T1 - Verschlusssystem für einen leitungseinlass, sowie staustrahltriebwerk und rakete mit einem solchen system - Google Patents

Verschlusssystem für einen leitungseinlass, sowie staustrahltriebwerk und rakete mit einem solchen system

Info

Publication number
ATE242427T1
ATE242427T1 AT01402054T AT01402054T ATE242427T1 AT E242427 T1 ATE242427 T1 AT E242427T1 AT 01402054 T AT01402054 T AT 01402054T AT 01402054 T AT01402054 T AT 01402054T AT E242427 T1 ATE242427 T1 AT E242427T1
Authority
AT
Austria
Prior art keywords
blanking
rocket
cap
jet engine
pipe inlet
Prior art date
Application number
AT01402054T
Other languages
English (en)
Inventor
Jean-Paul Demay
Laurent Carton
Original Assignee
Aerospatiale Matra Missiles
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Aerospatiale Matra Missiles filed Critical Aerospatiale Matra Missiles
Application granted granted Critical
Publication of ATE242427T1 publication Critical patent/ATE242427T1/de

Links

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)
  • Loading And Unloading Of Fuel Tanks Or Ships (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Toys (AREA)
  • Motor Or Generator Cooling System (AREA)
  • Re-Forming, After-Treatment, Cutting And Transporting Of Glass Products (AREA)
  • Testing Of Engines (AREA)
  • Jet Pumps And Other Pumps (AREA)
AT01402054T 2000-08-28 2001-07-30 Verschlusssystem für einen leitungseinlass, sowie staustrahltriebwerk und rakete mit einem solchen system ATE242427T1 (de)

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
ATE242427T1 true ATE242427T1 (de) 2003-06-15

Family

ID=8853761

Family Applications (1)

Application Number Title Priority Date Filing Date
AT01402054T ATE242427T1 (de) 2000-08-28 2001-07-30 Verschlusssystem für einen leitungseinlass, sowie staustrahltriebwerk und rakete mit einem solchen system

Country Status (8)

Country Link
US (1) US6557339B2 (de)
EP (1) EP1184559B1 (de)
AT (1) ATE242427T1 (de)
CA (1) CA2356308C (de)
DE (1) DE60100330T2 (de)
ES (1) ES2194820T3 (de)
FR (1) FR2813344B1 (de)
RU (1) RU2209330C2 (de)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
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
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
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
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)

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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
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
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
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

Also Published As

Publication number Publication date
CA2356308A1 (fr) 2002-02-28
ES2194820T3 (es) 2003-12-01
US6557339B2 (en) 2003-05-06
DE60100330D1 (de) 2003-07-10
EP1184559B1 (de) 2003-06-04
EP1184559A1 (de) 2002-03-06
CA2356308C (fr) 2008-09-23
DE60100330T2 (de) 2004-05-13
RU2209330C2 (ru) 2003-07-27
FR2813344A1 (fr) 2002-03-01
FR2813344B1 (fr) 2002-11-29
US20020023428A1 (en) 2002-02-28

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Legal Events

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RER Ceased as to paragraph 5 lit. 3 law introducing patent treaties