FR2791398B1 - Tuyere de moteur fusee comportant un systeme de controle de separation de jet - Google Patents

Tuyere de moteur fusee comportant un systeme de controle de separation de jet

Info

Publication number
FR2791398B1
FR2791398B1 FR9903742A FR9903742A FR2791398B1 FR 2791398 B1 FR2791398 B1 FR 2791398B1 FR 9903742 A FR9903742 A FR 9903742A FR 9903742 A FR9903742 A FR 9903742A FR 2791398 B1 FR2791398 B1 FR 2791398B1
Authority
FR
France
Prior art keywords
fused
control system
separation control
engine nozzle
jet separation
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 - Fee Related
Application number
FR9903742A
Other languages
English (en)
Other versions
FR2791398A1 (fr
Inventor
Christian Francois Mi Dujarric
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Agence Spatiale Europeenne
Original Assignee
Agence Spatiale Europeenne
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 Agence Spatiale Europeenne filed Critical Agence Spatiale Europeenne
Priority to FR9903742A priority Critical patent/FR2791398B1/fr
Priority to US09/534,196 priority patent/US20020157399A1/en
Publication of FR2791398A1 publication Critical patent/FR2791398A1/fr
Application granted granted Critical
Publication of FR2791398B1 publication Critical patent/FR2791398B1/fr
Priority to US10/953,447 priority patent/US6996973B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • 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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
FR9903742A 1999-03-25 1999-03-25 Tuyere de moteur fusee comportant un systeme de controle de separation de jet Expired - Fee Related FR2791398B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR9903742A FR2791398B1 (fr) 1999-03-25 1999-03-25 Tuyere de moteur fusee comportant un systeme de controle de separation de jet
US09/534,196 US20020157399A1 (en) 1999-03-25 2000-03-24 Rocket engine nozzle comprising a jet separation control system
US10/953,447 US6996973B2 (en) 1999-03-25 2004-09-30 Method of achieving jet separation of an un-separated flow in a divergent nozzle body of a rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9903742A FR2791398B1 (fr) 1999-03-25 1999-03-25 Tuyere de moteur fusee comportant un systeme de controle de separation de jet

Publications (2)

Publication Number Publication Date
FR2791398A1 FR2791398A1 (fr) 2000-09-29
FR2791398B1 true FR2791398B1 (fr) 2001-05-18

Family

ID=9543635

Family Applications (1)

Application Number Title Priority Date Filing Date
FR9903742A Expired - Fee Related FR2791398B1 (fr) 1999-03-25 1999-03-25 Tuyere de moteur fusee comportant un systeme de controle de separation de jet

Country Status (2)

Country Link
US (2) US20020157399A1 (fr)
FR (1) FR2791398B1 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050138932A1 (en) * 2003-10-22 2005-06-30 Perricone Nicholas V. Aircraft protection method and system
FR2882401B1 (fr) * 2005-02-22 2007-05-11 Agence Spatiale Europeenne Dispositif et procede pour reduire les forces laterales non stationnaires agissant sur une tuyere d'un moteur de fusee
FR2882402B1 (fr) * 2005-02-22 2011-08-19 Agence Spatiale Europeenne Dispositif et procede pour reduire les forces laterales non stationnaires agissant sur une tuyere d'un moteur de fusee
KR20080024623A (ko) * 2006-09-14 2008-03-19 삼성전자주식회사 디스플레이장치 및 그 데이터 표시방법
US8984854B2 (en) * 2006-10-04 2015-03-24 Aecom Furnace and ductwork implosion interruption air jet system
US8065868B2 (en) * 2006-12-22 2011-11-29 Lockheed Martin Corporation System, method, and apparatus for control input prediction and state verification of fluidic vectoring exhaust in high performance aircraft
US20080264372A1 (en) * 2007-03-19 2008-10-30 Sisk David B Two-stage ignition system
US20110215204A1 (en) * 2007-06-20 2011-09-08 General Electric Company System and method for generating thrust
US20100019079A1 (en) * 2007-06-20 2010-01-28 General Electric Company Thrust generator for a rotary wing aircraft
US20080315042A1 (en) * 2007-06-20 2008-12-25 General Electric Company Thrust generator for a propulsion system
US9551296B2 (en) 2010-03-18 2017-01-24 The Boeing Company Method and apparatus for nozzle thrust vectoring
US20120145808A1 (en) * 2010-12-14 2012-06-14 The Boeing Company Method and apparatus for variable exhaust nozzle exit area
FR3080407B1 (fr) * 2018-04-18 2020-04-24 Centre National De La Recherche Scientifique Controle de transition de regime et de vectorisation de poussee dans une tuyere a galbe multiple par injection secondaire
US20240125291A1 (en) * 2022-10-14 2024-04-18 Innovative Rocket Technologies Inc. Rocket engine with dual contour nozzle

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3300978A (en) * 1962-06-18 1967-01-31 Lockheed Aircraft Corp Directional control means for rocket motor
US3273801A (en) * 1962-08-30 1966-09-20 Thiokol Chemical Corp Rocket acceleration and direction control by fluid injection
US3318532A (en) * 1964-04-29 1967-05-09 Gen Motors Corp Gas injection thrust vector control system for rocket engines
US3325103A (en) * 1964-08-05 1967-06-13 Aerospace Corp Thrust vector control for reaction engines
US3296799A (en) * 1965-08-27 1967-01-10 Thiokol Chemical Corp Thrust vector control system
US3374954A (en) * 1966-03-03 1968-03-26 Thiokol Chemical Corp Nozzle cooling and thrust vector control apparatus
US3426972A (en) * 1966-08-16 1969-02-11 Thiokol Chemical Corp Rocket motor thrust vector control apparatus
US3737103A (en) * 1969-08-28 1973-06-05 Trw Inc Digital liquid vector control system
US3995662A (en) * 1972-06-16 1976-12-07 Chandler Evans Inc. Fluidic switches
US3925982A (en) * 1973-09-11 1975-12-16 Martin Marietta Corp Fluid-dynamic shock ring for controlled flow separation in a rocket engine exhaust nozzle
DE2922576C2 (de) * 1979-06-02 1982-02-18 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Strahltriebwerk mit Schubvektorsteuerung
US4707981A (en) * 1986-01-27 1987-11-24 Rockwell International Corporation Variable expansion ratio reaction engine
US4754927A (en) * 1986-12-08 1988-07-05 Colt Industries Inc. Control vanes for thrust vector control nozzle
US5582000A (en) * 1989-02-08 1996-12-10 United Technologies Corporation Coolable rocket nozzle for a rocket engine
DE4343009C2 (de) * 1993-12-16 1996-06-13 Daimler Benz Aerospace Ag Einspritzvorrichtung, insbesondere für ein Strahltriebwerk

Also Published As

Publication number Publication date
US20020157399A1 (en) 2002-10-31
US6996973B2 (en) 2006-02-14
FR2791398A1 (fr) 2000-09-29
US20050178127A1 (en) 2005-08-18

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Legal Events

Date Code Title Description
ST Notification of lapse

Effective date: 20071130