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FR2402773A1 - Chambre de combustion de stato-fusee a booster integre - Google Patents

Chambre de combustion de stato-fusee a booster integre

Info

Publication number
FR2402773A1
FR2402773A1 FR7727097A FR7727097A FR2402773A1 FR 2402773 A1 FR2402773 A1 FR 2402773A1 FR 7727097 A FR7727097 A FR 7727097A FR 7727097 A FR7727097 A FR 7727097A FR 2402773 A1 FR2402773 A1 FR 2402773A1
Authority
FR
France
Prior art keywords
rocket
jet engine
combustion chamber
ram jet
chamber containing
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.)
Granted
Application number
FR7727097A
Other languages
English (en)
Other versions
FR2402773B1 (fr
Inventor
B Luscan
M Reichard
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.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP SA
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 Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Priority to FR7727097A priority Critical patent/FR2402773A1/fr
Priority to DE19782838206 priority patent/DE2838206A1/de
Priority to US05/940,146 priority patent/US4203284A/en
Publication of FR2402773A1 publication Critical patent/FR2402773A1/fr
Application granted granted Critical
Publication of FR2402773B1 publication Critical patent/FR2402773B1/fr
Granted 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)

Abstract

Chambre de combustion de stato-fusée à booster intégré. La chambre comprend une enveloppe interne 3 munie d'orifices latéraux 34 amont pour l'admission d'air et une tuyère aval 43 d'éjection des gaz de combustion, pour permettre un fonctionnement du stato-fusée en régime de croisière et une enveloppe externe 4, concentrique à l'enveloppe interne et fermée l'exclusion d'un seul orifice arrière d'éjection des gaz, pour permettre un fonctionnement du stato-fusée en régime de lancement. Des moyens de séparation sont prévus pour séparer de la chambre de combustion au moins une partie de l'enveloppe externe, à la fin du régime de lancement, afin d'assurer le dégagement des orifices latéraux amont de l'enveloppe interne.
FR7727097A 1977-09-07 1977-09-07 Chambre de combustion de stato-fusee a booster integre Granted FR2402773A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR7727097A FR2402773A1 (fr) 1977-09-07 1977-09-07 Chambre de combustion de stato-fusee a booster integre
DE19782838206 DE2838206A1 (de) 1977-09-07 1978-09-01 Brennkammer eines staustrahlrohres mit integrierter startrakete
US05/940,146 US4203284A (en) 1977-09-07 1978-09-06 Combustion chamber for a ramjet and booster rocket

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7727097A FR2402773A1 (fr) 1977-09-07 1977-09-07 Chambre de combustion de stato-fusee a booster integre

Publications (2)

Publication Number Publication Date
FR2402773A1 true FR2402773A1 (fr) 1979-04-06
FR2402773B1 FR2402773B1 (fr) 1980-04-04

Family

ID=9195132

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7727097A Granted FR2402773A1 (fr) 1977-09-07 1977-09-07 Chambre de combustion de stato-fusee a booster integre

Country Status (1)

Country Link
FR (1) FR2402773A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2574480A1 (fr) * 1984-12-10 1986-06-13 Matra Dispositif comportant une charge utile et un propulseur a tuyere deplacable longitudinalement
FR2755182A1 (fr) * 1996-10-30 1998-04-30 Aerospatiale Systeme d'obturation pour un orifice d'entree d'air dans la chambre de combustion d'un statoreacteur
FR2863665A1 (fr) * 1988-10-12 2005-06-17 Aerospatiale Statoreacteur a structure tubulaire et missile propulse par un tel statoreacteur
RU2670287C1 (ru) * 2016-07-15 2018-10-22 Акционерное общество "Федеральный научно-производственный центр "Алтай" Способ работы двухрежимного реактивного двигателя

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2883829A (en) * 1955-01-24 1959-04-28 Curtiss Wright Corp Rocket engine convertible to a ramjet engine
US3063240A (en) * 1960-08-22 1962-11-13 United Aircraft Corp Booster means for a ramjetrocket device
US3855789A (en) * 1968-04-05 1974-12-24 Us Navy Explosive coupling assembly
US3906719A (en) * 1968-08-19 1975-09-23 Aerojet General Co Rocket having movable secondary nozzle
US4050243A (en) * 1976-05-17 1977-09-27 The United States Of America As Represented By The Secretary Of The Navy Combination solid fuel ramjet injector/port cover

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2883829A (en) * 1955-01-24 1959-04-28 Curtiss Wright Corp Rocket engine convertible to a ramjet engine
US3063240A (en) * 1960-08-22 1962-11-13 United Aircraft Corp Booster means for a ramjetrocket device
US3855789A (en) * 1968-04-05 1974-12-24 Us Navy Explosive coupling assembly
US3906719A (en) * 1968-08-19 1975-09-23 Aerojet General Co Rocket having movable secondary nozzle
US4050243A (en) * 1976-05-17 1977-09-27 The United States Of America As Represented By The Secretary Of The Navy Combination solid fuel ramjet injector/port cover

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2574480A1 (fr) * 1984-12-10 1986-06-13 Matra Dispositif comportant une charge utile et un propulseur a tuyere deplacable longitudinalement
FR2863665A1 (fr) * 1988-10-12 2005-06-17 Aerospatiale Statoreacteur a structure tubulaire et missile propulse par un tel statoreacteur
FR2755182A1 (fr) * 1996-10-30 1998-04-30 Aerospatiale Systeme d'obturation pour un orifice d'entree d'air dans la chambre de combustion d'un statoreacteur
EP0839999A1 (fr) * 1996-10-30 1998-05-06 AEROSPATIALE Société Nationale Industrielle Système d'obturation pour un orifice d'entrée d'air dans la chambre de combustion d'un statoréacteur
WO1998019063A1 (fr) * 1996-10-30 1998-05-07 Aerospatiale Societe Nationale Industrielle Systeme d'obturation pour un orifice d'entree d'air dans la chambre de combustion d'un statoreacteur
US6116019A (en) * 1996-10-30 2000-09-12 Societe Nationale Industrielle Et Aerospatiale Sealing system for an air intake opening of a ram jet combustion chamber
RU2670287C1 (ru) * 2016-07-15 2018-10-22 Акционерное общество "Федеральный научно-производственный центр "Алтай" Способ работы двухрежимного реактивного двигателя

Also Published As

Publication number Publication date
FR2402773B1 (fr) 1980-04-04

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