FR2422831A1 - DEPLOYABLE DIVERGENT THRUSTER TUBE - Google Patents

DEPLOYABLE DIVERGENT THRUSTER TUBE

Info

Publication number
FR2422831A1
FR2422831A1 FR7803090A FR7803090A FR2422831A1 FR 2422831 A1 FR2422831 A1 FR 2422831A1 FR 7803090 A FR7803090 A FR 7803090A FR 7803090 A FR7803090 A FR 7803090A FR 2422831 A1 FR2422831 A1 FR 2422831A1
Authority
FR
France
Prior art keywords
deployable divergent
rings
relates
vehicles
deployable
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
FR7803090A
Other languages
French (fr)
Other versions
FR2422831B1 (en
Inventor
Max Jean-Pierre Calabro
Herve Yves Christian Girard
Jean-Claude Joseph Realland
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Priority to FR7803090A priority Critical patent/FR2422831A1/en
Priority to DE2903098A priority patent/DE2903098C2/en
Priority to IT19742/79A priority patent/IT1110084B/en
Priority to GB7903369A priority patent/GB2013787B/en
Publication of FR2422831A1 publication Critical patent/FR2422831A1/en
Application granted granted Critical
Publication of FR2422831B1 publication Critical patent/FR2422831B1/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
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/976—Deployable nozzles
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Moulding By Coating Moulds (AREA)
  • Tents Or Canopies (AREA)
  • Nonwoven Fabrics (AREA)

Abstract

L'invention concerne les tuyères de propulseurs. Elle a pour objet une tuyère à divergent déployable, composé d'une succession d'anneaux 22 à 25 alternativement souples et rigides. Ces anneaux, initialement, repliés en accordéon autour du corps de tuyère 10, peuvent être déployés, grâce à des vérins pyrotechniques 17, jusque dans des positions 22' à 25' où ils forment le divergent suivant le profil désiré pour celui-ci. Application à la réduction de l'encombrement de fusées, missiles ou engins embarqués à bord de véhicules aériens ou sous-marins.The invention relates to thruster nozzles. It relates to a nozzle with a deployable divergent, composed of a succession of rings 22 to 25 alternately flexible and rigid. These rings, initially folded in accordion around the nozzle body 10, can be deployed, thanks to pyrotechnic jacks 17, into positions 22 ′ to 25 ′ where they form the diverging portion according to the profile desired for the latter. Application to the reduction of the size of rockets, missiles or vehicles on board air or submarine vehicles.

FR7803090A 1978-02-03 1978-02-03 DEPLOYABLE DIVERGENT THRUSTER TUBE Granted FR2422831A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR7803090A FR2422831A1 (en) 1978-02-03 1978-02-03 DEPLOYABLE DIVERGENT THRUSTER TUBE
DE2903098A DE2903098C2 (en) 1978-02-03 1979-01-27 Engine nozzle with unfoldable outlet part
IT19742/79A IT1110084B (en) 1978-02-03 1979-01-30 EXPANDABLE DIVERGENT PROPULSOR NOZZLE
GB7903369A GB2013787B (en) 1978-02-03 1979-01-31 Propulsion unit nozzle with a folding divergent section

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7803090A FR2422831A1 (en) 1978-02-03 1978-02-03 DEPLOYABLE DIVERGENT THRUSTER TUBE

Publications (2)

Publication Number Publication Date
FR2422831A1 true FR2422831A1 (en) 1979-11-09
FR2422831B1 FR2422831B1 (en) 1981-03-20

Family

ID=9204201

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7803090A Granted FR2422831A1 (en) 1978-02-03 1978-02-03 DEPLOYABLE DIVERGENT THRUSTER TUBE

Country Status (4)

Country Link
DE (1) DE2903098C2 (en)
FR (1) FR2422831A1 (en)
GB (1) GB2013787B (en)
IT (1) IT1110084B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0018300B1 (en) * 1979-04-24 1982-04-28 AEROSPATIALE Société Nationale Industrielle Propulsion unit nozzle with folding divergent section
US5156337A (en) * 1990-02-09 1992-10-20 Societe Nationale Industrielle Et Aerospatiale Flexible and pressure-permeable heat protection device
EP0516519A1 (en) * 1991-05-30 1992-12-02 Societe Europeenne De Propulsion Selflocking, reversible mechanism for the deployment of a rocket nozzle cone
EP1365138A1 (en) * 2002-05-21 2003-11-26 Eads Launch Vehicles Plug nozzle with a foldable inner cone

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4387564A (en) * 1980-10-03 1983-06-14 Textron Inc. Extendible rocket engine exhaust nozzle assembly
US7966828B2 (en) * 2007-01-08 2011-06-28 United Technologies Corporation Variable area nozzle with woven sleeve extension
FR2944063B1 (en) * 2009-04-02 2014-04-25 Snecma DIVERGENT DEPLOYABLE OF PROPELLER
RU2647022C1 (en) * 2015-12-22 2018-03-13 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Rotary control nozzle with a flexible folding head
RU2712561C1 (en) * 2018-11-20 2020-01-29 Федеральное государственное бюджетное образовательное учреждение высшего образования Балтийский государственный технический университет "ВОЕНМЕХ" им. Д.Ф. Устинова (БГТУ "ВОЕНМЕХ") Rocket engine extension nozzle (versions)
CN110594044B (en) * 2019-10-17 2022-03-18 哈尔滨工程大学 Flexible extension spray tube with self-adaptive height
FR3105994A1 (en) * 2020-01-08 2021-07-09 Julien SENON Variable outlet section nozzle for rocket motor and rocket motor comprising such a nozzle

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526365A (en) * 1968-05-21 1970-09-01 T O Paine Collapsible nozzle extension for rocket engines
US3933310A (en) * 1974-07-11 1976-01-20 Thiokol Corporation Rocket nozzle construction and surfaces impervious to hot, high velocity gases

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3711027A (en) * 1971-03-17 1973-01-16 Textron Inc Extendible nozzle for rocket engines
US3951342A (en) * 1973-02-15 1976-04-20 Aerojet-General Corporation Extendible nozzle for a rocket motor or the like

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526365A (en) * 1968-05-21 1970-09-01 T O Paine Collapsible nozzle extension for rocket engines
US3933310A (en) * 1974-07-11 1976-01-20 Thiokol Corporation Rocket nozzle construction and surfaces impervious to hot, high velocity gases

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0018300B1 (en) * 1979-04-24 1982-04-28 AEROSPATIALE Société Nationale Industrielle Propulsion unit nozzle with folding divergent section
US5156337A (en) * 1990-02-09 1992-10-20 Societe Nationale Industrielle Et Aerospatiale Flexible and pressure-permeable heat protection device
EP0516519A1 (en) * 1991-05-30 1992-12-02 Societe Europeenne De Propulsion Selflocking, reversible mechanism for the deployment of a rocket nozzle cone
FR2677080A1 (en) * 1991-05-30 1992-12-04 Europ Propulsion SELF-LOCKING AND REVERSIBLE MECHANISM FOR DEPLOYING DIVERGENT OF MOTOR-ROCKET NOZZLE.
US5282576A (en) * 1991-05-30 1994-02-01 Societe Europeenne De Propulsion Self-locking and reversible mechanism for deploying the diverging portion of a rocket engine nozzle
EP1365138A1 (en) * 2002-05-21 2003-11-26 Eads Launch Vehicles Plug nozzle with a foldable inner cone
FR2840030A1 (en) * 2002-05-21 2003-11-28 Eads Launch Vehicles CENTRAL CORE NOZZLE MOTOR FOR SPACE LAUNCHER
US6901740B2 (en) 2002-05-21 2005-06-07 Eads Launch Vehicles Engine with a central spike for a space launcher

Also Published As

Publication number Publication date
GB2013787A (en) 1979-08-15
IT7919742A0 (en) 1979-01-30
DE2903098A1 (en) 1979-08-09
DE2903098C2 (en) 1982-06-24
FR2422831B1 (en) 1981-03-20
GB2013787B (en) 1982-04-21
IT1110084B (en) 1985-12-23

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Legal Events

Date Code Title Description
ST Notification of lapse