ES8707328A1 - Dispositivo de cierre provisional de un orificio - Google Patents

Dispositivo de cierre provisional de un orificio

Info

Publication number
ES8707328A1
ES8707328A1 ES556566A ES556566A ES8707328A1 ES 8707328 A1 ES8707328 A1 ES 8707328A1 ES 556566 A ES556566 A ES 556566A ES 556566 A ES556566 A ES 556566A ES 8707328 A1 ES8707328 A1 ES 8707328A1
Authority
ES
Spain
Prior art keywords
plug
downstream
angle
hand
upstream
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
Application number
ES556566A
Other languages
English (en)
Other versions
ES556566A0 (es
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 Nationale des Poudres et Explosifs
Original Assignee
Societe Nationale des Poudres et Explosifs
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 Nationale des Poudres et Explosifs filed Critical Societe Nationale des Poudres et Explosifs
Publication of ES8707328A1 publication Critical patent/ES8707328A1/es
Publication of ES556566A0 publication Critical patent/ES556566A0/es
Expired 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
    • F02K9/978—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
  • Safety Valves (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Valve Device For Special Equipments (AREA)
  • Power-Operated Mechanisms For Wings (AREA)

Abstract

DISPOSITIVO PARA EL CIERRE PROVISIONAL DE UN ORIFICIO. CARACTERIZADO PORQUE UN ELEMENTO FRANGIBLE (4) SOLIDARIZA EL TAPON A LA ESTRUCTURA; PORQUE EL TAPON A LA ESTRUCTURA; PORQUE EL TAPON INCLUYE UNA SUPERFICIE DE APOYO SITUADA A UNA DISTANCIA DETERMINADA DE UN TOPE LONGITUDINAL HACIA ARRIBA (5) DE LA ESTRUCTURA; PORQUE EL ELEMENTO FRANGIBLE SE ROMPE BAJO EL EFECTO DE UNA PRESION HACIA ABAJO, INFERIOR A LA TERCERA PARTE DE LA PRESION DE COMBUSTION EN LA CAMARA (2); PORQUE LA DISTANCIA LONGITUDINAL ENTRE LA SUPERFICIE DE APOYO DEL TAPON Y EL TOPE HACIA ARRIBA (5) ES SUPERIOR AL ESPESOR LONGITUDINAL DEL ELEMENTO FRANGIBLE; Y PORQUE EL ELEMENTO FRANGIBLE ESTA CONSTITUIDO POR UNA CORONA PERIFERICA QUE PERTENECE AL TAPON EYECTABLE (3).
ES556566A 1985-07-03 1986-06-24 Dispositivo de cierre provisional de un orificio Expired ES8707328A1 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR8510131A FR2584456B1 (fr) 1985-07-03 1985-07-03 Dispositif de fermeture temporaire d'un orifice interne d'un propulseur

Publications (2)

Publication Number Publication Date
ES8707328A1 true ES8707328A1 (es) 1987-08-01
ES556566A0 ES556566A0 (es) 1987-08-01

Family

ID=9320911

Family Applications (1)

Application Number Title Priority Date Filing Date
ES556566A Expired ES8707328A1 (es) 1985-07-03 1986-06-24 Dispositivo de cierre provisional de un orificio

Country Status (6)

Country Link
EP (1) EP0211703B1 (es)
JP (1) JPH0670408B2 (es)
DE (1) DE3669563D1 (es)
ES (1) ES8707328A1 (es)
FR (1) FR2584456B1 (es)
NO (1) NO164435C (es)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU212932U1 (ru) * 2022-06-30 2022-08-12 федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н.Туполева-КАИ" Сопловая заглушка ракетного двигателя твердого топлива

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5148518B2 (ja) * 2009-01-22 2013-02-20 三菱重工業株式会社 ラムジェットロケットエンジンのポートカバー構造及びポート開口方法
CN104696104B (zh) * 2013-12-10 2016-08-31 上海新力动力设备研究所 固体火箭发动机挡环连接结构
CN106089493A (zh) * 2016-06-17 2016-11-09 上海新力动力设备研究所 一种导弹发动机尾喷管橡胶堵盖
CN109139296B (zh) * 2018-09-11 2020-01-24 中国人民解放军国防科技大学 火箭基组合循环发动机

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2177880A (en) * 1935-08-13 1939-10-31 Servel Inc Refrigeration
US3564845A (en) * 1968-09-19 1971-02-23 Thiokol Chemical Corp Membrane seal assembly for use with solid propellant rocket motors having selective zoning capabilities
DE2214802A1 (de) * 1972-03-25 1973-09-27 Dynamit Nobel Ag Feststoffraketenmotor
DE2230457C3 (de) * 1972-06-22 1981-05-27 Dynamit Nobel Ag, 5210 Troisdorf Zwischenwand für Raketentriebwerke
GB1468814A (en) * 1974-12-03 1977-03-30 Secr Defence Rocket propulsion motors
DE2458180A1 (de) * 1974-12-09 1976-06-10 Dynamit Nobel Ag Trennwand fuer raketentriebwerke
FR2376300A1 (fr) * 1976-12-28 1978-07-28 Luchaire Sa Dispositif pour la liaison entre deux etages d'un engin autopropulse
FR2376301A1 (fr) * 1976-12-28 1978-07-28 Luchaire Sa Engin autopropulse a etages separables
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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU212932U1 (ru) * 2022-06-30 2022-08-12 федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н.Туполева-КАИ" Сопловая заглушка ракетного двигателя твердого топлива

Also Published As

Publication number Publication date
EP0211703A1 (fr) 1987-02-25
JPS6210460A (ja) 1987-01-19
NO862649L (no) 1987-01-05
JPH0670408B2 (ja) 1994-09-07
FR2584456A1 (fr) 1987-01-09
NO164435B (no) 1990-06-25
FR2584456B1 (fr) 1987-10-02
NO862649D0 (no) 1986-07-01
DE3669563D1 (de) 1990-04-19
NO164435C (no) 1990-10-03
ES556566A0 (es) 1987-08-01
EP0211703B1 (fr) 1990-03-14

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