FR2405456A1 - Missile teleguide avec dispositif pour engendrer un moment de tangage, de lacet et de roulis - Google Patents

Missile teleguide avec dispositif pour engendrer un moment de tangage, de lacet et de roulis

Info

Publication number
FR2405456A1
FR2405456A1 FR7828241A FR7828241A FR2405456A1 FR 2405456 A1 FR2405456 A1 FR 2405456A1 FR 7828241 A FR7828241 A FR 7828241A FR 7828241 A FR7828241 A FR 7828241A FR 2405456 A1 FR2405456 A1 FR 2405456A1
Authority
FR
France
Prior art keywords
moment
thrust
nozzle
missile
roll
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.)
Withdrawn
Application number
FR7828241A
Other languages
English (en)
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.)
Bayern Chemie Gesellschaft fuer Flugchemische Antriebe mbH
Original Assignee
Bayern Chemie Gesellschaft fuer Flugchemische Antriebe mbH
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 Bayern Chemie Gesellschaft fuer Flugchemische Antriebe mbH filed Critical Bayern Chemie Gesellschaft fuer Flugchemische Antriebe mbH
Publication of FR2405456A1 publication Critical patent/FR2405456A1/fr
Withdrawn legal-status Critical Current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
    • F02K9/80—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
    • 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
    • F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)

Abstract

Missile téléguidé comportant un statoréacteur, en particulier à propergol solide, constitué d'une partie chambre de combustion et d'une partie tuyère de poussée, et une commande du vecteur 5 de poussée agissant sur le jet et destinée à engendrer un moment de tangage, de lacet et de roulis. Le dispositif de commande du vecteur de poussée comporte, pour la commande du moment de tangage et de lacet, un mécanisme d'actionnement 22 réglant angulairement, par rapport à l'axe longitudinal A-A du missile 2, la partie de tuyère de poussé 10 réalisée sous la forme d'une tuyère pivotante 12, en combinaison avec un dispositif de commande à fluide, associé à la tuyère pivotante 12 et injectant dans le jet de poussée une quantité de fluide dosée avec production d'une impulsion de compression soumettant la tuyere 12 à un moment de roulis.
FR7828241A 1977-10-06 1978-10-03 Missile teleguide avec dispositif pour engendrer un moment de tangage, de lacet et de roulis Withdrawn FR2405456A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19772744897 DE2744897A1 (de) 1977-10-06 1977-10-06 Lenkflugkoerper

Publications (1)

Publication Number Publication Date
FR2405456A1 true FR2405456A1 (fr) 1979-05-04

Family

ID=6020761

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7828241A Withdrawn FR2405456A1 (fr) 1977-10-06 1978-10-03 Missile teleguide avec dispositif pour engendrer un moment de tangage, de lacet et de roulis

Country Status (4)

Country Link
DE (1) DE2744897A1 (fr)
FR (1) FR2405456A1 (fr)
GB (1) GB2005606B (fr)
IT (1) IT1099232B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112572840A (zh) * 2020-12-14 2021-03-30 兰州空间技术物理研究所 一种电推进***贮供单元及其制造方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9291410B2 (en) 2010-07-22 2016-03-22 Saab Ab Cooling device for cooling combustion gases from recoilless anti-tank weapons

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1316191A (fr) * 1962-02-26 1963-01-25 United Aircraft Corp Dispositif de commande pour appareil propulseur
US3147590A (en) * 1961-03-16 1964-09-08 Thompson Ramo Wooldridge Inc Reaction motor with nozzle vector control having ablative port means and cooled valve means
US3266732A (en) * 1963-09-03 1966-08-16 United Aircraft Corp Roll control system
US3270505A (en) * 1964-10-21 1966-09-06 Norman L Crabill Control system for rocket vehicles
GB1134835A (en) * 1965-12-06 1968-11-27 Us Navy Liquid injection thrust vectoring
US4063685A (en) * 1976-07-30 1977-12-20 The United States Of America As Represented By The Secretary Of The Army Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3147590A (en) * 1961-03-16 1964-09-08 Thompson Ramo Wooldridge Inc Reaction motor with nozzle vector control having ablative port means and cooled valve means
FR1316191A (fr) * 1962-02-26 1963-01-25 United Aircraft Corp Dispositif de commande pour appareil propulseur
US3266732A (en) * 1963-09-03 1966-08-16 United Aircraft Corp Roll control system
US3270505A (en) * 1964-10-21 1966-09-06 Norman L Crabill Control system for rocket vehicles
GB1134835A (en) * 1965-12-06 1968-11-27 Us Navy Liquid injection thrust vectoring
US4063685A (en) * 1976-07-30 1977-12-20 The United States Of America As Represented By The Secretary Of The Army Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
EXBK/73 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112572840A (zh) * 2020-12-14 2021-03-30 兰州空间技术物理研究所 一种电推进***贮供单元及其制造方法

Also Published As

Publication number Publication date
IT1099232B (it) 1985-09-18
GB2005606B (en) 1982-06-30
DE2744897A1 (de) 1979-04-19
IT7828403A0 (it) 1978-10-04
GB2005606A (en) 1979-04-25

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Legal Events

Date Code Title Description
ST Notification of lapse