GB2005606A - Rocket propulsion unit - Google Patents

Rocket propulsion unit

Info

Publication number
GB2005606A
GB2005606A GB7839345A GB7839345A GB2005606A GB 2005606 A GB2005606 A GB 2005606A GB 7839345 A GB7839345 A GB 7839345A GB 7839345 A GB7839345 A GB 7839345A GB 2005606 A GB2005606 A GB 2005606A
Authority
GB
United Kingdom
Prior art keywords
propulsion unit
rocket propulsion
stream
produce
apertures
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
GB7839345A
Other versions
GB2005606B (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 GB2005606A publication Critical patent/GB2005606A/en
Application granted granted Critical
Publication of GB2005606B publication Critical patent/GB2005606B/en
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
    • F02K9/80—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

Abstract

A rocket propulsion unit for a guided missile has means 22 to adjust a part 12 of the thrust nozzle angularly to produce yaw and pitch moments, and means 38, 42 to controllably inject a fluid medium into the exhaust jet stream through apertures 32A-D to produce disturbance of the stream whereby a roll moment may be produced. <IMAGE>
GB7839345A 1977-10-06 1978-10-04 Rocket propulsion unit for a guided missile Expired GB2005606B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19772744897 DE2744897A1 (en) 1977-10-06 1977-10-06 STEERING BODY

Publications (2)

Publication Number Publication Date
GB2005606A true GB2005606A (en) 1979-04-25
GB2005606B GB2005606B (en) 1982-06-30

Family

ID=6020761

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7839345A Expired GB2005606B (en) 1977-10-06 1978-10-04 Rocket propulsion unit for a guided missile

Country Status (4)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012011853A1 (en) * 2010-07-22 2012-01-26 Saab Ab Cooling device for cooling combustion gases from recoilless anti-tank weapons

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112572840A (en) * 2020-12-14 2021-03-30 兰州空间技术物理研究所 Electric propulsion system storage and supply unit and manufacturing method thereof

Family Cites Families (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 (en) * 1962-02-26 1963-01-25 United Aircraft Corp Control device for propellant
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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012011853A1 (en) * 2010-07-22 2012-01-26 Saab Ab Cooling device for cooling combustion gases from recoilless anti-tank weapons
DE112010005752B4 (en) * 2010-07-22 2014-11-13 Saab Ab Cooling device for cooling combustion gases from recoilless anti-tank weapons
US9291410B2 (en) 2010-07-22 2016-03-22 Saab Ab Cooling device for cooling combustion gases from recoilless anti-tank weapons

Also Published As

Publication number Publication date
GB2005606B (en) 1982-06-30
IT7828403A0 (en) 1978-10-04
FR2405456A1 (en) 1979-05-04
IT1099232B (en) 1985-09-18
DE2744897A1 (en) 1979-04-19

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)
PCNP Patent ceased through non-payment of renewal fee