GB1439368A - Liquid propellant rocket propulsion unit - Google Patents

Liquid propellant rocket propulsion unit

Info

Publication number
GB1439368A
GB1439368A GB3257873A GB3257873A GB1439368A GB 1439368 A GB1439368 A GB 1439368A GB 3257873 A GB3257873 A GB 3257873A GB 3257873 A GB3257873 A GB 3257873A GB 1439368 A GB1439368 A GB 1439368A
Authority
GB
United Kingdom
Prior art keywords
hydrazine
rocket
fluorine
container
combustion chamber
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
GB3257873A
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 Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of GB1439368A publication Critical patent/GB1439368A/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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • 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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/68—Decomposition chambers
    • 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
    • F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

1439368 Rocket propulsion units MESSERSCHMITT BOLKOW BLOHM GmbH 9 July 1973 [23 Aug 1972] 32578/73 Heading F1J The invention relates to a liquid propellant rocket unit which may operate either as a single propellant unit or as a bi-propellant unit, the propellants comprising hydrazine and a cryogenic oxidizer such as fluorine, oxygen di-fluoride or a mixture of oxygen and fluorine. The rocket unit shown comprises a combustion chamber 3 and propulsion nozzle 4, a hydrazine container 5a and a cryogenic oxidizer container 5b, the two containers being pressurized from a reservoir 11. For single-propellant operation hydrazine passes from container 5a to a reaction chamber 6 where it is decomposed catalytically, the decomposition gases then passing through a heat exchanger 7 which is not in operation, through line 10 to the rocket combustion chamber 3 before discharging through nozzle 4. For bi-propellant operation, hydrazine flows to the decomposition chamber 6 as before then through the heat exchanger 7 where the decomposition products are cooled, the cooled products then passing through line 9 where they are utilized to cool the rocket combustion chamber and nozzle before entering the combustion chamber 3. Cryogenic oxidizer such as fluorine passes from container 5b direct to the heat exchanger 7 where it is utilized to cool the hydrazine decomposition products, the fluorine being vaporized thereby, the fluorine vapour then passing through line 8 into the combustion chamber 3 where it reacts with the hydrazine decomposition products. The rocket vehicle comprises also two groups of control rockets 13a, 13b, 13c and 14a, 14b, 14c which are supplied with hydrazine decomposition products from the chamber 6 through lines 17, 18, the control rockets having suitable control valves. Alternatively the control rockets may receive hydrazine direct from the container 5a, there being decomposition catalysts associated with each control rocket.
GB3257873A 1972-08-23 1973-07-09 Liquid propellant rocket propulsion unit Expired GB1439368A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19722241424 DE2241424C3 (en) 1972-08-23 1972-08-23 Method for operating a liquid rocket engine

Publications (1)

Publication Number Publication Date
GB1439368A true GB1439368A (en) 1976-06-16

Family

ID=5854307

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3257873A Expired GB1439368A (en) 1972-08-23 1973-07-09 Liquid propellant rocket propulsion unit

Country Status (3)

Country Link
DE (1) DE2241424C3 (en)
FR (1) FR2197118B1 (en)
GB (1) GB1439368A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2226999A (en) * 1988-12-16 1990-07-18 Gen Electric Spacecraft with increased stationkeeping fuel load
GB2272488A (en) * 1992-11-04 1994-05-18 Europ Propulsion System for feeding reignitable rocket engines
US5417049A (en) * 1990-04-19 1995-05-23 Trw Inc. Satellite propulsion and power system
GB2293627A (en) * 1990-04-19 1996-04-03 Trw Inc High performance dual mode rocket propulsion system
EP0919464A1 (en) * 1997-11-25 1999-06-02 TRW Inc. Spacecraft attitude and velocity control thruster system
WO2000058619A1 (en) * 1999-03-26 2000-10-05 Alliant Techsystems Inc. Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines
EP1172545A1 (en) * 2000-07-15 2002-01-16 Astrium GmbH Ignition system for combustion chambers in rocket engines
EP1283347A1 (en) * 2001-08-07 2003-02-12 L'AIR LIQUIDE, Société Anonyme à Directoire et Conseil de Surveillance pour l'Etude et l'Exploitation des Auxiliary propulsion system of a cryogenic launcher stage and launcher stage comprising such a system

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8609228D0 (en) * 1986-04-16 1986-05-21 Marconi Co Ltd Thrusters
GB8610849D0 (en) * 1986-05-02 1986-08-20 Marconi Co Ltd Gas thruster
EP0272284A1 (en) * 1986-06-19 1988-06-29 Hughes Aircraft Company Hybrid spacecraft control system
DE102005005156B4 (en) * 2005-02-04 2007-06-06 Astrium Gmbh engine
CN107701330B (en) * 2017-09-14 2019-08-09 北京控制工程研究所 A kind of system mixing ratio Active Control Method being not based on gas bypassing

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2226999B (en) * 1988-12-16 1992-05-27 Gen Electric Spacecraft with increased stationkeeping fuel load
US5263666A (en) * 1988-12-16 1993-11-23 General Electric Co. Spacecraft with increased stationkeeping fuel load
GB2226999A (en) * 1988-12-16 1990-07-18 Gen Electric Spacecraft with increased stationkeeping fuel load
US5572865A (en) * 1990-04-19 1996-11-12 Trw Inc. Satellite propulsion and power system
US5417049A (en) * 1990-04-19 1995-05-23 Trw Inc. Satellite propulsion and power system
GB2293627A (en) * 1990-04-19 1996-04-03 Trw Inc High performance dual mode rocket propulsion system
GB2293627B (en) * 1990-04-19 1996-08-21 Trw Inc High performance dual mode rocket propulsion system
GB2272488B (en) * 1992-11-04 1996-11-20 Europ Propulsion An optimized system for feeding a reignitable rocket engine
GB2272488A (en) * 1992-11-04 1994-05-18 Europ Propulsion System for feeding reignitable rocket engines
EP0919464A1 (en) * 1997-11-25 1999-06-02 TRW Inc. Spacecraft attitude and velocity control thruster system
WO2000058619A1 (en) * 1999-03-26 2000-10-05 Alliant Techsystems Inc. Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines
US6393830B1 (en) 1999-03-26 2002-05-28 Alliant Techsystems Inc. Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines
EP1172545A1 (en) * 2000-07-15 2002-01-16 Astrium GmbH Ignition system for combustion chambers in rocket engines
US6564542B2 (en) 2000-07-15 2003-05-20 Astrium Gmbh Ignition system for combustion chambers of rocket engines
EP1283347A1 (en) * 2001-08-07 2003-02-12 L'AIR LIQUIDE, Société Anonyme à Directoire et Conseil de Surveillance pour l'Etude et l'Exploitation des Auxiliary propulsion system of a cryogenic launcher stage and launcher stage comprising such a system
FR2828524A1 (en) * 2001-08-07 2003-02-14 Air Liquide PROPULSION SYSTEM ANNEX FOR LAUNCHER CRYOTECHNICAL STAGE AND LAUNCHER STAGE COMPRISING SUCH A SYSTEM

Also Published As

Publication number Publication date
DE2241424A1 (en) 1974-03-07
FR2197118A1 (en) 1974-03-22
DE2241424B2 (en) 1977-10-06
FR2197118B1 (en) 1978-01-06
DE2241424C3 (en) 1978-06-22

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee