GB1320766A - Rocket propulsion system - Google Patents

Rocket propulsion system

Info

Publication number
GB1320766A
GB1320766A GB4755570A GB4755570A GB1320766A GB 1320766 A GB1320766 A GB 1320766A GB 4755570 A GB4755570 A GB 4755570A GB 4755570 A GB4755570 A GB 4755570A GB 1320766 A GB1320766 A GB 1320766A
Authority
GB
United Kingdom
Prior art keywords
propellants
lines
turbines
combustion chamber
propellant
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
GB4755570A
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.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg 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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of GB1320766A publication Critical patent/GB1320766A/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
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Supercharger (AREA)

Abstract

1320766 Rocket engines; supply of propellants MASCHINENFABRIK AUGSBURG-NURNBERG AG 6 Oct 1970 [7 Oct 1969] 47555/70 Addition to 1210601 Heading FIT The invention relates to a rocket propulsion system and is a modification or improvement in the invention of parent Specification 1210601. The system comprises a turbine connected to receive, on ignition, one of the propellants in its gaseous form before this propellant reaches the injection nozzle means, the turbine being arranged to drive a propellant supply pump. In the embodiment shown two propellant tanks 14, 19 are provided, the tanks being insulated and the propellants such as hydrogen and oxygen being stored in liquefied form. The system comprises also a combustion chamber and propulsion nozzle assembly 1, 2 there being passages 8, 9 in the walls thereof for flow of propellants for cooling purposes. At starting propellants flows through lines 69, 70 which are uninsulated so that the liquid propellants are vapourized and pass through non-return valves 61, 62 to lines 71, 72 thence through passages 9, 8, all respectively, in the walls of the combustion chamber and nozzle assembly, then passing to turbines 67, 68 to drive them. The propellants discharge from the turbines 67, 68 through lines 73, 74 and pass through valves 4, 5 and nozzles 6, 7 into the combustion chamber. The turbines 67, 68 drive propellant pumps 65, 66 which in normal operation receive liquid propellants through lines 75, 76 and valves 63, 64, the pumps discharging the propellants through lines 77, 78 into the lines 71, 72 and so to the coolant passages 9, 8, turbines 67, 68 and so into the combustion chamber.
GB4755570A 1969-10-07 1970-10-06 Rocket propulsion system Expired GB1320766A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19691950407 DE1950407B2 (en) 1969-10-07 1969-10-07 FUEL SUPPLY SYSTEM FOR A ROCKET ENGINE

Publications (1)

Publication Number Publication Date
GB1320766A true GB1320766A (en) 1973-06-20

Family

ID=5747482

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4755570A Expired GB1320766A (en) 1969-10-07 1970-10-06 Rocket propulsion system

Country Status (3)

Country Link
DE (1) DE1950407B2 (en)
FR (1) FR2031047A6 (en)
GB (1) GB1320766A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103133183A (en) * 2013-02-06 2013-06-05 北京航天试验技术研究所 Safe processing device of low-temperature hydrogen in rocket engine thrust chamber
US20140260181A1 (en) * 2011-10-11 2014-09-18 Snecma Jet propulsion device and fuel supply method
CN113404621A (en) * 2021-06-19 2021-09-17 西北工业大学 Solid-liquid mixed engine and method for Mars ascending aircraft
CN113586286A (en) * 2021-07-08 2021-11-02 北京星途探索科技有限公司 Liquid oxygen methane propellant supply system
CN114030656A (en) * 2021-11-09 2022-02-11 西安交通大学 Novel variable-thrust nuclear heat propulsion system

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2743983C2 (en) * 1977-09-30 1982-11-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München By-pass liquid rocket engine for operation in a vacuum
US4583362A (en) * 1983-12-12 1986-04-22 Rockwell International Corporation Expander-cycle, turbine-drive, regenerative rocket engine
JPS62261652A (en) * 1986-05-07 1987-11-13 Natl Space Dev Agency Japan<Nasda> Liquid rocket engine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140260181A1 (en) * 2011-10-11 2014-09-18 Snecma Jet propulsion device and fuel supply method
US9771897B2 (en) * 2011-10-11 2017-09-26 Snecma Jet propulsion device and fuel supply method
CN103133183A (en) * 2013-02-06 2013-06-05 北京航天试验技术研究所 Safe processing device of low-temperature hydrogen in rocket engine thrust chamber
CN103133183B (en) * 2013-02-06 2015-11-04 北京航天试验技术研究所 A kind of thrust chamber low temperature hydrogen secure processing device
CN113404621A (en) * 2021-06-19 2021-09-17 西北工业大学 Solid-liquid mixed engine and method for Mars ascending aircraft
CN113404621B (en) * 2021-06-19 2022-08-16 西北工业大学 Solid-liquid mixed engine and method for Mars ascending aircraft
CN113586286A (en) * 2021-07-08 2021-11-02 北京星途探索科技有限公司 Liquid oxygen methane propellant supply system
CN114030656A (en) * 2021-11-09 2022-02-11 西安交通大学 Novel variable-thrust nuclear heat propulsion system

Also Published As

Publication number Publication date
DE1950407A1 (en) 1971-04-22
DE1950407B2 (en) 1972-03-30
FR2031047A6 (en) 1970-11-13

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees