FR2232685A1 - Fluid drive system for rockets - with pre-combustion chamber to raise oxydator-rich gas mixture, and based on main drive electrical system - Google Patents

Fluid drive system for rockets - with pre-combustion chamber to raise oxydator-rich gas mixture, and based on main drive electrical system

Info

Publication number
FR2232685A1
FR2232685A1 FR7419403A FR7419403A FR2232685A1 FR 2232685 A1 FR2232685 A1 FR 2232685A1 FR 7419403 A FR7419403 A FR 7419403A FR 7419403 A FR7419403 A FR 7419403A FR 2232685 A1 FR2232685 A1 FR 2232685A1
Authority
FR
France
Prior art keywords
main drive
rockets
combustion chamber
oxydator
raise
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
FR7419403A
Other languages
French (fr)
Other versions
FR2232685B1 (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.)
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
Priority claimed from DE19732329624 external-priority patent/DE2329624C3/en
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of FR2232685A1 publication Critical patent/FR2232685A1/en
Application granted granted Critical
Publication of FR2232685B1 publication Critical patent/FR2232685B1/fr
Granted 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
    • 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

Abstract

Two separate fuel transport systems are used for main drive rockets and auxiliary (steering) rockets superfluous resulting in considerable weight-advantage. Turbo-pump combination can supply both main drive and auxiliary-drive with fuel and oxidiser. Pre-combustion chamber of main drive is also gas generator of the auxiliary. If auxiliary is used, the fuel and oxidiser are evaporated in heat exchanger with gas from a gas generator which was supplied by same turbo-pump combination. Heat-exchanger is not in use when main drive is on full power.
FR7419403A 1973-06-09 1974-06-05 Fluid drive system for rockets - with pre-combustion chamber to raise oxydator-rich gas mixture, and based on main drive electrical system Granted FR2232685A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19732329624 DE2329624C3 (en) 1973-06-09 A missile system comprising a main flow liquid rocket engine and a plurality of control rocket engines

Publications (2)

Publication Number Publication Date
FR2232685A1 true FR2232685A1 (en) 1975-01-03
FR2232685B1 FR2232685B1 (en) 1979-04-20

Family

ID=5883635

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7419403A Granted FR2232685A1 (en) 1973-06-09 1974-06-05 Fluid drive system for rockets - with pre-combustion chamber to raise oxydator-rich gas mixture, and based on main drive electrical system

Country Status (3)

Country Link
JP (1) JPS5032308A (en)
FR (1) FR2232685A1 (en)
IN (1) IN141928B (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4589253A (en) * 1984-04-16 1986-05-20 Rockwell International Corporation Pre-regenerated staged-combustion rocket engine
EP0242196A1 (en) * 1986-04-16 1987-10-21 The Marconi Company Limited Thrusters
EP1022454A3 (en) * 1999-01-21 2002-07-17 Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie "Energomash", Imeni Akademika V.P. Glushko, Russian Fed. Liquid propellant rocket engine
WO2018017788A1 (en) * 2016-07-22 2018-01-25 Aerojet Rocketdyne, Inc. Boost turbo-pump with axially fed turbine
EP4155612A1 (en) * 2021-09-22 2023-03-29 Siec Badawcza Lukasiewicz-Instytut Lotnictwa Pre-combustion chamber for feeding a turbine in a liquid propellant rocket engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921979B1 (en) * 2007-10-08 2014-06-13 Astrium Sas DEVICE AND METHOD FOR PUMP MOTORIZATION FOR INTERNAL COMBUSTION ENGINE FUSE ENGINE
FR2998926B1 (en) * 2012-11-30 2014-12-26 Snecma PROPULSIVE ASSEMBLY FOR FUSEE

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
NEANT *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4589253A (en) * 1984-04-16 1986-05-20 Rockwell International Corporation Pre-regenerated staged-combustion rocket engine
EP0242196A1 (en) * 1986-04-16 1987-10-21 The Marconi Company Limited Thrusters
EP1022454A3 (en) * 1999-01-21 2002-07-17 Otkrytoe Aktsionernoe Obschestvo Nauchno-Proizvodstvennoe Obiedinenie "Energomash", Imeni Akademika V.P. Glushko, Russian Fed. Liquid propellant rocket engine
WO2018017788A1 (en) * 2016-07-22 2018-01-25 Aerojet Rocketdyne, Inc. Boost turbo-pump with axially fed turbine
US11002224B2 (en) 2016-07-22 2021-05-11 Aerojet Rocketdyne, Inc. Boost turbo-pump with axially fed turbine
EP4155612A1 (en) * 2021-09-22 2023-03-29 Siec Badawcza Lukasiewicz-Instytut Lotnictwa Pre-combustion chamber for feeding a turbine in a liquid propellant rocket engine

Also Published As

Publication number Publication date
DE2329624A1 (en) 1975-01-02
DE2329624B2 (en) 1975-06-19
FR2232685B1 (en) 1979-04-20
JPS5032308A (en) 1975-03-29
IN141928B (en) 1977-05-07

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Legal Events

Date Code Title Description
ST Notification of lapse