RU2002100639A - Rocket engine chamber - Google Patents

Rocket engine chamber

Info

Publication number
RU2002100639A
RU2002100639A RU2002100639/06A RU2002100639A RU2002100639A RU 2002100639 A RU2002100639 A RU 2002100639A RU 2002100639/06 A RU2002100639/06 A RU 2002100639/06A RU 2002100639 A RU2002100639 A RU 2002100639A RU 2002100639 A RU2002100639 A RU 2002100639A
Authority
RU
Russia
Prior art keywords
housing
nozzle
welding
expanding
rocket engine
Prior art date
Application number
RU2002100639/06A
Other languages
Russian (ru)
Other versions
RU2220313C2 (en
Inventor
Армин ЗОВА
Original Assignee
Астриум Гмбх
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 DE19927734A external-priority patent/DE19927734C2/en
Application filed by Астриум Гмбх filed Critical Астриум Гмбх
Publication of RU2002100639A publication Critical patent/RU2002100639A/en
Application granted granted Critical
Publication of RU2220313C2 publication Critical patent/RU2220313C2/en

Links

Claims (4)

1. Корпус камеры (1) ракетного двигателя для космических аппаратов, который одним концом (3) закреплен на форсуночной головке (2) и состоит из корпуса (11) камеры сгорания из высокожаропрочной стали и корпуса расширяющегося сопла (17) из высокожаропрочной стали, отличающийся тем, что между корпусом (11) камеры сгорания и корпусом расширяющегося сопла (17) расположена сопловая часть (13), выполненная из сплава платины с иридием.1. The housing of the chamber (1) of the rocket engine for spacecraft, which at one end (3) is mounted on the nozzle head (2) and consists of the housing (11) of the combustion chamber made of high heat resistant steel and the casing of the expanding nozzle (17) made of high heat resistant steel, characterized the fact that between the housing (11) of the combustion chamber and the housing of the expanding nozzle (17) is the nozzle part (13) made of an alloy of platinum with iridium. 2. Корпус камеры по п.1, отличающийся тем, что корпус (11) камеры сгорания сваркой соединен через первое промежуточное кольцо (12) с сопловой частью (13), а сопловая часть (13) через второе промежуточное кольцо (14) сваркой соединена с корпусом расширяющегося сопла (17), при этом указанные первое (12) и второе (14) промежуточные кольца выполнены из сплава платины с родием.2. The camera body according to claim 1, characterized in that the body (11) of the combustion chamber is connected by welding through the first intermediate ring (12) to the nozzle part (13), and the nozzle part (13) through the second intermediate ring (14) is connected by welding with the housing of the expanding nozzle (17), wherein said first (12) and second (14) intermediate rings are made of an alloy of platinum with rhodium. 3. Корпус камеры по п.2, отличающийся тем, что сварные соединения получены методом электронно-лучевой сварки.3. The camera body according to claim 2, characterized in that the welded joints are obtained by electron beam welding. 4. Корпус камеры по п.2 или 3, отличающийся тем, что корпус расширяющегося сопла (17) имеет расширяющуюся сопловую часть (16) и кольцевой переходник (15), который сваркой соединен со вторым промежуточным кольцом (14), при этом кольцевой переходник (15) сваркой соединен с расширяющейся сопловой частью (16).4. The camera housing according to claim 2 or 3, characterized in that the housing of the expanding nozzle (17) has an expanding nozzle part (16) and an annular adapter (15), which is welded to the second intermediate ring (14), while the annular adapter (15) by welding is connected to the expanding nozzle portion (16).
RU2002100639/06A 1999-06-17 2000-06-06 Rocket engine chamber housing RU2220313C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19927734A DE19927734C2 (en) 1999-06-17 1999-06-17 Thrust chamber of a propulsion engine for satellites and transport devices for space applications
DE19927734.6 1999-06-17

Publications (2)

Publication Number Publication Date
RU2002100639A true RU2002100639A (en) 2003-08-20
RU2220313C2 RU2220313C2 (en) 2003-12-27

Family

ID=7911610

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2002100639/06A RU2220313C2 (en) 1999-06-17 2000-06-06 Rocket engine chamber housing

Country Status (6)

Country Link
US (1) US6705076B1 (en)
EP (1) EP1187979B1 (en)
JP (1) JP4394320B2 (en)
DE (2) DE19927734C2 (en)
RU (1) RU2220313C2 (en)
WO (1) WO2000079116A1 (en)

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US20070012370A1 (en) * 2005-07-18 2007-01-18 Honeywell International, Inc. Facetted high temperature thruster design
JP5098111B2 (en) * 2006-07-07 2012-12-12 独立行政法人物質・材料研究機構 Method for producing mold for glass press
US20080264372A1 (en) * 2007-03-19 2008-10-30 Sisk David B Two-stage ignition system
US8512808B2 (en) * 2008-04-28 2013-08-20 The Boeing Company Built-up composite structures with a graded coefficient of thermal expansion for extreme environment applications
KR101014787B1 (en) 2008-08-26 2011-02-14 한국항공우주연구원 A Head of the Liquid Rocket Thrust chamber
US8667776B2 (en) * 2009-02-23 2014-03-11 Raytheon Company Pellet-loaded multiple impulse rocket motor
RU2563289C1 (en) * 2014-05-13 2015-09-20 Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ им. М.В. Хруничева") Method of fabrication of internal shell of nozzle of combustion chamber of liquid-propellant rocket engine (lpre)
WO2019108306A1 (en) * 2017-12-02 2019-06-06 Aerojet Rocketdyne, Inc. Copper combustion chamber attached to injector by non-copper weld transition ring
CN110159456B (en) * 2019-04-16 2020-07-14 上海空间推进研究所 Rocket engine thrust chamber

Family Cites Families (19)

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US2405465A (en) * 1943-05-07 1946-08-06 Aerojet Engineering Corp Jet propulsion motor
US3044257A (en) * 1958-06-02 1962-07-17 Thiokol Chemical Corp Combustion chamber outer jacket
US3167909A (en) * 1961-04-24 1965-02-02 Thompson Ramo Wooldridge Inc Self-cooled rocket nozzle
US3443384A (en) * 1967-05-17 1969-05-13 Nasa Swirling flow nozzle
DE2166904A1 (en) * 1971-12-01 1976-07-08 Erno Raumfahrttechnik Gmbh Rocket motor suitable for diverse fuels - has propulsion nozzle axially adjustable in combustion chamber
CA1079078A (en) * 1977-05-25 1980-06-10 Michael N. Clark Rocket nozzle assembly
DE3300930C2 (en) * 1983-01-13 1986-06-12 Heraeus Elektroden GmbH, 6450 Hanau Apparatus parts, in particular in the form of rings, some of which are provided with a coating material, their manufacturing process and use
US4882904A (en) * 1988-03-24 1989-11-28 Aerojet-General Corporation Two stage rocket combustor
GB9418705D0 (en) * 1994-09-16 1994-11-16 Johnson Matthey Plc Improvements in high temperature articles
US5613299A (en) * 1994-11-09 1997-03-25 Ring; Peter J. Method of fabricating a rocket thrust chamber
EP0899447B1 (en) * 1997-08-29 2003-12-03 Hughes Electronics Corporation Attachment ring for a rocket combustion chamber
DE69812253T2 (en) * 1997-08-29 2004-02-05 Hughes Electronics Corp., El Segundo Manufacture of a rocket engine with a connector between the combustion chamber and injector
EP0899449B1 (en) * 1997-08-29 2003-03-12 Hughes Electronics Corporation Rocket engine having a transition attachment between a combustion chamber and an injector
US6138451A (en) * 1998-05-11 2000-10-31 Hughes Electronics Corporation Rocket engine with combustion chamber step structure insert, and its fabrication
US6138450A (en) * 1998-05-11 2000-10-31 Hughes Electronics Corporation Rocket engine with integral combustion chamber step structure and its fabrication
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US6397580B1 (en) * 1998-07-09 2002-06-04 Bi-Propellant Rocket Research Corporation High performance rocket engine having a stepped expansion combustion chamber and method of making the same
RU2158666C2 (en) * 1999-02-04 2000-11-10 Открытое акционерное общество НПО Энергомаш им. акад. В.П. Глушко Method of manufacturing welded-soldered structure
US6205661B1 (en) * 1999-04-15 2001-03-27 Peter John Ring Method of making a rocket thrust chamber

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