JPS59557U - Mainstream structure type liquid fuel rocket drive engine - Google Patents

Mainstream structure type liquid fuel rocket drive engine

Info

Publication number
JPS59557U
JPS59557U JP6088583U JP6088583U JPS59557U JP S59557 U JPS59557 U JP S59557U JP 6088583 U JP6088583 U JP 6088583U JP 6088583 U JP6088583 U JP 6088583U JP S59557 U JPS59557 U JP S59557U
Authority
JP
Japan
Prior art keywords
drive engine
combustion chamber
liquid fuel
container
structure type
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.)
Pending
Application number
JP6088583U
Other languages
Japanese (ja)
Inventor
ギユンテル・シユミツト
Original Assignee
メツセルシユミツト・ベルコウ・ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング
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 メツセルシユミツト・ベルコウ・ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング filed Critical メツセルシユミツト・ベルコウ・ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング
Publication of JPS59557U publication Critical patent/JPS59557U/en
Pending 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
    • 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

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)
  • Testing Of Engines (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)

Abstract

(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

【図面の簡単な説明】[Brief explanation of drawings]

図面は本考案による液体燃料ロケット機関の原理を略示
するブロック・ダイヤグラムである。 １・・・駆動機関、２・・・主燃焼室、３・・・ノズル
、４・・・酸化剤容器、５：燃料容器、６．７・・・予
備燃焼室、１３．１４・・・ポンプ。The drawing is a block diagram schematically illustrating the principle of a liquid-fueled rocket engine according to the invention. DESCRIPTION OF SYMBOLS 1... Drive engine, 2... Main combustion chamber, 3... Nozzle, 4... Oxidizer container, 5: Fuel container, 6.7... Preliminary combustion chamber, 13.14... pump.

Claims (1)

【実用新案登録請求の範囲】[Scope of utility model registration request] １箇もしくは２箇の予備燃焼室を有し、吸込側を推進燃
料容器に、そして流出側を予備燃焼室又は予備燃焼室と
主燃焼室に接続されているタービン・ポンプを備え、そ
の際推進燃料容器が予備燃焼室から分流したガス混合物
で加圧されそしてタービン・ポンプは導管系内の圧力損
失を補償し且つ予備燃焼室内に推進燃料を噴射するため
の過圧を提供するのみとなっている主流構造型式の低推
力用液体燃料ロケット駆動機関において、酸化剤容器４
を予備燃焼室６から分流した混合ガスで加圧することに
より流れ出す酸化剤の全量を、酸化剤ポンプ１３により
流動さす、燃料容器５を予備燃焼室７から分流した混合
ガスで加圧することにより流れ出す燃料の全量を、燃料
ポンプ１４により流動させることを特徴とする液体燃料
ロケット駆動機関。A turbine pump having one or two pre-combustion chambers and connected on the suction side to the propellant container and on the outlet side to the pre-combustion chamber or to the pre-combustion chamber and the main combustion chamber, in which case the propulsion The fuel container is pressurized with the gas mixture diverted from the precombustion chamber and the turbine pump only compensates for pressure losses in the ducting system and provides an overpressure for injecting the propellant into the precombustion chamber. In the mainstream structure type low-thrust liquid fuel rocket drive engine, the oxidizer container 4
The entire amount of the oxidizer flowing out by pressurizing the fuel container 5 with the mixed gas diverted from the pre-combustion chamber 6 is made to flow by the oxidizer pump 13. A liquid fuel rocket drive engine characterized in that the entire amount of liquid is caused to flow by a fuel pump 14.
JP6088583U 1972-08-23 1983-04-25 Mainstream structure type liquid fuel rocket drive engine Pending JPS59557U (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19722241383 DE2241383C3 (en) 1972-08-23 1972-08-23 Main flow type liquid rocket engine
DE22413838 1972-08-23

Publications (1)

Publication Number Publication Date
JPS59557U true JPS59557U (en) 1984-01-05

Family

ID=5854287

Family Applications (2)

Application Number Title Priority Date Filing Date
JP9393473A Pending JPS49108414A (en) 1972-08-23 1973-08-23
JP6088583U Pending JPS59557U (en) 1972-08-23 1983-04-25 Mainstream structure type liquid fuel rocket drive engine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
JP9393473A Pending JPS49108414A (en) 1972-08-23 1973-08-23

Country Status (4)

Country Link
JP (2) JPS49108414A (en)
DE (1) DE2241383C3 (en)
FR (1) FR2197117B3 (en)
GB (1) GB1439535A (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3209251C2 (en) * 1982-03-13 1984-04-05 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Method for pushing liquid in a container in a weightless state towards outflow openings and device for carrying out the method
DE3328117A1 (en) * 1983-08-04 1985-02-14 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Method for the operation of a bypass flow rocket engine
FR2728627B1 (en) * 1994-12-27 1997-03-14 Europ Propulsion TANK SELF-PRESSURIZATION
DE19958310C2 (en) * 1999-12-03 2002-01-17 Daimler Chrysler Ag Rocket engine for liquid fuels with a closed engine circuit
JP3870252B2 (en) * 2001-07-19 2007-01-17 独立行政法人 宇宙航空研究開発機構 Cavitation suppression pump system
JP5144365B2 (en) * 2008-05-13 2013-02-13 株式会社Ｉｈｉエアロスペース Propellant tank pressure control system
FR3009587B1 (en) * 2013-08-06 2015-08-28 Snecma PRESSURIZATION DEVICE FOR ERGOL TANKS OF A ROTOR MOTOR
JP6227931B2 (en) * 2013-08-21 2017-11-08 株式会社Ｉｈｉエアロスペース Two-stage combustion type two-component thruster
IT201700087235A1 (en) * 2017-07-28 2019-01-28 Angelo Minotti Space propulsion system
FR3101676B1 (en) * 2019-10-08 2021-10-15 Centre Nat Etd Spatiales Rocket propulsion set
CN112412660B (en) * 2020-12-03 2021-11-02 西安航天动力研究所 Space power system combining extrusion and electric pump auxiliary pressurization
CN114542315B (en) * 2022-01-18 2023-02-21 北京理工大学 Turbulent jet flow spontaneous combustion ignition engine
CN114941800B (en) * 2022-04-29 2024-05-17 北京航天试验技术研究所 Rocket combustible propellant filling platform and filling method

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3170295A (en) * 1963-04-09 1965-02-23 Hugh L Dryden Propellant tank pressurization system
DE977815C (en) * 1963-12-21 1970-12-03 Messerschmitt Boelkow Blohm Liquid rocket engine
GB1167948A (en) * 1967-06-03 1969-10-22 Rolls Royce Rocket Engine.
US3577735A (en) * 1969-11-05 1971-05-04 Bolkow Ges Mit Beschrankter Liquid fuel rocket engine construction

Also Published As

Publication number Publication date
DE2241383B2 (en) 1977-11-10
JPS49108414A (en) 1974-10-15
DE2241383C3 (en) 1978-07-27
DE2241383A1 (en) 1974-02-28
GB1439535A (en) 1976-06-16
FR2197117A1 (en) 1974-03-22
FR2197117B3 (en) 1976-07-16

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