ATE437302T1 - Schubverstärkung eines raketenfahrzeugs mittels eines divergenten abschnitts in der schubdüse - Google Patents

Schubverstärkung eines raketenfahrzeugs mittels eines divergenten abschnitts in der schubdüse

Info

Publication number
ATE437302T1
ATE437302T1 AT02749714T AT02749714T ATE437302T1 AT E437302 T1 ATE437302 T1 AT E437302T1 AT 02749714 T AT02749714 T AT 02749714T AT 02749714 T AT02749714 T AT 02749714T AT E437302 T1 ATE437302 T1 AT E437302T1
Authority
AT
Austria
Prior art keywords
thrust
nozzle
divergent section
secondary combustion
increase
Prior art date
Application number
AT02749714T
Other languages
English (en)
Inventor
Melvin Bulman
Original Assignee
Aerojet General Co
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 Aerojet General Co filed Critical Aerojet General Co
Application granted granted Critical
Publication of ATE437302T1 publication Critical patent/ATE437302T1/de

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
    • 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
    • F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust 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
    • F02K9/97—Rocket nozzles
    • 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
    • F02K9/97—Rocket nozzles
    • F02K9/974—Nozzle- linings; Ablative coatings

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Body Structure For Vehicles (AREA)
AT02749714T 2001-07-05 2002-06-28 Schubverstärkung eines raketenfahrzeugs mittels eines divergenten abschnitts in der schubdüse ATE437302T1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/899,813 US6568171B2 (en) 2001-07-05 2001-07-05 Rocket vehicle thrust augmentation within divergent section of nozzle
PCT/US2002/020688 WO2003004852A1 (en) 2001-07-05 2002-06-28 Rocket vehicle thrust augmentation within divergent section of nozzle

Publications (1)

Publication Number Publication Date
ATE437302T1 true ATE437302T1 (de) 2009-08-15

Family

ID=25411600

Family Applications (1)

Application Number Title Priority Date Filing Date
AT02749714T ATE437302T1 (de) 2001-07-05 2002-06-28 Schubverstärkung eines raketenfahrzeugs mittels eines divergenten abschnitts in der schubdüse

Country Status (8)

Country Link
US (1) US6568171B2 (de)
EP (1) EP1402166B1 (de)
JP (1) JP4095021B2 (de)
AT (1) ATE437302T1 (de)
DE (1) DE60233051D1 (de)
RU (1) RU2265132C2 (de)
UA (1) UA74456C2 (de)
WO (1) WO2003004852A1 (de)

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US6983587B2 (en) * 2002-10-28 2006-01-10 James Shumate Method and apparatus for thrust augmentation for rocket nozzles
US6948306B1 (en) * 2002-12-24 2005-09-27 The United States Of America As Represented By The Secretary Of The Navy Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing
US7320285B1 (en) * 2005-03-31 2008-01-22 The United States Of America As Represented By The Secretary Of The Navy Safe and arm device and method of using the same
US6918243B2 (en) * 2003-05-19 2005-07-19 The Boeing Company Bi-propellant injector with flame-holding zone igniter
US7823376B2 (en) * 2005-09-13 2010-11-02 Aerojet-General Corporation Thrust augmentation in plug nozzles and expansion-deflection nozzles
US7565795B1 (en) 2006-01-17 2009-07-28 Pratt & Whitney Rocketdyne, Inc. Piezo-resonance igniter and ignition method for propellant liquid rocket engine
US8122703B2 (en) 2006-04-28 2012-02-28 United Technologies Corporation Coaxial ignition assembly
KR20080024623A (ko) * 2006-09-14 2008-03-19 삼성전자주식회사 디스플레이장치 및 그 데이터 표시방법
US7886516B2 (en) 2006-12-18 2011-02-15 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system
US20080264372A1 (en) * 2007-03-19 2008-10-30 Sisk David B Two-stage ignition system
US20080299504A1 (en) * 2007-06-01 2008-12-04 Mark David Horn Resonance driven glow plug torch igniter and ignition method
US20110215204A1 (en) * 2007-06-20 2011-09-08 General Electric Company System and method for generating thrust
US20080315042A1 (en) * 2007-06-20 2008-12-25 General Electric Company Thrust generator for a propulsion system
US20100019079A1 (en) * 2007-06-20 2010-01-28 General Electric Company Thrust generator for a rotary wing aircraft
US8814562B2 (en) * 2008-06-02 2014-08-26 Aerojet Rocketdyne Of De, Inc. Igniter/thruster with catalytic decomposition chamber
US8161725B2 (en) 2008-09-22 2012-04-24 Pratt & Whitney Rocketdyne, Inc. Compact cyclone combustion torch igniter
US8484980B1 (en) 2009-11-19 2013-07-16 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Dual-mode combustor
WO2011152912A2 (en) * 2010-03-12 2011-12-08 Firestar Engineering, Llc Supersonic combustor rocket nozzle
US20130199155A1 (en) * 2012-01-02 2013-08-08 Jordin Kare Rocket Propulsion Systems, and Related Methods
US20140182265A1 (en) * 2013-01-03 2014-07-03 Jordin Kare Rocket Propulsion Systems, and Related Methods
CN107208510B (zh) * 2015-02-28 2020-09-08 工机控股株式会社 发动机及发动机式作业机
KR102668106B1 (ko) 2015-09-02 2024-05-22 제톱테라 잉크. 이젝터 및 에어포일 구조체
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11181076B2 (en) 2016-03-03 2021-11-23 Kevin Michael Weldon Rocket engine bipropellant supply system including an electrolyzer
KR20200043980A (ko) 2017-06-27 2020-04-28 제톱테라 잉크. 항공 비히클용 수직 이륙 및 착륙 시스템을 위한 구성
EP3829979A4 (de) * 2018-05-25 2022-05-18 Radian Aerospace, Inc. Transportsystem von erde zu umlaufbahn
EP3891376A4 (de) 2018-07-03 2022-10-26 Radian Aerospace, Inc. Raketentriebwerke und zugehörige verfahren
US10807703B2 (en) * 2018-07-19 2020-10-20 General Electric Company Control system for an aircraft
US11976613B1 (en) * 2023-08-28 2024-05-07 Pivotal Space, Inc. Dual mode rocket engine with bipropellant injection in the nozzle

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Also Published As

Publication number Publication date
WO2003004852A1 (en) 2003-01-16
US6568171B2 (en) 2003-05-27
JP2004534172A (ja) 2004-11-11
EP1402166B1 (de) 2009-07-22
EP1402166A4 (de) 2004-08-18
RU2004103185A (ru) 2005-05-27
UA74456C2 (uk) 2005-12-15
JP4095021B2 (ja) 2008-06-04
EP1402166A1 (de) 2004-03-31
US20030005701A1 (en) 2003-01-09
DE60233051D1 (de) 2009-09-03
RU2265132C2 (ru) 2005-11-27

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