RU2004103185A - Увеличение тяги ракетного летательного аппарата внутри расширяющейся части сопла - Google Patents

Увеличение тяги ракетного летательного аппарата внутри расширяющейся части сопла Download PDF

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Publication number
RU2004103185A
RU2004103185A RU2004103185/06A RU2004103185A RU2004103185A RU 2004103185 A RU2004103185 A RU 2004103185A RU 2004103185/06 A RU2004103185/06 A RU 2004103185/06A RU 2004103185 A RU2004103185 A RU 2004103185A RU 2004103185 A RU2004103185 A RU 2004103185A
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RU
Russia
Prior art keywords
nozzle
rocket
supersonic
expanding part
secondary combustion
Prior art date
Application number
RU2004103185/06A
Other languages
English (en)
Other versions
RU2265132C2 (ru
Inventor
Мелвин Дж БАЛМАН (US)
Мелвин Дж БАЛМАН
Original Assignee
Эроджет-Джэнерел Корпорейшн (Us)
Эроджет-Джэнерел Корпорейшн
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 Эроджет-Джэнерел Корпорейшн (Us), Эроджет-Джэнерел Корпорейшн filed Critical Эроджет-Джэнерел Корпорейшн (Us)
Publication of RU2004103185A publication Critical patent/RU2004103185A/ru
Application granted granted Critical
Publication of RU2265132C2 publication Critical patent/RU2265132C2/ru

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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)

Claims (2)

1. Реактивная двигательная установка, содержащая: сверхзвуковое ракетное сопло, образованное сужающейся частью, горловиной и сверхзвуковой расширяющейся частью; и средства для вызывания сгорания внутри кольцевой зоны указанной сверхзвуковой расширяющейся части и только в указанной сверхзвуковой расширяющейся части посредством впрыска и сжигания жидкого ракетного топлива в указанной кольцевой зоне так, что происходит увеличение тяги, при этом указанные средства содержат множество инжекторов, расположенных в местах, распределенных вдоль окружности указанной сверхзвуковой расширяющейся части для впрыска жидкого топлива и жидкого окислителя по окружности в направлении друг друга в указанной кольцевой зоне.
2. Реактивная двигательная система по п.1, в которой указанное сверхзвуковое ракетное сопло является перерасширенным соплом.
RU2004103185/06A 2001-07-05 2002-06-28 Реактивная двигательная установка RU2265132C2 (ru)

Applications Claiming Priority (2)

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

Publications (2)

Publication Number Publication Date
RU2004103185A true RU2004103185A (ru) 2005-05-27
RU2265132C2 RU2265132C2 (ru) 2005-11-27

Family

ID=25411600

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2004103185/06A RU2265132C2 (ru) 2001-07-05 2002-06-28 Реактивная двигательная установка

Country Status (8)

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

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7296411B2 (en) * 2002-06-21 2007-11-20 Darko Segota Method and system for regulating internal fluid flow within an enclosed or semi-enclosed environment
US6983587B2 (en) * 2002-10-28 2006-01-10 James Shumate Method and apparatus for thrust augmentation for rocket nozzles
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
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
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
US20100019079A1 (en) * 2007-06-20 2010-01-28 General Electric Company Thrust generator for a rotary wing aircraft
US20080315042A1 (en) * 2007-06-20 2008-12-25 General Electric Company Thrust generator for a propulsion system
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
US20110219742A1 (en) * 2010-03-12 2011-09-15 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
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CA2996284A1 (en) 2015-09-02 2017-04-20 Jetoptera, Inc. Fluidic propulsive system
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
BR112019027805A2 (pt) 2017-06-27 2020-07-07 Jetoptera, Inc. configuração de sistema de decolagem e aterrissagem vertical para veículos aéreos
EP3829979A4 (en) * 2018-05-25 2022-05-18 Radian Aerospace, Inc. EARTH-TO-ORBIT TRANSPORTATION SYSTEM
EP3891376A4 (en) 2018-07-03 2022-10-26 Radian Aerospace, Inc. ROCKET ENGINES AND RELATED PROCEDURES
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

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2939275A (en) * 1954-02-24 1960-06-07 Unexcelled Chemical Corp Solid-fuel rocket type motor assemblies
US2952123A (en) * 1956-05-25 1960-09-13 Lockheed Aircraft Corp Directional controls for propulsive jets
US3032970A (en) * 1957-01-25 1962-05-08 Phillips Petroleum Co Disposable rocket motor
US2981059A (en) 1958-02-04 1961-04-25 Thompson Ramo Wooldridge Inc Dual thrust chamber rocket
US3128599A (en) * 1958-10-06 1964-04-14 Phillips Petroleum Co Solid-fluid rocket propellant system
US3095694A (en) * 1959-10-28 1963-07-02 Walter Hermine Johanna Reaction motors
US4137286A (en) 1960-08-12 1979-01-30 Aerojet-General Corporation Method of making dual-thrust rocket motor
US3091924A (en) * 1960-12-15 1963-06-04 United Aircraft Corp Gaseous nozzle boundary
US3120737A (en) * 1961-02-17 1964-02-11 David G Holloway Rocket motor propellant
US3147590A (en) * 1961-03-16 1964-09-08 Thompson Ramo Wooldridge Inc Reaction motor with nozzle vector control having ablative port means and cooled valve means
FR1322872A (fr) * 1962-02-08 1963-04-05 Bertin & Cie Procédé et dispositif de déviation du jet d'une fusée
US3374631A (en) * 1965-08-16 1968-03-26 Mcdonnell Aircraft Corp Combination subsonic and supersonic propulsion system and apparatus
US3698642A (en) * 1966-11-04 1972-10-17 Thiokol Chemical Corp Thrust vector control system
US3668872A (en) * 1967-01-30 1972-06-13 Albert T Camp Solid propellant rocket
US3759039A (en) * 1968-11-22 1973-09-18 Thiokol Chemical Corp Thrust control and modulation system
US3739984A (en) 1971-08-25 1973-06-19 Rohr Industries Inc Thrust augmenting and south suppressing apparatus and method
US4220001A (en) 1977-08-17 1980-09-02 Aerojet-General Corporation Dual expander rocket engine
US4223606A (en) 1978-08-21 1980-09-23 Aerojet-General Corporation Dual thrust rocket motor
US4574700A (en) * 1984-11-15 1986-03-11 The United States Of America As Represented By The Secretary Of The Air Force Solid rocket motor with nozzle containing aromatic amide fibers
FR2661454B1 (fr) * 1985-07-12 1994-02-11 Onera Perfectionnements apportes aux propulseurs de type statoreacteur.
FR2618488B1 (fr) 1987-07-20 1989-12-15 Europ Propulsion Divergent a rupture de galbe pour tuyere de moteur-fusee
FR2639404B1 (fr) 1988-11-21 1994-04-15 Propulsion Ste Europeenne Divergent de moteur-fusee a tuyere annulaire complementaire
FR2648518B1 (fr) * 1989-06-15 1991-08-30 Poudres & Explosifs Ste Nale Propulseur comprenant un bloc de propergol muni d'un canal central de section variable
US5220787A (en) 1991-04-29 1993-06-22 Aerojet-General Corporation Scramjet injector
US5463866A (en) 1993-12-30 1995-11-07 The Boeing Company Supersonic jet engine installation and method with sound suppressing nozzle
DE19651646C2 (de) 1996-12-12 2002-07-11 Deutsch Zentr Luft & Raumfahrt Verfahren zum Einblasen einer ersten und zweiten Brennstoffkomponente und Einblaskopf

Also Published As

Publication number Publication date
EP1402166A1 (en) 2004-03-31
DE60233051D1 (de) 2009-09-03
EP1402166A4 (en) 2004-08-18
US6568171B2 (en) 2003-05-27
EP1402166B1 (en) 2009-07-22
JP2004534172A (ja) 2004-11-11
RU2265132C2 (ru) 2005-11-27
ATE437302T1 (de) 2009-08-15
US20030005701A1 (en) 2003-01-09
JP4095021B2 (ja) 2008-06-04
WO2003004852A1 (en) 2003-01-16
UA74456C2 (ru) 2005-12-15

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20150629