ATE437302T1 - Schubverstärkung eines raketenfahrzeugs mittels eines divergenten abschnitts in der schubdüse - Google Patents
Schubverstärkung eines raketenfahrzeugs mittels eines divergenten abschnitts in der schubdüseInfo
- 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
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)
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) |
Families Citing this family (31)
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 |
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 |
Family Cites Families (26)
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 |
-
2001
- 2001-07-05 US US09/899,813 patent/US6568171B2/en not_active Expired - Lifetime
-
2002
- 2002-06-28 JP JP2003510592A patent/JP4095021B2/ja not_active Expired - Fee Related
- 2002-06-28 RU RU2004103185/06A patent/RU2265132C2/ru not_active IP Right Cessation
- 2002-06-28 WO PCT/US2002/020688 patent/WO2003004852A1/en active Application Filing
- 2002-06-28 EP EP02749714A patent/EP1402166B1/de not_active Expired - Lifetime
- 2002-06-28 UA UA2004020744A patent/UA74456C2/uk unknown
- 2002-06-28 AT AT02749714T patent/ATE437302T1/de not_active IP Right Cessation
- 2002-06-28 DE DE60233051T patent/DE60233051D1/de not_active Expired - Lifetime
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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Legal Events
Date | Code | Title | Description |
---|---|---|---|
RER | Ceased as to paragraph 5 lit. 3 law introducing patent treaties |