[특허]System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine

System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/00 F02K-009/97
출원번호	US-0119648 (2012-05-15)
등록번호	US-9494110 (2016-11-15)
우선권정보	FR-11 54454 (2011-05-23)
국제출원번호	PCT/FR2012/051091 (2012-05-15)
§371/§102 date	20140211 (20140211)
국제공개번호	WO2012/160297 (2012-11-29)
발명자 / 주소	David, Noël Pyre, Alain
출원인 / 주소	SNECMA
대리인 / 주소	Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보	피인용 횟수 : 0 인용 특허 : 23

초록 ▼

A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

대표청구항 ▼

1. A deployable nozzle for a rocket engine, the nozzle comprising: at least a stationary divergent segment;a movable divergent segment that is coaxial about the stationary divergent segment and is configured to move along the stationary divergent segment from a retracted position towards a deployed position; anda transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment. 2. A deployable nozzle according to claim 1, wherein the transverse stiffener extends in a transverse plane of the movable divergent segment. 3. A deployable nozzle according to claim 1, wherein the transverse stiffener comprises at least one tie extending diametrically and having two ends, each end being connected to a point of the periphery of the inside wall of the movable divergent segment. 4. A deployable nozzle according to claim 1, wherein the transverse stiffener comprises at least two ties extending radially from a primary central body. 5. A deployable nozzle according to claim 1, wherein the transverse stiffener comprises adjustment means for adjusting a prestress tension. 6. A deployable nozzle according to claim 1, wherein the transverse stiffener comprises at least one cord made of polymer fibers. 7. A deployable nozzle according to claim 1, wherein the transverse stiffener comprises fastener means for fastening to the movable divergent segment and secured to the movable divergent segment. 8. A deployable nozzle according to claim 1, wherein, in the retracted position, the transverse stiffener cooperates with a downstream end portion of the stationary divergent segment. 9. A deployable nozzle according to claim 1, wherein the stationary divergent segment and the movable divergent segment include, in a vicinity of their downstream ends, complementary centering means that cooperate with each other in the retracted position. 10. A deployable nozzle according to claim 9, wherein the transverse stiffener carries an annular centering skirt that cooperates with a downstream end portion of the stationary divergent segment in the retracted position by mutually engaging therewith. 11. A deployable nozzle according to claim 9, wherein the transverse stiffener comprises at least two ties extending radially from a primary central body while the downstream end of the stationary divergent segment carries a secondary central body with which the primary central body cooperates in the retracted position by mutual engagement therewith. 12. A deployable nozzle according to claim 11, wherein the stationary divergent segment includes a further transverse stiffener prestressed in tension comprising at least two ties extending radially in a vicinity of a downstream end of the stationary divergent segment, between at least two points of a periphery of an inside wall of the stationary divergent segment from the secondary central body. 13. A rocket engine comprising at least one deployable nozzle according to claim 1.

이 특허에 인용된 특허 (23)

Bruno Perrier FR; Jean-Luc Sans FR; Laurent Collignon FR, Deployable diverging part for a thruster.
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Kishimoto Kenji (Komaki JPX) Kakuma Yojiro (Komaki JPX) Yasui Masaaki (Komaki JPX), Expandable nozzle mechanism for a rocket engine.
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Kretschmer, Joachim, Extendible exhaust nozzle bell for a rocket engine.
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Jencek Premysl (Chatsworth CA), Extendible nozzle.
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Inman Frank S. (Brigham City UT), Extendible nozzle exit cone.
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Jencek Premysl (Chatsworth CA), Extendible rocket-engine nozzle.
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Inman, Frank S., Extendible thrust nozzle for rockets.
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Carey Lee F. (North Tonawanda NY), Extendible/expandable nozzle for rocket engines and the like and method of making same.
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Fage Etienne (Ramatuelle FRX), Gas ejection nozzle for a jet engine and a jet engine fitted with this nozzle, in particular an engine of the separate f.
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Wong, Joey; Chen, Peter; Stewart, Dana P.; Waxman, David N.; Mike, Michael A., Gas turbine engine systems involving I-beam struts.
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Elorriaga Vicario Javier,ESX ; Villanueva Salazar Miguel,ESX, Guiding mechanism for variable geometry vectoring nozzles.
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Miltenberger Louis E. (Ridgeley WV), Nested cone extendible nozzle system for a rocket motor.
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Klees Garry W. (Mercer Island WA), Plug-type exhaust nozzle having a variable centerbody and translating shroud.
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Flyborg Nils O. (Kristinehamn SEX) Bjrheden Orvar (Kristinehamn SEX), Propeller assembly.
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Szuminski Gary F. (Marietta GA) Pearson Charles R. (Marietta GA), Propulsion nozzle for gas turbine engine.
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Frosch Robert A. Administrator of the National Aeronautics and Space Administration ; with respect to an invention of ( Santa Clara CA) Dettling Joseph R. (Santa Clara CA), Retractable environmental seal.
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Hapke Donald W. (Issaquah WA), Retractable nozzle fairing system for aeroplane center boost engine.
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Bonniot Claude (Vernon FRX) Vuillamy Didier (Quincampoix FRX) Desclos Pierre (Vernon FRX) Tiret Etienne (La Chapelle Reanville FRX) Beaurain Andr (Chambly FRX), Rocket engine nozzle with an engine diffuser.
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Pacou Claude (Nancay FRX) Vuillamy Didier (Quincampoix FRX) Tiret Etienne (La Chapelle Reanville FRX) Desclos Pierre (Vernon FRX) Beaurain Andr (Chambly FRX), Rocket engine nozzle with selectively smaller outlet cross-section.
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Willis Kenneth E. (Litchfield Park AZ), Rocket motor nozzle extension system.
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Chatenet Luc H. (Vernon FRX) Desclos Pierre (Vernon FRX), Self-locking and reversible mechanism for deploying the diverging portion of a rocket engine nozzle.
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Jurich Umberto (Kirkland WA), Thrust reverser for high bypass jet engines.
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Donguy Paul (Bruges FRX), Unfoldable divergent nozzle for a rocket engine.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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연합인증

System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine 원문보기

초록 ▼

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System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine 원문보기

초록 ▼

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연구과제 타임라인

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이 특허에 인용된 특허 (23)

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