[특허]Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section

Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-029/06 F02K-001/72 B64D-027/18
출원번호	US-0516759 (2010-12-09)
등록번호	US-9409650 (2016-08-09)
우선권정보	FR-09 06159 (2009-12-18)
국제출원번호	PCT/FR2010/052655 (2010-12-09)
§371/§102 date	20120618 (20120618)
국제공개번호	WO2011/073551 (2011-06-23)
발명자 / 주소	Bellanger, Alexandre Bouillon, Florent Dubois, Laurent
출원인 / 주소	AIRCELLE
대리인 / 주소	Burris Law, PLLC
인용정보	피인용 횟수 : 0 인용 특허 : 22

초록 ▼

An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.

대표청구항 ▼

1. An aircraft nacelle comprising: a thrust reverser device comprising at least one movable cowl; a supporting structure configured to support the thrust reverser device, the supporting structure comprising: at least one base body extending along a longitudinal direction of the nacelle and made from a composite material, wherein open walls of the base body form an open L-shaped bending section such that the entire base body in the form of the open L-shaped bending section provides access to an inner surface of the supporting structure from outside of the supporting structure, and a plurality of reinforcements attached on the inner surface of the supporting structure and distributed along the longitudinal direction, the reinforcements comprising a plurality of cores and plies draping the cores, wherein the cores and the plies are integrated with at least one open wall of the base body and form a portion of the open L-shaped bending section. 2. The aircraft nacelle according to claim 1, wherein the base body is made using a resin infusion molding method. 3. The aircraft nacelle according to claim 1, further comprising at least one guide means of the rail type for slidingly mounting a movable cowl of the thrust reverser device. 4. The aircraft nacelle according to claim 1, wherein the supporting structure is connected to part of a panel of an inner fixed fairing structure of a turbojet engine. 5. The aircraft nacelle according to claim 4, wherein the panel of the inner fixed fairing structure is attached on the supporting structure. 6. The aircraft nacelle according to claim 5, wherein the panel of the inner fixed fairing structure is attached so as to close the open L-shaped bending section. 7. The aircraft nacelle according to claim 4, wherein the panel of the inner fixed fairing structure is integrated into the supporting structure. 8. The aircraft nacelle according to claim 1, further comprising at least one yoke or fitting for fastening to a load-bearing structure of the pylon type or another supporting structure. 9. The aircraft nacelle according to claim 8, wherein the supporting structure is a 12 o'clock beam. 10. The aircraft nacelle according to claim 8, wherein the supporting structure is a 6 o'clock beam. 11. The aircraft nacelle according to claim 1, wherein the supporting structure integrates at least one connecting portion for connecting to a front frame. 12. The aircraft nacelle according to claim 1, wherein the supporting structure integrates a fairing wall and forms inner aerodynamic lines with the faring wall inside a secondary flow circulation tunnel.

이 특허에 인용된 특허 (22)

Dumont, Jean-François; Lefort, Marc, Aerodynamic aft fairing of an aircraft engine suspension pylon.
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Kraft Kurt R. ; Vieth Gary L. ; Louden Peter J., Aircraft labyrinth fire seal.
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Sternberger, Joe; Lallement, Michael K., Apparatus and method for mounting a cascade support ring to a thrust reverser.
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Calder, David P.; Howarth, Graham F., Apparatus for facilitating access to a nacelle interior and method of assembling the same.
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Lair,Jean Pierre, Cascade reverser without blocker doors.
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Huggins,George L; Meyer,Brian J; Post,Lee J; Crook,Gordon R; Nelson,Scott N; Kampf,Stanley T; Heitmann,Aaron R; Wardak,Hafizullah; Allison,Daniel J; Camenzind,Joseph W, Cast unitized primary truss structure and method.
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Buchacher Daniel A. (Kirkland WA), Composite structure for thrust reverser torque box.
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Marche, Jacques Herve; Raison, Fabien, Engine attachment pylon comprising means of fastening spars and panels located outside the inner space in the box.
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Welch John M. ; Benton William E. ; Lobsinger Michael R., Engine nacelle outer cowl panel with integral track fairings.
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Ramlaoui, Jihad I.; Roberts, Stephen Michael; Forsey, David, Guide system for nacelle assembly.
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Roberts, Stephen Michael, Guide system for nacelle assembly.
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Seaquist John D. ; Culbertson Chris, Horizontally opposed trunnion forward engine mount system supported beneath a wing pylon.
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Welch, John M.; Schaefer, Henry Arnold; Tymes, Matthew Scott; Urban, Michael Patrick, Hybrid torque box for a thrust reverser.
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Benedetti, Brenda; Farrell, Robert S.; Leon, Luis R.; Lan, Justin H.; Booker, Garry A., Metallic sandwich structure having small bend radius.
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Aten, Michael Ray; Crawford, Sara, Nacelle.
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Asaki Sam Isamu ; Cooper Kenneth Jack ; Hamilton Gordon L. ; Johns Christopher J. ; Jones James R. ; McComb James G., Reverse thrust inlet vortex inhibitor.
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Powell Donald T., Strut-wing interface having dual upper links.
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Michel Christian Marie Jean FR; Pascal Lardy FR; Laurent Marcel Vicogne FR, Thrust reverser having a bypass vane-cascade and fitted with a stationary rear structure.
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Lecordix Jean-Loic,FRX ; Schreiber Laurent Claude Jacques,FRX, Thrust reverser with turning vanes capable of being superposed.
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Brian E. Barton, Translating independently mounted air inlet system for aircraft turbofan jet engine.
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Amkraut, Daniel M.; Layland, Michael John; James, Norman John, Translating variable area fan nozzle providing an upstream bypass flow exit.
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Canadas Marc,FRX, Turbojet pod with laminar flow.
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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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Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section 원문보기

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Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section 원문보기

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