飞机制造商相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
1	航空機乗務員用ミラー	PCT/JP2014/067449	2014-06-30	WO2016001993A1	2016-01-07	渡邉　剛; 竹田　尚永
ポケットに入れても嵩張らないコンパクトなサイズにしながら、使用時に鏡面の有効面積を大きく確保できるようにした航空機乗務員用ミラーを提供する。少なくとも鍵（９）とともに連結具（８）に保持される航空機乗務員用ミラー（１）のミラー本体（２）を縦長形状に形成し、このミラー本体（２）の長手方向の端部に幅方向中心（ＣＷ）から片側に離間した偏心位置に貫通穴（７）を設け、この貫通穴（７）に連結具（８）を挿通させる。貫通穴（７）が幅方向中心（ＣＷ）から両側方向に延びる長穴（７Ａ）であってもよい。
2	MIRROR FOR AIRCRAFT CREW MEMBERS	US15301746	2014-06-30	US20170027307A1	2017-02-02	Tsuyoshi Watanabe; Hisanaga TAKEDA
Provided is a mirror for aircraft crew members, whereby a large effective surface area of the mirror surface can be maintained during use even though the mirror is compact and does not feel bulky when placed inside a pocket. A mirror main body (2) of the mirror (1) for aircraft crew members is formed in a vertically long shape, said mirror (1) being held together with at least a key (9), by a coupling tool (8). A through-hole (7) is provided in an end section in the longitudinal direction of this mirror main body (2), at an eccentric position on one side away from the center (CW) in the width direction. The coupling tool (8) is inserted into this through-hole (7). The through-hole (7) can be a long hole (7A) that extends from the center (CW) in the width direction towards both sides.
3	RUDDER OF A COMMERICAL AIRCRAFT	US12136689	2008-06-10	US20100140393A1	2010-06-10	Klaus BENDER
A rudder of a commercial aircraft is provided that is divided along its longitudinal direction in at least one region and the parts of the rudder can be spread against the air flow surrounding the aircraft by means of an actuator in order to decelerate the aircraft.
4	Aircraft manueuver stabilizer	US60722256	1956-08-30	US2964269A	1960-12-13	BUXTON ELLIOTT R

5	Model airplane builders jig	US95587	1993-07-23	US5335900A	1994-08-09	Randall W. Bonde
A supporting holder for a model airplane or similar small device being worked on, The holder is adjustable in various directions so that the work piece can be turned over, turned at right angles to an original position and variously placed for easy manipulation. In at least one position, the holder is adjustable to set the model such as an airplane in a precise location so that the angle of incidence of the wing and of the tail surfaces can be accurately set.
6	穴開け装置およびこれを用いて製造された航空機	JP2013148801	2013-07-17	JP2015020232A	2015-02-02	YANAGIHARA HIDEYASU
【課題】航空機の主翼の付け根のような狭隘部の奥であっても、正確且つ容易に穴開け加工を行うことができる穴開け装置を提供する。【解決手段】穴開け装置1は、ワーク(102,103)表面の穴開け基準線CLに平行して延びる長尺状であり、穴開け基準線CLの上に重ならず、且つ平行にワーク表面に固定されるガイド部材2と、このガイド部材2の長手方向に沿って摺動自在なドリル保持部材3と、ドリル保持部材3に取り付けられるドリルユニット4とを備え、ドリルユニット4は、そのドリル刃6を穴開け基準線CL上に位置させた状態で、該ドリル刃6をワークの表面に対して離接方向に移動させるように構成され、ガイド部材2とドリル保持部材3との間には、ドリル刃6を穴開け基準線CL上の各穴開け位置に合致させるように、ドリル保持部材3をガイド部材2の長手方向の所定の位置に位置決めして固定する位置決め固定部55が設けられている。【選択図】図8
7	Material having fine crystal grain useful as stringer of airplane and its manufacture	JP21679482	1982-12-13	JPS5941434A	1984-03-07	BABA YOSHIO; UNO TERUO; YOSHIDA HIDEO
PURPOSE: To obtain the titled material having the size of crystal grains below 100μm useful as the stringer of an airplane, by cold-joggling an alloy prepd. by mixing the specified amounts of Zn, Mg, Cu, Ti and Zr in Al, and then solution-treating it. CONSTITUTION: The composition of the alloy is made as follows: by wt%, 5.1W 8.1 Zn, 1.8W3.4 Mg, 1.2W2.6 Cu, Ti<0.2, 0.05W0.25 Zn, and the balance Al and impurities. This alloy is homogenized, hot-rolled and then cold-rolled to predetermined thickness in a conventional manner. Thereafter, it is heated up to 320W500°C at a heating speed of 11°C/min in average and then softened. When a cooling speed during the softening is above 30°C/hr, the alloy is reheated at 200W500°C. When the reheating temp. is at 200W350°C, the alloy is air-cooled or cooled at a speed below 30°C/hr. When the reheating temp. is at 350W500°C, the alloy is cooled at a speed below 30°C/hr. The softened alloy is then cold- joggled with a different work ratio of 0W90%. Thereafter, solution treatment is performed. COPYRIGHT: (C)1984,JPO&Japio
8	Sitz, insbesondere für einen Flugbegleiter	EP89109896.4	1989-06-01	EP0349762A3	1990-06-27	Lehnert, Franzrudolf
Bei einem Sitz, insbesondere für einen Flugbegleiter, im wesentlichen bestehend aus einem Gestell sowie einem Sitzteil, mit einem vorderen und einem hinteren Bereich und einer Schale für das Rückenpolster, mit einem oberen und einem unteren Bereich, wobei der Sitzteil in einer in seinem hinteren Bereich angeordneten ersten Anlenkung schwenkbar ausgebildet ist, so daß der Sitzteil zwischen einer im wesentlichen horizontalen Gebrauchslage und einer im allgemeinen vertikalen Ruhelage schwenkbar ist, wobei die Schale für das Rückenpolster in ihrem oberen Bereich eine zweite Anlenkung aufweist, besteht die Erfindung darin, daß die Schale (3) für das Rückenpolster (4) in ihrem unteren Bereich in der ersten Anlenkung mit dem Sitzteil um eine Achse (11) gelenkig verbunden ist, wobei ein um eine gestellfeste Achse (10) schwenkbarer Traglenker (9) vorgesehen ist, an dessen äußerem Ende das Sitzteil und die Schale (3) für das Rückenpolster (4) um die Achse (11) schwenkbar angelenkt sind, wobei ein im oberen Bereich der Schale (3) angeordnetes Gelenk (18) eine Schwenkbewegung und eine Verschiebung zuläßt, so daß der Traglenker (9) mit der Schale (3) im Prinzip einen Kurbeltrieb bildet. Dabei ist von Vorteil, daß der Sitz in unterschiedliche Gebrauchslagen gebracht werden kann, wobei sowohl die Rückenlehne als auch die Sitzschale bezüglich ihrer Winkellagen einstellbar sind.
9	항공기 복합재용 프리프레그의 성형 장치	KR1020140195063	2014-12-31	KR1020160081351A	2016-07-08	배병환; 이해동
본발명에따른항공기보강재용프리프레그의성형장치(1000)는프리프레그(10)의일측및 타측을각각접촉부위(11) 및성형부위(12)라고할때, 상면에프리프레그(10)의접촉부위(11)가올려지는몰드(100); 프리프레그(10)를둘러싸며탄성있는재질로이루어지는백 필름(200); 상기백 필름(200)의내부에채워진공기를배출시켜진공상태를만드는배출부; 프리프레그(10)의성형부위(12)가가열연화되도록프리프레그(10)의성형부위(12)에접촉되어열을가하는히트패널(300); 및프리프레그(10)와상기히트패널(300)의접촉이해제되도록상기히트패널(300)을이동시켜프리프레그(10)의가열연화된성형부위(12)가상기몰드(100)의윤곽에대응하는구조로성형되게하는이동패널(400);를포함하는것을특징으로한다.
10	AIRCRAFT NACELLE THAT INCORPORATES A DEVICE FOR REVERSING THRUST	US12525578	2008-01-23	US20100031630A1	2010-02-11	Guillaume Bulin; Patrick Oberle
An aircraft nacelle in which a power plant is arranged and delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position. Each flap includes articulation elements with a first pivoting axis and a second pivoting axis, whereby the pivoting axes are essentially parallel to the vertical median axis of the nacelle.
11	AIRCRAFT NACELLE INCLUDING AN OPTIMISED ICE TREATMENT SYSTEM	PCT/FR2008052166	2008-12-01	WO2009077690A3	2009-08-20	PORTE ALAIN; CHENE GILLES; HORMIERE ARNAUD
The invention relates to an aircraft nacelle that comprises a duct (32), a peripheral wall (34), a front lip (36) connecting said duct (32) and said peripheral wall (34) and defining an air inlet, as well as an ice treatment system for treating an area extending along a longitudinal section from a point A at the peripheral wall (34) to a point B at the duct (32) and including a front frame (38) defining together with said lip (36) a duct (51) in which flows hot air for de-icing, wherein said duct (32) includes an acoustic-treatment coating (44) that comprises, from the inside to the outside, a reflecting layer, at least one cellular structure and at least one acoustically-resistive structure, characterised in that the front frame (38) includes a junction area with the lip (36) and/or the duct (32), that is offset towards the front of the nacelle relative to point B, wherein ducts (50) are provided at the inner face of the lip (36) and of the duct (32) in order to direct hot air from said hot-air duct (51) to outlets provided at a circle corresponding to point B, said ducts (50) extending beyond the junction area between the front frame (38) and the lip (36) and/or the duct (32), and being defined by at least one wall that insulates the hot air of the coating (44) for the acoustic treatment.
12	航空機用飲料製造機のための調節インライン水加熱システム	JP2015532094	2013-09-13	JP2015533541A	2015-11-26	エー．レイマス、セバスチャン; ディーツ、スチュアート; ディー．アロンソン、ウィリアム
【解決手段】水加熱部および淹出部を有する飲料淹出装置(10)であって、水加熱部が、3つの加熱素子(40)を有する、3つの加熱素子のタンク(30)と、三相電力システムとを備え、各加熱素子が、位相の異なる電力によって電力供給される飲料淹出装置(10)。淹出装置を管理するプロセッサ(160)によって制御される、異なる加熱能力を有する加熱素子のそれぞれは、加熱動作をより良好に制御するように動作する。【選択図】図1
13	WATER VENTING SYSTEMS AND METHODS FOR AIRCRAFT BEVERAGE MAKERS	PCT/US2012028699	2012-03-12	WO2012125522A3	2012-11-08	KUNIYOSHI CABE RACHEL
Embodiments of the present invention provide improved draining and venting systems for coffee makers and other water-using appliances used on board passenger transport vehicles.
14	AIRCRAFT NACELLE INCLUDING AN OPTIMISED ACOUSTIC PROCESSING SYSTEM	PCT/FR2010050137	2010-01-28	WO2010086560A2	2010-08-05	CHELIN FREDERIC; PORTE ALAIN; GANTIE FABRICE; LALANE JACQUES
The invention relates to an aircraft nacelle including a duct (32), a peripheral wall (34), a lip (36) and a front frame (38) connecting the peripheral wall (34) and the duct (32) and defining a gap (50) with the lip (36) in which hot air can flow for treating icing, the duct (32) including a coating (44) for acoustic processing made of a composite material, characterised in that the nacelle further includes at least one element (52) made of a heat-conducting material and provided between the lip (36) and the duct (32) and ensuring the continuity of the aerodynamic surfaces of the lip (36) and the duct (32) and the propagation of heat from said gap (50) towards the back of the nacelle, said at least one element (52) comprising a coating (54) for acoustic processing made of a heat resistant material.
15	AIRCRAFT NACELLE THAT INCORPORATES A THRUST REVERSAL DEVICE	US12825393	2010-06-29	US20110127353A1	2011-06-02	Benoît LETAY; Benjamin SAGET; Franck LESIEUR; Stéphane FLIN
An aircraft nacelle in which a power plant with an outside surface (46) is arranged, whereby the nacelle has an inside wall (44) that with the outside surface (46) of the power plant delimits a secondary annular pipe, at least one moving part (52) so as to create at least one lateral opening (54), and a thrust reversal device that has at least one moving physical obstacle (56, 58) that can occupy a first retracted state in which it does not deflect the stream that circulates in the secondary pipe and another deployed state in which it at least partially deflects the stream that circulates in the secondary annular pipe toward the at least one side opening (54), characterized in that it includes a ring (50) that is arranged in the secondary pipe, distant from the inside wall (44) of the nacelle and the outside surface (46) of the power plant that supports the at least one moving physical obstacle (56, 58).
16	Aircraft trash compactor and box therefor	EP85305174	1985-07-19	EP0169719A3	1988-03-02	Diamond, Fredric L.; Andrews, Kenneth E.
A trash compactor and collapsible box for use therewith to handle waste material generated during flight of passenger-carrying aircraft. The trash compactor includes a housing (20) formed with front and rear box chambers (22, 24) to receive first and second collapsible trash-receiving boxed (B-1, B-2). A front door (26) is provided for the housing having a trash-receiving chute (28) in its upper portion. The first box is initially disposed in the front box chamber. When it is filled, the front door is opened and the first box is pushed to the rear box chamber. The second box is then positioned within the front box chamber to receive trash, and the front door is shut. The collapsible boxes have a front wall disposed at the same elevation as the lower edge of the chute, while the tops of the side and rear walls are at a higher elevation than the top of the front wall to permit the boxes to receive a maximum amount of trash for their size. The bottom portion of the wall is of liquid-tight construction.
17	WATER VENTING SYSTEMS AND METHODS FOR AIRCRAFT BEVERAGE MAKERS	PCT/US2012/028699	2012-03-12	WO2012125522A2	2012-09-20	KUNIYOSHI CABE, Rachel
Embodiments of the present invention provide improved draining and venting systems for coffee makers and other water-using appliances used on board passenger transport vehicles.
18	OXYGEN SUPPLYING CIRCUIT FOR AN AIRCRAFT CREW MEMBER	US12093002	2005-11-09	US20090126737A1	2009-05-21	Severine Aubonnet; Andrew R.T Tatarek-Gintowt
The invention relates to a breathing apparatus for an aircraft crew member, said apparatus comprising at least one breathing mask (620) provided with a demand regulator (810), said demand regulator being linked through a feedline to a central source of oxygen enriched air (600), so that oxygen enriched air is supplied to said breathing mask, and pressure regulating means (601,602,603, 604) provided on said feedline between said central source and said demand regulator and adapted, to level the pressure fluctuations of said oxygen enriched air supplied to said breathing mask.
19	MODULATED INLINE WATER HEATING SYSTEM FOR AIRCRAFT BEVERAGE MAKERS	PCT/US2013/059756	2013-09-13	WO2014046980A1	2014-03-27	RAMUS, Sebastien A.; DIETZ, Stuart; ARONSON, William D.
A beverage brewing apparatus (10) having a water heating portion and a brewing portion, the water heating portion comprising a three heating element tank (30) having three heating elements (40), a three phase power system, and wherein each heating element is powered by a different phase power. Each heating element may operate with a different heating capacity to better control the heating operation, controlled by a processor (160) that manages the brewing apparatus.
20	A STORAGE BOX FOR A RESPIRATORY MASK TO BE WORN BY CREWMEMBERS OF AN AIRCRAFT	PCT/IB2006/003481	2006-08-10	WO2008017901A1	2008-02-14	BLOCH, Nicolas; MAROTTE, Henri
The invention relates to a storage box (13) in which is received a protective mask (4) adapted to be applied on the face of an aircraft crewmember, said storage box further comprising signaling means (19) activable upon occurrence in the aircraft of a triggering event to help said aircraft crewmember distinguish said stora e box from its environment.

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