序号 | 专利名 | 申请号 | 申请日 | 公开(公告)号 | 公开(公告)日 | 发明人 |
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181 | AÉRONEF COMPORTANT UNE TRAPPE ET UN DISPOSITIF ANTICHUTE | EP15184221.8 | 2015-09-08 | EP3000721B1 | 2018-07-25 | CHOURREAU, Yannick; CHALLANCIN, Loïc |
182 | WINDOW WITH AN EMERGENCY EXIT FUNCTION FOR A HELICOPTER AND METHOD FOR REMOVING A TRANSPARENT ELEMENT FROM THIS WINDOW | EP16187548.9 | 2016-09-07 | EP3293106A1 | 2018-03-14 | GORGOGLIONE, Giorgio; PAPALEO, Gaetano |
A window (7) with an emergency exit function for a helicopter (1) is described that comprises: a frame shaped as a framework (8) that can be coupled to a door (6) of said helicopter provided with an opening (9); and a transparent element (10) designed to engage the opening (9) and held in position by the frame (8); the frame (8) comprises a first side (25) arranged abutting against the transparent element (10) when a first force (F) below a threshold value is exerted on the latter in a direction transversal to a first plane (P) of a main portion (11) of the transparent element (10), and which can be elastically moved away from the transparent element (10) when the first force (F) exerted on the latter exceeds the threshold value; and a second side (30) having greater flexural rigidity than the first side (25) in a second plane transversal to first plane (P) and arranged abutting against the transparent element (10) even when the force (F) is greater than said threshold value. |
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183 | Retractable shade and method for assembling the same | EP14182471.4 | 2014-08-27 | EP2845796B1 | 2017-10-04 | Apdalhaliem, Sahrudine; Meredith, Kimberly Dawn; Safai, Morteza; Switzer, Lon E.; Perkins, Thomas Seth; Langdon, Scott A.; Nguyen, Tuan D. |
A heated roller shade system is provided. The heated roller shade system includes a roller located in a cavity defined between an inner wall of a vehicle and an outer wall of the vehicle. The roller shade system also includes a shade coupled to the roller. The roller is configured to selectively move the shade between a deployed position and an open position. The roller shade system also includes a heating mechanism coupled to at least one of the roller and the shade. The heating mechanism facilitates increasing a temperature of at least one of the roller and the shade. | ||||||
184 | Aircraft with integrated jettison mechanism | EP13400004.1 | 2013-03-18 | EP2781451B1 | 2016-06-22 | Steger, Justus; Görlich, Stefan |
185 | AÉRONEF COMPORTANT UNE TRAPPE ET UN DISPOSITIF ANTICHUTE | EP15184221.8 | 2015-09-08 | EP3000721A1 | 2016-03-30 | CHOURREAU, Yannick; CHALLANCIN, Loïc |
L'invention concerne un aéronef comportant : |
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186 | PASSENGER AIRCRAFT WITH AN EMERGENCY EXIT DOOR | EP15167479.3 | 2015-05-13 | EP2944562A2 | 2015-11-18 | Jörn, Paul; Hanske, Claus; Roth, Arne |
A passenger aircraft (100) with a passenger cabin (102) is described, wherein the passenger aircraft (100) comprises a fully functional door (110), which is openable and closable and which is adapted for an entrance and an exit of passengers, and en emergency exit door (112), which is exclusively adapted for an emergency exit of passengers from the passenger cabin (102). Therein, the emergency exit door (112) is arranged in an area of a fuselage (106) of the passenger aircraft (100), which is arranged ahead of and/or behind of wings (108) of the passenger aircraft (100). |
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187 | Retractable shade and method for assembling the same | EP14182471.4 | 2014-08-27 | EP2845796A1 | 2015-03-11 | Apdalhaliem, Sahrudine; Meredith, Kimberly Dawn; Safai, Morteza; Switzer, Lon E.; Perkins, Thomas Seth; Langdon, Scott A.; Nguyen, Tuan D. |
A heated roller shade system is provided. The heated roller shade system includes a roller located in a cavity defined between an inner wall of a vehicle and an outer wall of the vehicle. The roller shade system also includes a shade coupled to the roller. The roller is configured to selectively move the shade between a deployed position and an open position. The roller shade system also includes a heating mechanism coupled to at least one of the roller and the shade. The heating mechanism facilitates increasing a temperature of at least one of the roller and the shade. |
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188 | Low profile jettisonable door system | EP13153927.2 | 2013-02-04 | EP2626294B1 | 2015-01-28 | Sumner, William P.; Bookout, Philip J. |
189 | Cockpit d'aéronef à issue de secours par une glace centrale | EP13197233.3 | 2013-12-13 | EP2749492A1 | 2014-07-02 | Durand, Yves; Guering, Bernard |
La présente invention concerne un cockpit d'aéronef à double poste de pilotage dans lequel une glace centrale (11) de pare-brise (10) est amovible pour pouvoir dégager au moins partiellement une ouverture (13) pour constituer une issue de secours et assurer une ventilation naturelle du cockpit. De plus, une partie centrale d'un auvent et d'une planche de bord sont optionnellement mobiles pour faciliter un accès à l'ouverture (13) en cas de nécessité d'évacuation d'urgence. |
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190 | PYROTECHNIC EGRESS SYSTEM | EP08877199 | 2008-09-30 | EP2340201A4 | 2013-05-29 | AU-YEUNG HONMARTIN K; GOLDSCHMIDT DAVID J; STOBIECKI ANTHONY Z |
191 | AIRCRAFT FLIGHT TERMINATION SYSTEM AND METHOD | EP09739315.1 | 2009-02-19 | EP2279116B1 | 2012-04-04 | DIETRICH, Mark, C.; TREPANIER, Charles, N.; WERCH, Timothy, R. |
An aircraft (10) has a flight termination system (12) that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces (20) of the aircraft, such as a wing (32), from a fuselage (14) of the aircraft, while one or more other control surfaces connected to the fuselage. The separation may be accomplished by firing one or more explosive bolts to release a clamp that connects the control surface to the fuselage. The separation causes an asymmetry in configuration that results in a rapid crash of the aircraft. The flight termination system causes termination to be effected in small flight footprint, without use of powerful explosives, and without a large cost in weight or volume. The flight termination system may be used in unpowered or powered aircraft. | ||||||
192 | PYROTECHNIC EGRESS SYSTEM | EP08877199.3 | 2008-09-30 | EP2340201A1 | 2011-07-06 | AU-YEUNG, Honmartin, K.; GOLDSCHMIDT, David, J.; STOBIECKI, Anthony, Z. |
A pyrotechnic egress system includes an air encapsulation member which at least partially surrounds a charge holder which contains an explosive cord. | ||||||
193 | AIRCRAFT FLIGHT TERMINATION SYSTEM AND METHOD | EP09739315.1 | 2009-02-19 | EP2279116A2 | 2011-02-02 | DIETRICH, Mark, C.; TREPANIER, Charles, N.; WERCH, Timothy, R. |
An aircraft (10) has a flight termination system (12) that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces (20) of the aircraft, such as a wing (32), from a fuselage (14) of the aircraft, while one or more other control surfaces connected to the fuselage. The separation may be accomplished by firing one or more explosive bolts to release a clamp that connects the control surface to the fuselage. The separation causes an asymmetry in configuration that results in a rapid crash of the aircraft. The flight termination system causes termination to be effected in small flight footprint, without use of powerful explosives, and without a large cost in weight or volume. The flight termination system may be used in unpowered or powered aircraft. | ||||||
194 | Porte ejectable, pour aeronef | EP03290221.5 | 2003-01-29 | EP1332962B1 | 2004-08-04 | Leclerc, Frédéric |
195 | Porte ejectable, pour aeronef | EP03290221.5 | 2003-01-29 | EP1332962A1 | 2003-08-06 | Leclerc, Frédéric |
Une porte de type bouchon, destinée notamment à un aéronef militaire de type avion cargo, est conçue de façon à permettre son éjection en cas de nécessité. A cet effet, un organe de manoeuvre tel qu'une poignée (28) commande simultanément l'effacement des axes de pivotement (16c) des charnières par lesquelles le panneau (10) de la porte est articulé sur son cadre (12) et l'effacement des éléments mécaniques (21) contre lesquels sont normalement en appui, par gravité, les butées (19) montées sur le panneau, lorsque la porte est fermée. De plus, des rampes de guidage liées au cadre (12) et dans lesquelles sont reçus des galets portés par le panneau (10) sont ouvertes vers le bas, pour permettre la chute du panneau (10) par gravité, lorsque la poignée (28) est actionnée. |
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196 | Corona discharge surface treatment, and aircraft cockpit canopies so treated | EP88309646.3 | 1988-10-14 | EP0312385A3 | 1990-03-14 | Elford, Andrew Mark |
Apparatus for and a method of rendering selected areas 17, 18 of an aircraft canopy 2 receptive to an adhesive by means of which a detonating cord 7 is attached in loop form to the canopy, to facilitate fracture of the canopy for pilot ejection in an emergency, comprises pretreating those areas 17, 18 by corona discharge. The canopy 2 is mounted in a jig 10 shaped to conform with the canopy and having rebates 11 for accommodating discharge electrodes 12 located at a distance from the canopy 2. A pump 16 is provided to remove ozone formed due to the discharge and trapped between the canopy 2 and the jig 10. |
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197 | Dispositif de maintien d'un cordeau détonant contre un élément transparent de verrière d'avion | EP83400395.6 | 1983-02-25 | EP0089259A1 | 1983-09-21 | Devienne, Jules Henri Paul |
La présente invention a pour object un dispositif de maintien d'un cordeau détonant (10) contre un élément transparent (2) de verrière d'avion. Le cordeau (10) étant placé à l'intérieur d'une gaine fermée (12), le dispositif comporte en outre une enveloppe externe (14) dont une première partie (15), entourant complètement la gaine fermée (12), est maintenue en appui contre l'élément transparent (2) et dont une deuxième partie (16) est fixée à un élément (4) de la structure de l'habitacle de l'avion. Application au découpage et à l'éjection des éléments transparents de verrière d'avion. |
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198 | Dispositif pyrotechnique de découpage et d'éjection d'un élément transparent de verrière d'avion | EP81401103.7 | 1981-07-08 | EP0044251A1 | 1982-01-20 | Chigot, Claude; Morlan, Serge |
L'invention concerne un dispositif et un procédé pyrotechniques permettant le découpage et l'éjection d'un élément transparent d'une verrière d'avion. Le dispositif assurant de découpage et l'éjection d'un élément transparent (2) de verrière d'avion (1), muni de sièges éjectables (5), au moyen d'un cordeau détonant (8), la verrière (1) étant maintenue par deux bordures longitudinales (5, 6) comportant un profilé d'accrochage de l'élément transparent (2), et par deux arceaux (3,4) comportant un talon d'accrochage de l'élément transparent (2), se caractérise en ce que le cordeau détonant (8) est disposé à la périphérie de la verrière (1), dans les bordures longitudinales (5,6) et contre le profilé d'accrochage, et dans les arceaux avant (3) et arrière (4), en regard et contre le talon d'accrochage. |
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199 | 一种可自卸电池式无人机电池固定安装结构 | CN201620383316.8 | 2016-04-28 | CN205633009U | 2016-10-12 | 鲍静云; 王威; 殷兰兰 |
本实用新型公开了一种可自卸电池式无人机电池固定安装结构,包括无人机主体和电池盖,所述无人机主体底部开设有用于容纳电池的电池腔,电池腔的一侧设置有铰接孔,所述电池盖上对应的一侧设置有配合于所述铰接孔的铰接柱,所述铰接柱铰接在铰接孔中并使得电池盖铰接设置在无人机主体上,所述电池腔在其远离铰接孔的另一侧设置有电池盖母扣,所述电池盖的自由端设置有配合于所述电池盖母扣的电池盖公扣,所述电池盖公扣可扣紧在无人机主体上的电池盖母扣上并将电池限位在电池腔内部,电池盖公扣和/或电池盖母扣为可变形构件。该种可自卸电池式无人机电池固定安装结构具有结构简单、实施方便、可保护无人机主体安全、有效延长无人机寿命等优点。 |