| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Emergency exit for a vehicle, in particular an airborne or space vehicle | EP87109930 | 1987-07-10 | EP0261329A3 | 1988-06-15 | GRONOW, WERNER |
| 22 | Notausgang an Fahrzeugen, insbesondere Luft- und Raumfahrzeugen | EP87109930.5 | 1987-07-10 | EP0261329A2 | 1988-03-30 | Gronow, Werner |
Die Erfindung betrifft einen Notausgang (18) an Fahrzeugen, insbesondere Luft- und Raumfahrzeugen, bestehend aus einer Notdurchstiegsöffnung (17) in der Fahrzeugwand (6) und einer mit dieser verriegelbaren und gegen deren Innenseite formschlüssig anliegenden Türe (4), die zum vollständigen Öffnen durch die Notdurchstiegsöffnung (17) nach außen zu verbringen ist. |
||||||
| 23 | Aircraft cockpit canopy | EP84302525.5 | 1984-04-13 | EP0123481B1 | 1987-10-28 | Brophy, Gilbert Edward |
| 24 | Dispositif pyrotechnique de découpage et d'éjection d'un élément transparent de verrière d'avion | EP81401103.7 | 1981-07-08 | EP0044251B1 | 1985-01-02 | Chigot, Claude; Morlan, Serge |
| 25 | Aircraft cockpit canopy | EP84302525.5 | 1984-04-13 | EP0123481A1 | 1984-10-31 | Brophy, Gilbert Edward |
An aircraft cockpit canopy(1) has a separable portion (3) which is capable of being separated from a remaining portion of the canopy at a clearly defined break line by means of detonating cord (22), to facilitate ejection of a crew member along a predetermined path (2) through the canopy, the separable portion (3) being of such a size that hinges (7) are provided to constrain it to swing in a predetermined path to clear the ejection path, the hinges (7) being attached to the canopy and bridging the break line so that priorto separation, they remain unused but subsequently they are effective to pivotally constrain the separated portion. Conveniently, the separable portion may be in two or three large parts. |
||||||
| 26 | Glace munie d'un dispositif de découpage pyrotechnique | EP79401076.9 | 1979-12-28 | EP0013529B1 | 1981-11-04 | Chigot, Claude René; Boeglin, Paul Hubert |
| 27 | PUSH-OUT BUBBLE WINDOW FOR ROTARY AIRCRAFT | US15482594 | 2017-04-07 | US20180290723A1 | 2018-10-11 | Matthew John Hill; William David Tohlen; Bobby Howard Mosier; Lynn Francis Eschete |
| Aspects of the embodiments of the present disclosure are directed to a window panel having a bubble form. The window panel is a push-out window that permits emergency egress from an aircraft, such as a rotorcraft. The bubble form is designed and selected such that the window panel will remain secured in a window frame of the aircraft at a level cruising speed of 120 knots true air speed. In embodiments, the window panel remains secured in the window frame at 120 ktas and a sideslip of at least 6 degrees. | ||||||
| 28 | Triggering systems for cartridge activated devices | US15147727 | 2016-05-05 | US10071493B2 | 2018-09-11 | Stephen B. Povroznik, III; Darryl A. Tetrault |
| A triggering system includes a source lead, a ground lead, primary and secondary actuation circuits, and a serializing switch. Both the primary and second actuation circuits are connected to the source lead and the serializing switch has first and second positions. In a first position, the serializing switch connects the primary and secondary actuation circuit in parallel for actuating primary and secondary cartridge activated devices. In a second position, the serializing switch connects the secondary actuation circuit in series with the primary actuation circuit for verifying that the actuation circuits can reliably actuate both cartridge activated devices. | ||||||
| 29 | Aircraft with selectively attachable passenger pod assembly | US15200163 | 2016-07-01 | US09963228B2 | 2018-05-08 | John Richard McCullough; Paul K. Oldroyd |
| In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween. | ||||||
| 30 | TRIGGERING SYSTEMS FOR CARTRIDGE ACTIVATED DEVICES | US15147727 | 2016-05-05 | US20160325454A1 | 2016-11-10 | Stephan B. Povroznik, III; Darryl A. Tetrault |
| A triggering system includes a source lead, a ground lead, primary and secondary actuation circuits, and a serializing switch. Both the primary and second actuation circuits are connected to the source lead and the serializing switch has first and second positions. In a first position, the serializing switch connects the primary and secondary actuation circuit in parallel for actuating primary and secondary cartridge activated devices. In a second position, the serializing switch connects the secondary actuation circuit in series with the primary actuation circuit for verifying that the actuation circuits can reliably actuate both cartridge activated devices. | ||||||
| 31 | Aircraft cockpit with emergency exit via a central pane | US14106113 | 2013-12-13 | US09434478B2 | 2016-09-06 | Yves Durand; Bernard Guering |
| The present invention relates to an aircraft cockpit with a double flight deck in which a central pane of a windscreen can be removed in order to at least partially clear an opening in order to constitute an emergency exit and ensure natural ventilation of the cockpit. Moreover, a central portion of a glare shield and of a flight station instrument panel are optionally moveable in order to facilitate access to the opening in the event of the need for emergency evacuation. | ||||||
| 32 | Aeroplane Equipped With An Internal Escape Hatch Incorporating A Pressure Regulating System | US14750114 | 2015-06-25 | US20150375866A1 | 2015-12-31 | Patrick Salgues; Anne-Laure Neveu |
| An aeroplane includes an external skin and an internal bulkhead delimiting a cabin, and an escape opening passing through the external skin and the internal bulkhead. The escape opening is closed off by an external escape hatch disposed flush with the external skin. The aeroplane also includes an internal escape hatch that closes off the escape opening disposed flush with the internal bulkhead, and pressure regulating means capable of automatically triggering an opening of the internal escape hatch or a part of the internal escape hatch when a pressure differential on both sides of the internal escape hatch exceeds a determined value. | ||||||
| 33 | PASSENGER AIRCRAFT WITH AN EMERGENCY EXIT DOOR | US14711906 | 2015-05-14 | US20150329194A1 | 2015-11-19 | Paul JOERN; Claus HANSKE; Arne ROTH |
| A passenger aircraft with a passenger cabin is described, wherein the passenger aircraft comprises a fully functional door, which is openable and closable and which is adapted for an entrance and an exit of passengers, and en emergency exit door, which is exclusively adapted for an emergency exit of passengers from the passenger cabin. Therein, the emergency exit door is arranged in an area of a fuselage of the passenger aircraft, which is arranged ahead of and/or behind of wings of the passenger aircraft. | ||||||
| 34 | RETRACTABLE SHADE AND METHOD SEALING AN OVER-WING EXIT IN AN AIRCRAFT | US14012383 | 2013-08-28 | US20150059988A1 | 2015-03-05 | Sahrudine Apdalhaliem; Kimberly Dawn Meredith; Morteza Safai; Lon E. Switzer; Thomas Seth Perkins; Scott A. Langdon; Tuan D. Nguyen |
| 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. | ||||||
| 35 | Weatherproof surround for safely jettisoning a removable panel | US13431078 | 2012-03-27 | US08826597B2 | 2014-09-09 | Nicolas Raspic |
| A weatherproof surround, for a jettisonable panel (5) of a vehicle (1) such as a helicopter, possesses four confinement flanges (17-20) integrally formed with a projecting ridge for spring-clipping a corresponding locking strip. Longitudinal foldable shoulders connect the confinement flanges (17-20) to a central trunk (13). Each confinement flange (17-20) can be folded back through pivot angle (31) of at least 90°. | ||||||
| 36 | LOW PROFILE JETTISONABLE DOOR SYSTEM | US13746015 | 2013-01-21 | US20130200214A1 | 2013-08-08 | William P. Sumner; Philip J. Bookout |
| A jettisonable door system for an aircraft includes an upper hinge having a forward portion that is hingedly coupled to an airframe of the aircraft, the upper hinge having an aft portion that is releasably secured to an upper outboard plate with an upper pin. The jettisonable door system further includes a lower hinge having a forward portion that is hingedly coupled to the airframe of the aircraft, the upper hinge having an aft portion that is releasably secured to a lower outboard plate with a lower pin. A rotation of the upper pin releases the upper hinge from the upper outboard plate and a rotation of the lower pin releases the lower hinge from the lower outboard plate. | ||||||
| 37 | Aircraft flight termination system and method | US12112047 | 2008-04-30 | US08256716B2 | 2012-09-04 | Mark C. Dietrich; Charles N. Trepanier; Timothy R. Werch |
| An aircraft has a flight termination system that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces of the aircraft, such as a wing, from a fuselage 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. | ||||||
| 38 | PYROTECHNIC EGRESS SYSTEM | US13063980 | 2008-09-30 | US20110167994A1 | 2011-07-14 | Honmartin K. Au-Yeung; David J. Goldschmidt; Anthony Z. Stobiecki |
| A pyrotechnic egress system includes an air encapsulation member which at least partially surrounds a charge holder which contains an explosive cord. | ||||||
| 39 | SHIELD FOR EXPLOSIVE CUTTER | US12705922 | 2010-02-15 | US20100206159A1 | 2010-08-19 | YaoHua Wang; Hui Wang |
| A blast shield formed as a multilayer sandwich of composite material configured to provide protection to bystanders in close proximity to operation of a linear shaped charge. An exemplary embodiment may be used to shield passengers when explosively cutting an emergency door in airliners. The composite material forming a blast shield may have two types of composition: the first type contains a layer of carbon fiber cloth, a layer of natural rubber and a layer of Kevlar fiber cloth, from the inside out in order. The second type contains a layer of carbon fiber cloth, a layer of Kevlar fiber cloth and a layer of polyurethane rubber, from the inside out in order. Both types typically use epoxy resin as the bond between each layer. Through the composition of fiber and rubber, embodiments can effectively block the spread of explosive shock waves, reduce the noise, decrease the weight of protective devices, and avoid forming wounding debris. When applied on the surface of a linear shaped charge, the blast shield can limit the explosive sub-effect to the minimum, which meets the features of aircraft cabin which has limited space and multiple passengers. | ||||||
| 40 | AIRCRAFT FLIGHT TERMINATION SYSTEM AND METHOD | US12112047 | 2008-04-30 | US20090272840A1 | 2009-11-05 | Mark C. Dietrich; Charles N. Trepanier; Timothy R. Werch |
| An aircraft has a flight termination system that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces of the aircraft, such as a wing, from a fuselage 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. | ||||||
QQ群二维码
意见反馈
意见反馈