| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Water-inflow prevention device of aircraft, air pressure regulating valve for aircraft, and aircraft | US13938545 | 2013-07-10 | US09533767B2 | 2017-01-03 | Shingo Kawano; Tomoka Mashio; Akitaka Urano; Shuichi Hagino |
| A water-inflow prevention device is provided by installing a closing lid 6 for blocking a duct 2 of an air pressure regulating valve 1, which regulates air pressure inside a cabin 101. A buoyant body 9 is attached to the disc-shaped closing lid 6 installed to the duct 2 so as to be rotatable around a rotation shaft 7. The buoyant body 9 receives a buoyant force from water when immersed in the water. Since the side of the closing lid 6 in which the buoyant body 9 is attached is thereby floated in the water, the closing lid 6 automatically rotates around the rotation shaft 7 so as to close a ventilation port 2a. | ||||||
| 142 | WATER INFLOW PREVENTION DEVICE FOR AIRCRAFT WORKING WHEN LANDING IN WATER, PRESSURE ADJUSTING VALVE, AND AIRCRAFT | US15044457 | 2016-02-16 | US20160272334A1 | 2016-09-22 | Shingo Kawano; Takashi Uchino; Syuichi Hagino; Akitaka Urano |
| The present invention provides a water inflow prevention device for aircraft, working when landing in water, the device including: a blocking body for blocking a flow channel from an outside of the aircraft when landing in water, the flow channel allowing the inside and outside of the aircraft to communicate with each other, and a valve element of a pressure adjusting valve being positioned in the flow channel; and a connection part that is deformed when landing in water, wherein the blocking body is supported by a member constituting an end of the flow channel on a side outside the aircraft through the connection part, and the connection part is deformed in a direction so as to block the flow channel by the blocking body, with use of force of water acting on the blocking body when landing in water. | ||||||
| 143 | Decompression unit | US13880201 | 2011-10-13 | US09387917B2 | 2016-07-12 | Erich Pamminger; Bernhard Kammerer |
| A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure Δp in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded. | ||||||
| 144 | Avionics cargo hold module having an upper integrated floor | US14138588 | 2013-12-23 | US09359084B2 | 2016-06-07 | Yves Durand; Bernard Guering |
| An integral avionics bay module. The module has a structure that has an integral cabin floor on top that closes the structure. Installing such an integral avionics bay structure in a single operation inside a primary fuselage structure considerably reduces the integration time on the final assembly line for the aircraft. | ||||||
| 145 | Method and system for emergency ventilation of an aircraft cabin in the case of a leak in the area of an air mixer | US13126544 | 2009-09-08 | US09266601B2 | 2016-02-23 | Frank Klimpel; Rüdiger Schmidt |
| In a method for emergency ventilation of an aircraft cabin, a leak is detected in the area of an air mixer of an aircraft air conditioning system. An emergency air flap, which in a closed position prevents an air exchange between an aircraft area adjacent to the air mixer and the aircraft cabin, is controlled into an open position. Air from the aircraft area adjacent to the air mixer is conveyed through the open emergency air flap into the aircraft cabin. | ||||||
| 146 | Decompression panel and latch | US13910503 | 2013-06-05 | US09114869B1 | 2015-08-25 | Casey J. Barrett; Khoa Duy Nguyen; Mark A. Wolf; Andrew H. Wu |
| A decompression panel for use in a door of an aircraft disclosed herein includes bi-directional latching mechanisms. A differential pressure sensor disengages upon a decompression event in a compartment of an aircraft, allowing latch hooks to disengage from a panel latch of the decompression panel. Once disengaged, the decompression panel can rotate to vent air in a compartment of higher pressure to the compartment experiencing the decompression event. | ||||||
| 147 | PRESSURE RELIEF PANEL GUARD | US14601126 | 2015-01-20 | US20150225068A1 | 2015-08-13 | William J. Boyer |
| A pressure relief panel guard for use with a pressure relief ceiling panel having a perimeter and positioned in an aircraft cargo bay ceiling. The panel guard including a mounting structure attachable to the cargo bay ceiling, and having a mounting portion and a guard support portion, and a guard structure releasably supported by the guard support portion of the mounting structure. The guard structure having a perimeter wall and a central opening between the perimeter wall sized such that when supported by the guard support portion of the mounting structure at the pressure relief ceiling panel the pressure relief ceiling panel is vertically aligned with the central opening with the perimeter wall extending about the perimeter of the pressure relief ceiling panel and the perimeter wall does not overlap the pressure relief ceiling panel or otherwise restrict operational access to the pressure relief ceiling panel from below. | ||||||
| 148 | DOOR ASSEMBLY FOR AIRCRAFT INTERIOR | US14421625 | 2012-08-17 | US20150210373A1 | 2015-07-30 | Jean-Francois Guimont; Yvan Rosa; Benjamin Tremblay; Usher Boxer |
| Door assemblies for aircraft interiors are described. Such door assemblies may comprise a door for opening and closing an aperture between zones of the aircraft interior and an interface configured to couple the door to the aircraft interior. A pressure-relief element may form at least a portion of the door wherein the pressure-relief element is retained by a magnetic force calibrated to permit release of the pressure-relief element upon presence of a predetermined pressure differential across the pressure-relief element. Components and mechanisms useful in reducing light bleed across doors for aircraft interiors are also disclosed. | ||||||
| 149 | DECOMPRESSION PANEL FOR USE IN AN AIRCRAFT ASSEMBLY | US14471161 | 2014-08-28 | US20150115104A1 | 2015-04-30 | Thomas Perkins; Jeremy Ryan Glaze Tatum; Allan A. Loken; Hannah Rebecca Arm |
| A decompression panel for use in an aircraft assembly is provided. The decompression panel includes a body portion including a top edge and a bottom edge, and a front surface and a rear surface opposing the front surface. A plurality of openings are formed in the body portion, and a first stiffening member is formed on the rear surface below the plurality of openings. The first stiffening member extends from the rear surface towards the top edge such that the plurality of openings are at least partially obstructed by the first stiffening member. | ||||||
| 150 | Method and apparatus for establishing an environmentally isolated volume | US13781004 | 2013-02-28 | US08857762B2 | 2014-10-14 | Brad A. Kauffman |
| A method and apparatus are provided for at least partially environmentally isolating a volume, such as by environmentally isolating the cargo compartment from the passenger compartment of an aircraft. In the context of an apparatus, a barrier curtain is provided that partially defines the volume. The apparatus also includes a cable extending along one or more walls that partially define the volume. The barrier curtain is supported by the cable. The apparatus may also include a cable release mechanism attached to a respective wall. The cable is carried by the cable release mechanism and the cable release mechanism is configured to fail at a predetermined load, thereby permitting the barrier curtain to drop in response to a decompression event. | ||||||
| 151 | METHOD AND APPARATUS FOR ESTABLISHING AN ENVIRONMENTALLY ISOLATED VOLUME | US13773049 | 2013-02-21 | US20130292069A1 | 2013-11-07 | William Robert Clos |
| A method and apparatus are provided for at least partially environmentally isolating a volume, such as by environmentally isolating the cargo compartment from the passenger compartment of an aircraft. In the context of an apparatus, a barrier curtain is provided that partially defines the volume. The apparatus also includes a cable extending along one or more walls that partially define the volume. The barrier curtain is supported by the cable. The apparatus may also include a cable release mechanism. The cable is held in place by the cable release mechanism and the cable release mechanism is configured to detach the cable at a predetermined load, thereby permitting the barrier curtain to drop in response to a decompression event. | ||||||
| 152 | EXPLOSION VENT INCLUDING BUCKLE TAB PLATE | US13408429 | 2012-02-29 | US20130225064A1 | 2013-08-29 | Guy Jakus; Tom Eijkelenberg; Guido Dom |
| Improved, non-fragmenting, high efficiency vent apparatus (10, 78) are provided for protecting a structure (12) from potentially damaging or destructive abnormal pressure conditions. The apparatus (10, 78) is positioned in covering relationship to a vent opening (14) formed in the structure (12), and generally includes a burst member (16) and a tab assembly (18) equipped with a series of tabs (56); the tabs (56) bend or buckle to a burst member-clearing position when the vent apparatus (10, 78) experiences an abnormal pressure condition, thereby permitting rapid opening of burst member (16) to thus protect structure (12). The burst member (16) may be of domed or flat construction, and can be in the form of a quadrate panel or any other desired shape. | ||||||
| 153 | DECOMPRESSION ARRANGEMENT FOR AN AIRCRAFT | US13401937 | 2012-02-22 | US20120214393A1 | 2012-08-23 | Jürgen Vogt; Katja Strobel |
| A decompression arrangement includes first and second cabin lining elements each with an edge region, the edge region of the second being arranged at a smaller distance from an aircraft outer skin than the edge region of the first, an air discharge opening arranged between the first edge region and second edge region and which is adapted to discharge air from an inner region of the cabin delimited by the cabin lining elements into a region of the aircraft lying between the cabin lining elements and the aircraft outer skin, and a decompression element integrated in the second cabin lining element having a flap pivotable about an axis from a closed position, in which it closes a pressure equalising opening formed in the decompression element, into a first open position, in which it opens the pressure equalising opening if a first predetermined differential pressure acts on the decompression element. | ||||||
| 154 | RAPID RESPONSE SELF-CLOSING PRESSURE EQUALIZATION VENT | US12901325 | 2010-10-08 | US20120085426A1 | 2012-04-12 | Steven R. Kent; James S. Wells; John E. Kuhn |
| A rapid response self-closing pressure equalization vent employs a frame supported in a compartment divider and a movable vent portion having a periphery sealingly engaging the frame in a closed position. Multiple resilient extension elements are attached to the frame and engage the movable vent portion for even displacement around a periphery of the movable vent portion relative to the frame to an open position responsive to a pressure differential on the movable vent portion. The resilient extension elements retract upon equalization of the pressure differential to reseat the movable vent portion in the frame. | ||||||
| 155 | Deceleration device for a cockpit door for decelerating in case of decompression | US12231289 | 2008-08-29 | US08096505B2 | 2012-01-17 | Arne Klarmann; Nick Chignell-Stapleton |
| A deceleration device for a movable component in an aircraft, the device having a deformation component, wherein the deformation component includes a deformation tool, a deformation body with a deformable region, and a guide device. The deformation tool and the deformation body can be made to engage each other in such a manner by means of the guide device that in the case of movement of the deformation body and of the deformation tool relative to each other the deformable region of the deformation body can be deformed by the deformation tool. | ||||||
| 156 | Method And System For Emergency Ventilation Of An Aircraft Cabin In The Case Of A Leak In The Area Of An Air Mixer | US13126544 | 2009-09-08 | US20120003908A1 | 2012-01-05 | Frank Klimpel; Rudiger Schmidt |
| In a method for emergency ventilation of an aircraft cabin (12) a leak is detected in the area of an air mixer (24) of an aircraft air conditioning system (16). An emergency air flap (38), which in a closed position prevents an air exchange between an aircraft area (40) adjacent to the air mixer (24) and the aircraft cabin (12), is controlled into an open position. Finally, air from the aircraft area (40) adjacent to the air mixer (24) is conveyed through the open emergency air flap (38) into the aircraft cabin (12). | ||||||
| 157 | Apparatus for interconnecting a pilot station to at least one other aircraft zone, cockpit and aircraft equipped with such an apparatus | US11965203 | 2007-12-27 | US08040257B2 | 2011-10-18 | Daniel Ferro; Vincent Lautridou |
| An interconnecting apparatus for interconnecting a pilot station of an aircraft to at least one aircraft zone includes a device for communicating between the pilot station and the aircraft zone. The aircraft zone includes a device permitting a person present in the aircraft zone to identify themselves and a display device indicating a functional status of the aircraft. The pilot station includes a display device indicating a location of each person being identified in the aircraft zone. | ||||||
| 158 | Rapid Decompression Detection System and Method | US12921324 | 2009-03-09 | US20110201262A1 | 2011-08-18 | Michael Lehmann |
| A system for monitoring pressure change within at least one compartment of an aircraft is provided. The system includes a primary pressure sensor for providing a signal corresponding to a pressure within a primary compartment of the aircraft, a primary monitoring channel coupled to the primary pressure sensor, and an output driver coupled to the primary monitoring channel. The primary monitoring channel includes a band pass filter for receiving and filtering the primary pressure signal, a pressure change circuit for determining a change in the filtered pressure signal and for providing a pressure change output signal corresponding to the change in pressure, and a threshold logic circuit for determining whether the pressure change output signal meets a predetermined threshold and for providing a threshold output signal indicating that a decompression event has occurred if the pressure change output signal meets the predetermined threshold. The output driver receives the primary threshold output signal and outputs a notification signal. | ||||||
| 159 | Reduced door opening force and enhanced security flight deck door mechanism | US11923238 | 2007-10-24 | US07770949B2 | 2010-08-10 | James J. Kunda; Shannon J. Kupfer; Michael E. Renzelmann |
| An aircraft door mechanism includes a solenoid connected to a support assembly. The solenoid displaces the latch pin between a solenoid energized and a solenoid de-energized position. A catch assembly rotatably connected to the support assembly is positioned to engage a 3½ degree or less taper portion of the latch pin in the solenoid energized position. When the latch pin moves to the solenoid de-energized position, a latch bolt supported by the door rotates the catch assembly. The latch bolt includes a distal bulbous end which multiplies the force applied to the door to rotate the catch assembly. If the latch pin is extended, a substantially greater force is required to force the latch pin to the solenoid de-energized position owing to the reduced taper of the latch pin. Authorized door entry is therefore easier and unauthorized door entry is made more difficult. | ||||||
| 160 | Deceleration device | US11715285 | 2007-03-07 | US07712705B2 | 2010-05-11 | Clive French |
| A deceleration device adapted for gradual dissipation of kinetic energy comprises a spool reel carrying a belt being wound up on the spool reel; an elevating spindle being driven by the spool reel when the belt is being retracted from the spool reel; at least one collet screwed to the elevating spindle; and at least one spring assembly being installed between the collet and a fixed bearing portion of the deceleration device. The at least one collet is screwed towards the fixed bearing portion by retraction of the belt from the spool reel thereby compressing the spring assembly, whereby a reaction load is generated by the spring assembly counteracting the retraction of the belt. | ||||||
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