| 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 | OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT DESCRIPTION | US13828499 | 2013-03-14 | US20130306796A1 | 2013-11-21 | Marcos Alazraki |
| The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of “designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank”. | ||||||
| 142 | COMPOSITE MATERIAL STRUCTURE, AND AIRCRAFT WING AND AIRCRAFT FUSELAGE PROVIDED THEREWITH | US13881590 | 2012-01-26 | US20130236692A1 | 2013-09-12 | Yuya Tanaka; Hideyuki Suzuki; Yutaka Kanayama; Kazuki Sato; Masatake Hatano; Satoru Saito; Akihisa Watanabe; Ryo Abe |
| Provided is a composite material structure reinforced against stress concentration in the peripheral edge portions of holes and enabled to be reduced in weight. A wing (1) is formed in a box structure. A lower surface outer plate (3) of the wing (1) includes a center section (3b) made of metal extending in one direction and having access holes (5) formed therein, a front section (3a) and a rear section (3c) made of fiber reinforced plastics extending in the one direction and connected to both side portions of the center section (3b). As the metal used for the center section (3b), a titanium alloy or an aluminum alloy is suitable. | ||||||
| 143 | Device for closing an aircraft door, aircraft comprising such a device | US12989205 | 2009-03-27 | US08511610B2 | 2013-08-20 | Alain Depeige |
| An aircraft door closing device, and an aircraft incorporating such a device. The door includes a leaf and, connected to the aircraft fuselage, a frame including an opening configured to take the leaf, the leaf adopting a closed position to block the opening and another position to reveal the opening. The device includes a bearing mechanism, some on the leaf and some on the frame, each formed by a crenelated structure, two crenelated structures being arranged such that the teeth of one pass through notches of the other as the leaf moves from one position to the other, and such that the teeth of the leaf structure bear, in the closed position, on the inside face of the corresponding teeth of the frame structure. | ||||||
| 144 | Composite Panel Insert Ring and Method of Using the Same | US13756460 | 2013-01-31 | US20130174974A1 | 2013-07-11 | Raymond L. Schumacher, JR.; William B. Louder; Douglas E. Arnold |
| Provided is a method of forming a thru-hole through a composite structure having a plurality of internal compartments. An insert ring is connected to the composite structure to create a protective layer around the periphery of a penetration formed within the composite structure. An adhesive is disposed between the composite structure and the insert ring to create a fluid-tight seal between the insert ring and the internal compartments. In this regard, the fluid-tight seal mitigates fluid flow between the internal compartments. | ||||||
| 145 | Aircraft cabin door pressure vent system | US12874061 | 2010-09-01 | US08403265B2 | 2013-03-26 | Greg Gowing; Scott Weber; Elisabeth Archibald; Shad Plante; Matt Wiley |
| Disclosed is an aircraft door including a handle-activated pressure relief system that avoids potentially dangerous pressure differences between the cabin and the atmosphere outside the aircraft. A flow path is created between the inboard and outboard handles on the door. A pressure vent door is located in the flow path. The vent door being is opened when either of the inboard and outboard handle assemblies are activated. Once either handle is rotated beyond a particular point, a spring in the supporting mechanics becomes over-center. At the same time, the vent door comes under the influence of a magnet, snapping the vent open. After the door has been opened, it can be relatched by operating the handles in the reverse direction. The magnet and spring hold the vent door open until the aircraft door is fully latched, sealed, and secured. Only then does the vent door sealingly close. | ||||||
| 146 | Aircraft door actuator mounting assembly | US12355347 | 2009-01-16 | US08256311B2 | 2012-09-04 | David A. Payne; Jim Kern; Stephen Birn |
| An actuator mounting assembly includes a cap, a rod, a spring mechanism, and a switch assembly. The cap is adapted to couple to an actuator. The rod extends through the cap and includes a first end adapted to extend through the actuator and a second end adapted to attach to a fixed location. The spring mechanism is disposed in the cap cavity, is compressible, and has a predetermined preload. The switch assembly is disposed in the cap and adapted to sense relative positioning between the rod and the cap and to provide signals based on the sensed relative positioning. When the rod and the cap are in a first relative position, the switch assembly provides a first signal to the actuator to allow the cap to move axially relative to the rod, but when in a second relative position, the switch assembly discontinues providing the first signal to the actuator. | ||||||
| 147 | Hinge cover integration into door seal edges | US12341299 | 2008-12-22 | US08108980B2 | 2012-02-07 | James V. Eveker; Roger K. Young |
| An aircraft door includes a seal that integrates a flexible silicone seal portion and a rigid blade seal portion into a single continuous seal around the mold line gap between the door and frame. The arrangement allows for the use of space saving piano hinges to mount the door. The seal includes a rigid blade seal around three edges of the door and a flexible hinge cover seal adjacent to the hinge edge of the door. The flexible hinge cover seal is bonded to terminal blocks which in turn can be mounted to the door edge and to the door frame such that the flexible hinge cover seal covers the mold line gap adjacent to the hinge. | ||||||
| 148 | Aircraft with door seal arrangement | US11998129 | 2007-11-28 | US08091831B2 | 2012-01-10 | Thorsten Roming |
| A door arrangement for tightly closing a door opening comprises a door frame, a door which, when closed, is arranged in the door frame, and inner and outer sealing lips. The inner and outer sealing lips run next to each other along a periphery of the door opening between a first surface of the door and a second surface of the door frame, wherein the first and second surfaces face each other. The inner and outer sealing lips bound a space formed between them. The door arrangement further comprises a pressure-reducing device configured to reduce pressure in the space. | ||||||
| 149 | DEVICE FOR CLOSING AN AIRCRAFT DOOR, AIRCRAFT COMPRISING SUCH A DEVICE | US12989205 | 2009-03-27 | US20110042517A1 | 2011-02-24 | Alain Depeige |
| An aircraft door closing device, and an aircraft incorporating such a device. The door includes a leaf and, connected to the aircraft fuselage, a frame including an opening configured to take the leaf, the leaf adopting a closed position to block the opening and another position to reveal the opening. The device includes a bearing mechanism, some on the leaf and some on the frame, each formed by a crenelated structure, two crenelated structures being arranged such that the teeth of one pass through notches of the other as the leaf moves from one position to the other, and such that the teeth of the leaf structure bear, in the closed position, on the inside face of the corresponding teeth of the frame structure. | ||||||
| 150 | Pressure sensor device | US11582901 | 2006-10-18 | US07891607B2 | 2011-02-22 | Mitchell J. Piorkowski |
| The invention is directed to a pressure sensor device for sensing decompression in a compartment, such as an aircraft cockpit, and causing a compartment door to be free to open substantially simultaneously in response to the decompression. The pressure sensor comprises a first pressure port and a second pressure port where both pressure ports are open to the compartment, and the second pressure port has a greater flow restriction than the first pressure port, When the pressure sensor is actuated by a difference in pressure between the first pressure port and the second pressure port caused by decompression in the compartment, the pressure sensor sends a signal either via direct wired in series or to a controller to enable movement of a compartment door in response to the decompression. | ||||||
| 151 | Combined displacement and swivel mechanism | US11466683 | 2006-08-23 | US07832686B2 | 2010-11-16 | Johann Konrad Erben; Jan Wijnia |
| The present application relates to a specially designed hinge mechanism (4) which makes it possible to construct an aircraft door (2) that can be fitted in a fuselage (3) so as to be displaceable and swivellable on the fuselage (3). Furthermore, the invention relates to an aircraft door (2) comprising at least one such hinge mechanism (4) designed in this way, to a fuselage (3) with at least one aircraft door (2) that is linked to at least one hinge mechanism (4), designed in this way, on the fuselage (3), as well as to the use of at least one hinge mechanism (4) for installation of an aircraft door (2) on a fuselage (3). The hinge mechanism (4) essentially comprises a displacement mechanism (5, 6) as well as a telescopic scissor-type mechanism (7-12). The displacement mechanism (5, 6) can be linked to an aircraft door (2) and is kinematically designed such that as a result of its activation the aircraft door (2) can be displaced from its home position in the direction of the fuselage (3). The scissor-type mechanism (7-12) can be linked to a fuselage (3) and is kinematically designed such that as a result of its activation the aircraft door (2) is displaceable from the fuselage (3) to a final position, on a polar axis that is aligned perpendicularly in the direction of displacement. | ||||||
| 152 | Sealing profile | US12378596 | 2009-02-17 | US20100133760A1 | 2010-06-03 | Vicente Martinez Valdegrama; Francisco de Paula Burgos Gallego |
| The invention comprises an elastic material in order to carry out the joining and sealing between a first (2) and a second (3) element; and which has the aim of avoiding the formation of pinching of the sealing profile when carrying out the assembly and sealing between the first (2) and second (3) elements. For this, the sealing profile (6 and 7) presents a wedge-shaped configuration which projects with respect to the first (2) element, and on the sloping surface of which the second (3) element presses in order to facilitate its deformation and the assembly and sealing of the first (2) and second (3) element, in which position the surface of the wedge shape that projects with respect to the first element (2) presses against the second element (3). The invention is preferably applicable to aeronautical structures, particularly to those structures where both first and second elements form part of the aerodynamic surface. | ||||||
| 153 | Hinge cover integration into door seal edges | US11051595 | 2005-02-04 | US07575195B2 | 2009-08-18 | James V. Eveker; Roger K. Young |
| An aircraft door includes a seal that integrates a flexible silicone seal portion and a rigid blade seal portion into a single continuous seal around the mold line gap between the door and frame. The arrangement allows for the use of space saving piano hinges to mount the door. The seal includes a rigid blade seal around three edges of the door and a flexible hinge cover seal adjacent to the hinge edge of the door. The flexible hinge cover seal is bonded to terminal blocks which in turn can be mounted to the door edge and to the door frame such that the flexible hinge cover seal covers the mold line gap adjacent to the hinge. | ||||||
| 154 | Hinge Cover Integration Into Door Seal Edges | US12341299 | 2008-12-22 | US20090095841A1 | 2009-04-16 | James V. Eveker; Roger K. Young |
| An aircraft door includes a seal that integrates a flexible silicone seal portion and a rigid blade seal portion into a single continuous seal around the mold line gap between the door and frame. The arrangement allows for the use of space saving piano hinges to mount the door. The seal includes a rigid blade seal around three edges of the door and a flexible hinge cover seal adjacent to the hinge edge of the door. The flexible hinge cover seal is bonded to terminal blocks which in turn can be mounted to the door edge and to the door frame such that the flexible hinge cover seal covers the mold line gap adjacent to the hinge. | ||||||
| 155 | COMMUNICATION FLAP AND AIRCRAFT PROVIDED WITH ONE SUCH FLAP | US11917791 | 2006-06-06 | US20090084039A1 | 2009-04-02 | Bernard Guering; Bernard Groh; Christian Bergeret |
| A communication flap including a door for closing or freeing the access to an opening on a wall, the door having at least two leaves. A first leaf is pivotably mounted on the wall in such a way as to open and close the door, and a second leaf is pivotably mounted on the first leaf in such a way as to enable a range of movement around the first leaf. The disclosed embodiments also relate to an aircraft provided with one such flap. | ||||||
| 156 | Door arrangement and aircraft | US11998129 | 2007-11-28 | US20080164373A1 | 2008-07-10 | Thorsten Roming |
| A door arrangement for tightly closing a door opening comprises a door frame, a door which, when closed, is arranged in the door frame, and inner and outer sealing lips. The inner and outer sealing lips run next to each other along a periphery of the door opening between a first surface of the door and a second surface of the door frame, wherein the first and second surfaces face each other. The inner and outer sealing lips bound a space formed between them. The door arrangement further comprises a pressure-reducing device configured to reduce pressure in the space. | ||||||
| 157 | Doors of Aircraft Cabins | US11794549 | 2006-01-06 | US20080093504A1 | 2008-04-24 | Patrick Lamat; Christian Romec; Didier Molinari |
| The invention relates to a guard for the upper part of a door (2) of an aircraft, consisting of: a composite comprising a composite and/or stainless steel strip (14) which forms the core of the guard (1) and which renders same flexible and resistant, a silicon which is optionally reinforced with fibres and a polyester. | ||||||
| 158 | Pressure-Difference Warning System | US11795433 | 2006-01-19 | US20080088483A1 | 2008-04-17 | Robert Hellwig |
| The present invention relates to a pressure-difference warning system comprising an acoustic signal device, comprising an energy supply device and comprising a pressure sensor. The pressure sensor is designed for measuring a pressure difference between an interior region and an exterior region. The energy supply device is designed for providing energy for operating the warning system. The acoustic signal device is designed for outputting an acoustic signal if the measured pressure difference exceeds a specifiable threshold value. | ||||||
| 159 | COMBINED DISPLACEMENT AND SWIVEL MECHANISM | US11466683 | 2006-08-23 | US20070045471A1 | 2007-03-01 | Johann ERBEN; Jan WIJNIA |
| The present application relates to a specially designed hinge mechanism (4) which makes it possible to construct an aircraft door (2) that can be fitted in a fuselage (3) so as to be displaceable and swivellable on the fuselage (3). Furthermore, the invention relates to an aircraft door (2) comprising at least one such hinge mechanism (4) designed in this way, to a fuselage (3) with at least one aircraft door (2) that is linked to at least one hinge mechanism (4), designed in this way, on the fuselage (3), as well as to the use of at least one hinge mechanism (4) for installation of an aircraft door (2) on a fuselage (3). The hinge mechanism (4) essentially comprises a displacement mechanism (5, 6) as well as a telescopic scissor-type mechanism (7-12). The displacement mechanism (5, 6) can be linked to an aircraft door (2) and is kinematically designed such that as a result of its activation the aircraft door (2) can be displaced from its home position in the direction of the fuselage (3). The scissor-type mechanism (7-12) can be linked to a fuselage (3) and is kinematically designed such that as a result of its activation the aircraft door (2) is displaceable from the fuselage (3) to a final position, on a polar axis that is aligned perpendicularly in the direction of displacement. | ||||||
| 160 | Method of sealing a panel to an aircraft structure | US10238955 | 2002-09-11 | US06915987B2 | 2005-07-12 | David Fisher; Raja S. Abbas; John S. Robbens; Stan Wood |
| The invention relates to a method of providing a seal between an aircraft structure (14) and a removable panel (26) mountable on the structure to close an opening (12) therein. According to the invention, the method comprises applying a sealant compound (28) for example a polysulphide rubber compound, to one of the structure and the panel, forming a rebate (46) in the sealant compound, and providing a sealant tape (48) to fit within the rebate. Subsequently, the panel is fastened to the structure with the seal (50) comprising the sealant compound and the sealant tape being sandwiched between the structure and the panel and encircling the opening. | ||||||
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