| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | LINING FOR AN AIRCRAFT | US12521240 | 2008-01-18 | US20100096500A1 | 2010-04-22 | Hermann Benthien |
| The invention relates to a lining 1 for an aircraft. The lining 1 separates an intermediate space 6 from an interior space 7 of the aircraft in a pressure tight manner. The lining panels extend either substantially horizontally or are fastened approximately vertically on a lining framework formed by profiles for connection to the fuselage cell 2. According to the invention, at least one of the lining panels allows automatic pressure equalization between the interior space and the intermediate space in the event that the pressure in the interior space drops to something in the order of 0 hPa (known as “rapid decompression”). This pressure corresponds to the air pressure prevailing at an altitude above 10,000 m. For this purpose, mounts of the lining panels are provided with predetermined breaking points. The predetermined breaking points are formed in particular by plastic nuts, the thread of which tears away when a critical load-bearing capacity is exceeded. | ||||||
| 162 | Internal security door for an aircraft | US11195744 | 2005-08-03 | US07578477B2 | 2009-08-25 | Clive French; Smail Maksen |
| This door consists of: an internal structure (16) in which at least two compartments are executed; a panel (18) mounted in each of the compartments, and holding means of each panel (18) in the corresponding compartment. These means permit the release of the panel when a predetermined load, in a given direction, is applied to this panel. | ||||||
| 163 | Door which is intended to be positioned between the cockpit and the cabin of an aircraft | US10538446 | 2003-12-04 | US07568659B2 | 2009-08-04 | Serge Roques; Olivier Pujol; Dominique Prost; Philippe Malaval |
| The invention relates to a door (8) designed to be inserted between a cockpit and a cabin of an aircraft, the door comprising a cockpit side (8a) and a cabin side (8b). According to the invention, the door comprises at least one trapdoor (22) capable of closing off a passageway (20) passing through the door and secondly being opened towards the cabin side, the door also comprising a locking/unlocking mechanism (30) of the trapdoor arranged on the cockpit side and that can automatically unlock the trapdoor when the difference between a cockpit pressure and a cabin pressure corresponding to the air pressures applied on the cockpit side and the cabin side of the door respectively is greater than a predetermined value. | ||||||
| 164 | FIRE BARRIER FOR AN AIRCRAFT FUSELAGE | US12260902 | 2008-10-29 | US20090050741A1 | 2009-02-26 | Rainer Muller |
| When a fire breaks out, air flows that promote the spread of fire may occur in the region between the load bay and the skin of the aircraft. According to one embodiment of the present invention, a fire barrier is disclosed that allows rapid decompression of the passenger cabin in the normal operating mode of the aircraft and prevents flashovers in case of a fire. In this case, the fire barrier may be arranged at different positions in the intermediate wall space of the aircraft. | ||||||
| 165 | Flight deck security pocket door system | US11026889 | 2004-12-30 | US07441726B2 | 2008-10-28 | David S Melberg; Jonathan T Barrows |
| A security pocket door traverses within a security bulkhead wall that defines a pocket, within which the pocket door traverses, and a through passage to permit people, carts and luggage to pass. The pocket door has an upper door track mechanism and a lower door track mechanism that engages a corresponding upper and lower track mechanism of the bulkhead and floor, respectively. The bulkhead door locks with at least one solenoid with a locking pin that engages a hole in a tab of the pocket door. The locking pin creates a magnetic field with a magnet located in the tab to send a signal to the flight deck in order to indicate a closed and locked or an unlocked pocket door condition. When the pocket door is in its closed position, the door perimeter overlaps the bulkhead on at least three sides of the door and also overlaps with the floor. | ||||||
| 166 | AIRCRAFT FLOOR TO FUSELAGE ATTACHMENT | US11683228 | 2007-03-07 | US20080217478A1 | 2008-09-11 | Robert D. Keeler; Albert L. Neal |
| A floor to fuselage attachment structure incorporates a truss having an upper angled attachment engaging the floor proximate an edge and extending at an angle upward from the floor edge to attach to the fuselage. Additionally, the truss includes a lower angled attachment engaging the floor proximate the edge and extending at an angle downward to attach to the fuselage. The upper and lower angled attachments support the floor with the edge spaced from the fuselage and further have a plurality of apertures for providing airflow between a first volume above the floor and a second volume below the floor. | ||||||
| 167 | Deceleration device | US11715285 | 2007-03-07 | US20070235588A1 | 2007-10-11 | 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. | ||||||
| 168 | Decompression lock | US11635311 | 2006-12-07 | US20070158955A1 | 2007-07-12 | Bernhard Homner |
| Decompression locks are required in order to achieve a rapid compensation of pressure in case of a sudden increase in pressure in one of two areas which are separated by a pressure tight wall. Decompression locks are used where different pressures in two separate areas have to be compensated rapidly. The purpose of this invention is to provide an improved decompression lock or an improved structural unit with two adjacent decompression locks acting in opposite directions. The improvements include a reduction in weight, simplified installation, a lower number of constituent parts, and a resulting reduction in overall cost. | ||||||
| 169 | Door configured to close an opening inside an aircraft | US11195749 | 2005-08-03 | US20060169840A1 | 2006-08-03 | Clive French; Smail Maksen |
| This door includes a device that permits air to flow through the door in one direction but prevents this flow of air in the opposite direction. On the attached illustration, the door includes at least a window (74), that less air pass through as well as an elastic membrane (76) covering window (74). Elastic membrane (76) includes on the one hand an area that is airtight facing window (74) and capable of fully covering it and on the other hand, an area that is pervious to air near the impervious area. | ||||||
| 170 | Internal security door for an aircraft | US11195744 | 2005-08-03 | US20060169839A1 | 2006-08-03 | Clive French; Smail Maksen |
| This door consists of: an internal structure (16) in which at least two compartments are executed; a panel (18) mounted in each of the compartments, and holding means of each panel (18) in the corresponding compartment. These means permit the release of the panel when a predetermined load, in a given direction, is applied to this panel. | ||||||
| 171 | INCREASED SECURITY FLIGHT DECK DOOR STRIKE APPARATUS AND METHOD | US10966264 | 2004-10-15 | US20060102788A1 | 2006-05-18 | Mitchell Piorkowski; Jann Garrett; Douglas Emsley |
| A door strike apparatus for enabling opening of a door in the event of a decompression condition experienced within a flight deck area includes a housing supported adjacent the door and a strike arm movable between a locked state restricting rotation of the door and an unlocked state permitting rotation of the door. A solenoid having a lock member retracted from the strike arm when the strike arm is in the unlocked state and engaged with the strike arm when the strike arm is in the locked state. The solenoid is responsive to the decompression condition and selectively toggles the lock member out of engagement with the strike arm to permit automatic unlocking of the strike arm and opening of the door under the decompression condition and into engagement with the strike arm to permit selective locking of the door when the decompression condition is absent. | ||||||
| 172 | INSULATING BAFFLE FOR A FLOOR SHEAR TRUSS | US10807087 | 2004-03-23 | US20050224647A1 | 2005-10-13 | Gregory Tubbs |
| An insulation baffle for a mobile platform. The baffle is secured to a structure separating different lobes of the mobile platform. The baffle includes a main body portion and at least one blow out portion. A perimeter of the blow out portion is defined by at least one recess. The recess also forms a web portion that connects the blow out portion with the main body portion. A depth of the recess is predetermined such that the web portion formed by the recess will sever when a pressure differential between the different lobes exceeds a predetermined threshold. When the web portion severs at least a section of the blow out portion separates from the main body portion to air to pass between the lobes so that the pressure differential is reduced to approximately zero. | ||||||
| 173 | Avionic door lock system | US11128809 | 2005-05-13 | US20050218266A1 | 2005-10-06 | Paul Bandy; Darrell Gaston; Binh Truong; Dwight Schaeffer; Shannon Kupfer; Steven Flickinger; Steven Wehr; James Johnson; Julie Shinn; Mark Smith |
| A security system adapted for use on an aircraft to prevent unauthorized access into a cockpit area of the aircraft via a cockpit door. The system includes a keypad accessible by individuals in a cabin area of the aircraft. A logic system is in communication with the keypad and also with a switch disposed inside the cockpit. Occupants of the cockpit, via the switch, have the ability to manually unlock the cockpit door, to deny the request for entry, or to do nothing, in which case the door will be automatically unlocked after the expiration of a predetermined time interval. The switch further provides a cut-off switch which enables the power to be removed from the system if necessary. In addition, a display system may be employed to notify the occupants of the cockpit that entry into the cockpit has been requested. | ||||||
| 174 | Cockpit door of aircraft | US10759252 | 2004-01-20 | US06945497B2 | 2005-09-20 | Fumiaki Saku; Tadashi Watanabe; Yasuo Sekikawa |
| A cockpit door body 10 can be opened toward a cockpit in a direction shown by arrow R1 by a crew inside a cockpit 3 by manipulating a knob on a first hinge device 40. When rapid decompression occurs in the cockpit, a mechanical pressure-sensitive device of the first hinge device 40 operates to release a bolt from a catch. By the difference in pressure between the cabin and the cockpit, the door body 10 opens in the direction of arrow R1 to thereby reduce pressure difference. When rapid decompression occurs in cabin 4, a second latch device 60 detects this pressure difference and operates mechanically to rotate a link lever 62 to release a stopper 64 from a catch 66. Flaps 30 and 32 are opened toward cabin 4 in the direction of arrow R2 by the difference in pressure between the cockpit and cabin to thereby reduce pressure difference. | ||||||
| 175 | Avionic door lock system | US11041616 | 2005-01-24 | US20050178907A1 | 2005-08-18 | Mitchell Piorkowski; Paul Bandy; Darrell Gaston; Binh Truong; Dwight Schaeffer; Shannon Kupfer; Steven Flickinger; Julie Shinn; James Johnson; Steven Wehr; Mark Smith |
| A security system adapted for use on an aircraft to prevent unauthorized access into a cockpit area of the aircraft via a cockpit door. The system includes a keypad accessible by individuals in a cabin area of the aircraft. A logic system is in communication with the keypad and also with a switch disposed inside the cockpit. Occupants of the cockpit, via the switch, have the ability to manually unlock the cockpit door, to deny the request for entry, or to do nothing, in which case the door will be automatically unlocked after the expiration of a predetermined time interval. A pressure sensor in communication with the controller allows the electronic door locking member to be automatically overridden, and the door immediately opened, in the event of a decompression condition occurring in the cockpit. | ||||||
| 176 | Integrated cockpit door lock and access system | US10911842 | 2004-08-05 | US20050006528A1 | 2005-01-13 | Sami Movsesian; Binh Truong; Stephen Wiles; Ravinder Jain; Dinanath Gharmalkar; Danny Valdez; Stephen Kelekian; Gary Bartz |
| An electromechanical flight deck door locking system capable of functioning to keep a cockpit door locked in the event of an interruption in electrical power to the system. The flight deck door locking system includes a locking assembly including a locking component and a manually graspable handle for displacing the locking component. Further, the locking system includes an electronic control panel configured to receive data from an individual seeking access to the cockpit and for electrically locking and unlocking the locking assembly. The locking system also includes a mechanical locking assembly, such as a key lock, whereby a user can use a key to lock and unlock the door if electrical power to the system is unavailable. | ||||||
| 177 | Pressure sensing dead bolt | US10491977 | 2004-07-13 | US20040239126A1 | 2004-12-02 | John Pratt; Timothy S Rozema |
| An apparatus, system and method including a latching device for displaceably retaining a panel relative to a frame. The latching device includes at least a bolt which is carried on the latching device and is operatively associated with the panel to prevent disengagement of the panel. The latching device includes at least one pressure responsive device operatively coupled to the bolt to retain the bolt in a desired position and release the bolt when a predetermined pressure differential occurs relative to two, generally opposite, sides of the panel or when a pressure decrease occurs on one side of the panel. | ||||||
| 178 | DOOR REINFORCEMENT SYSTEM | US10385928 | 2003-03-11 | US20040177561A1 | 2004-09-16 | Magdy Morssi Youssef |
| A door reinforcement system comprises two pairs of assemblies, each assembly having subassemblies on the inside and the outside of the door. The inside subassemblies include a plate with a channel for housing a sliding bolt, and may include three subassemblies with two bolts, each of which spans a subassembly attached to the wall structure and a subassembly attached to the door. By providing the at least two pairs of assemblies, a better reinforment is obtained by reinforcing against the torque that would be present with a single dead bolt. | ||||||
| 179 | Pocket door with pivoting panel | US10382257 | 2003-03-05 | US20040173327A1 | 2004-09-09 | Charles F. Steel; Chris Steel |
| This invention discloses a pocket door. The pocket door is capable of pivoting on hinges between a frame that holds the pocket door and allows it to slide in and out of a pocket to open and close a passageway. More specifically, the pocket door is hinged to the moving frame and also includes a two-part panel, where each panel is separated from an adjacent panel by a hinge that is capable of allowing the panels to move between flush engagement where the two panels lie in the same plane and a position where the panels are no longer lying in the same plane. | ||||||
| 180 | Ballistic vent apparatus | US10300306 | 2002-11-20 | US06672195B1 | 2004-01-06 | Wesley M. Plattner |
| A ballistic vent apparatus for use in a cockpit door of an aircraft to provide venting and communication between the cockpit and the cabin of an aircraft while preventing bullets and/or splinters from passing through the ballistic vent apparatus. The present invention provides a frame having a U-shaped cross-section adaptable to receive a cross-section of the cockpit door of the aircraft. A pair of opposing and substantially similar supports are connected to the frame, and each of the supports has a plurality of longitudinally spaced slots formed therein in a substantially parallel manner. A plurality of ballistic vent angles extend through the slots of the supports and are connected to the supports. A ballistic panel is connected to the frame and extends along a back side of the ballistic vent angles to prevent bullets and/or splinters from passing through the ballistic vent angles. The entire ballistic vent apparatus is fabricated from a ballistic material such as stainless steel. | ||||||
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