| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Explosion vent including buckle tab plate | US13408429 | 2012-02-29 | US09199789B2 | 2015-12-01 | 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 a central section of the 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. | ||||||
| 82 | Rapid decompression detection system and method | US12921324 | 2009-03-09 | US09180959B2 | 2015-11-10 | 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. | ||||||
| 83 | DECOMPRESSION PANEL FOR USE IN AN AIRCRAFT | US14228524 | 2014-03-28 | US20150115102A1 | 2015-04-30 | Thomas Perkins; Michael J. Olliges; Allan A. Loken; Hannah Rebecca Arm; Jeremy Ryan Glaze Tatum |
| A decompression panel includes a body portion having a first end and a second end opposing the first end. The decompression panel also includes a tab extending along the first end and a flange coupled to the body portion. The flange defines a slot adjacent the second end. The decompression panel is secured in an airplane cabin by the tab and slot features, such that unwanted access to areas behind such panels is prevented. | ||||||
| 84 | GRILLE FOR VEHICLE WALL OPENING | US14034627 | 2013-09-24 | US20150087217A1 | 2015-03-26 | Lon E. Switzer; Fred P. Siebert |
| A grille for a vehicle wall opening may comprise a frame, a pair of first louvers, and a second louver. The frame may be receivable on the vehicle wall in an installed position extending around the opening, and may have an inboard side and an outboard side. The pair of first louvers may be supported on the frame, and may be transversely inclined to an outboard direction at a first angle. The second louver may be located between the first louvers, fixed relative to the first louvers, and inclined to the outboard direction at a second angle different from the first angle. | ||||||
| 85 | Avionics cargo hold module having an upper integrated floor | US14138588 | 2013-12-23 | US20140175226A1 | 2014-06-26 | 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. | ||||||
| 86 | AIRCRAFT COCKPIT HAVING A LOWERED FLOOR FOR WALKING ON | US14138572 | 2013-12-23 | US20140175225A1 | 2014-06-26 | Yves Durand; Bernard Guering |
| A cockpit for an aircraft nose, the cockpit having a floor that acts solely as a floor for the crew to walk on and that is lower than the height of the cabin floor situated behind the cockpit. The cockpit also has a stair connected to the floor in order to enter and leave the cockpit. This arrangement enlarges the volume of the cockpit and enables equipment to be housed therein that previously used to be housed in the zone that is difficult to access that is situated under the cockpit and that also contains the bay for storing landing gear. | ||||||
| 87 | Decompression device and decompression system | US13230903 | 2011-09-13 | US08714483B2 | 2014-05-06 | Stephan Hoetzeldt; Oliver Schindler; Gerhard Penski |
| A decompression device is provided having a frame element, in which at least one decompression opening is formed, and a cover is fastenable by means of a fastening device to the frame element in order in a first position to close the decompression opening formed in the frame element. The fastening device includes at least one holding clip and at least one receiving device that is complementary to the holding clip. The holding clip and the receiving device complementary to the holding clip are situated in engagement with one another when the cover is situated in its first position and are adapted to move out of engagement when a predetermined differential pressure acts upon the cover in order to enable the cover to move relative to the frame element into a second position, in which the cover releases the decompression opening formed in the frame element. | ||||||
| 88 | System and method for securing a panel such as an aircraft air grille | US12146253 | 2008-06-25 | US08696418B1 | 2014-04-15 | James A. Griffin |
| A system for securing a panel is described. In an exemplary embodiment, the panel is an air grille, such as, for example, an aircraft air-return air grille. | ||||||
| 89 | METHOD AND APPARATUS FOR ESTABLISHING AN ENVIRONMENTALLY ISOLATED VOLUME | US13781004 | 2013-02-28 | US20130340954A1 | 2013-12-26 | 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. | ||||||
| 90 | Decompression vent latching mechanism | US12264150 | 2008-11-03 | US08602464B2 | 2013-12-10 | Morteza Yadollahi |
| A decompression vent latching apparatus, includes a flap placed on a door opening to a first area from a second area, a housing fastened to the flap on the door, a plunger mounted within the housing, having rotational and lateral movement within the housing, a stop block connected to the plunger, a pair of tip blocks having movement restricted by the stop block connected to the plunger when contacting the stop block, the tip blocks being controlled to be a predetermined distance away from the stop block, and a locking unit connected to the pair of tip blocks providing a closed or open position. | ||||||
| 91 | OVERPRESSURE DOOR FOR AN AIRCRAFT | US13874558 | 2013-05-01 | US20130292515A1 | 2013-11-07 | Yannick Sommerer; Alexandre Massol |
| The overpressure door, of axial type, includes a hatch configured to pivot about an axis between a closed position and an open position and an aerodynamic appendage securely attached to the hatch. The aerodynamic appendage makes it possible to produce a deflection of the external flow in the open position of the hatch of the door. | ||||||
| 92 | Decompression device for an aircraft | US12693847 | 2010-01-26 | US08567721B2 | 2013-10-29 | Jens Voss; Markus Horst; Ingo Roth |
| The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel. | ||||||
| 93 | DOOR ASSEMBLY WITH TWO DOOR LEAVES | US13919273 | 2013-06-17 | US20130269258A1 | 2013-10-17 | Maik Koch; Matthias Breuer |
| A door assembly for a vehicle with two door leaves is stated. In each case the door leaves can be opened in such a manner that the maximum angle of opening between them can be limited. After a door leaf has been opened, the door leaves can thus only be pivoted together so that opening the first door leaf results in closing the second door leaf. As a result of this, access to a space in a vehicle may be controlled. | ||||||
| 94 | DECOMPRESSION UNIT | US13880201 | 2011-10-13 | US20130206909A1 | 2013-08-15 | 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. | ||||||
| 95 | Lining for an aircraft | US12521240 | 2008-01-18 | US08490922B2 | 2013-07-23 | Hermann Benthien; Radoslaw Lazar |
| A lining for an aircraft. The lining separates an intermediate space from an interior space of the aircraft in a pressuretight 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. 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. This pressure corresponds to the air pressure prevailing at an altitude above 10,000 m. 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. | ||||||
| 96 | Avionic door lock system | US11041616 | 2005-01-24 | US08398025B2 | 2013-03-19 | Mitchell J Piorkowski; Paul W Bandy; Darrell W Gaston, Jr.; Binh C Truong; Dwight R Schaeffer; Shannon J Kupfer; Steven D Flickinger; Julie M Shinn; James J Johnson; Steven L Wehr; Mark E 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. | ||||||
| 97 | FIREPROOF BIDIRECTIONAL DECOMPRESSION PANEL | US12637721 | 2009-12-14 | US20110139931A1 | 2011-06-16 | Fred W. Opp; Keith A. Krueger |
| A fireproof, bi-directional decompression panel includes a frame member and a pressure relief panel member that is releasably retained to the frame member to removably cover a decompression vent opening of an aircraft partition, such as a sidewall of an aircraft cargo compartment. During a decompression event, the pressure relief panel member is released bi-directionally in either of two opposing directions from the frame member when a predetermined pressure differential exists across the partition. The decompression panel assembly is fire resistant, and has reduced weight and fewer parts than prior conventional decompression panel assemblies. | ||||||
| 98 | Latch device of cockpit door of an aircraft | US11905519 | 2007-10-02 | US07896290B2 | 2011-03-01 | Fumiaki Saku; Tadashi Watanabe; Yasuo Sekikawa |
| A latch device for detecting pressure reduction of a cockpit in an aircraft and releasing a bolt and a stopper device are provided so as to prevent a cockpit door from unexpectedly opening by an impact. A main latch device 100 of the cockpit door has a frame 112 fixed to a door panel, and a latch base 120 is mounted to the frame 112 capable of pivotal rotation with a pin 122 as a fulcrum. A bolt 132 is inserted into a catch in conjunction with a door handle 130. A holding/releasing portion 150 holds the latch base 120. When a pressure difference occurs between a cockpit 4 and a cabin 5, a pressure-sensing piston 160 is pushed in, a trigger 170 and a flapper 180 are rotated and the latch base 120 is released. A stopper device 190 regulates movement of the trigger 170 by movement of an inertial piston 192 when an impact force is applied from the cabin 5 side. | ||||||
| 99 | Decompression-Element Fastening System For An Aircraft | US12862073 | 2010-08-24 | US20110041293A1 | 2011-02-24 | Juergen Langediers; Enno Cornelssen; Gerhard Penski |
| A decompression-element fastening system (10) is provided for releasably fastening a trim component (12) serving as a decompression element to a supporting structure (14) in an aircraft internal region. The decompression fastening system (10) comprises at least one bolt (20), a screw (44) configured for pressing the trim component (12) in the direction of the supporting structure (14), and at least one to detent element (22) configured for resilient support on the supporting structure (14). The bolt (20) has a bolt axis (21) and on a first end at least one detent recess (26) and on a second end (28) a first thread (40). The screw (44) is connected by a second thread (42) to the bolt (20). The detent element (22) upon approach of the bolt (20) may slide over the first end (28) thereof and come into engagement with the detent recess (26). If predetermined tensile force acting in the direction of the bolt axis (21) is exceeded, the detent element (22) disengages from the detent recess (26). Thus the decompression fastening system (10) in one device combines and improves a plurality of functions that are conventionally realized separately with increased weight. | ||||||
| 100 | DIFFERENTIAL PRESSURE-CONTROLLED LOCKING MECHANISM | US12663810 | 2008-06-05 | US20100193637A1 | 2010-08-05 | Maik Szarszewski |
| A differential pressure-controlled locking mechanism (10) comprises a housing (12), as well as a first pressure chamber (14) which is arranged in the housing (12) and which is connectable to a first ambient zone. A second pressure chamber, arranged in the housing (12), is connectable to a second ambient zone and is separated from the first pressure chamber (14) by a mobile separating device (18). The separating device (18) is in an inactive position when the pressure in the first pressure chamber (14) is equal to the pressure in the second pressure chamber. Conversely, the separating device (18) is movable from its inactive position into a differential pressure position when a predetermined differential pressure acts on the separating device (18). An actuation element (22), which is held in a first position by the separating device (18) when the separating device (18) is in its inactive position, is movable into a second position when the mobile separating device (18) is in its differential pressure position. A latch (32) is held in a locking position when the actuation element (22) is in its first position, and is movable into an unlocking position when the actuation element (22) is in its second position. | ||||||
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