| Entries |
| Document | Title | Date |
|---|
| 20080277529 | Nacelle Cowling for Turbojet and Nacelle Comprising at Least One Such Cowling - A nacelle cowling for a turbojet, characterized in that it is provided with a fixed part and a mobile part, the mobile part being adapted to slide along the fixed part, from a closed position wherein the mobile part extends in the extension of the fixed part, up to an open position wherein the mobile part is at least partly superimposed to the fixed part. For example, the fixed part is located in the upper part of the cowling, the mobile part being located in the lower part of the cowling. | 11-13-2008 |
| 20080290217 | Vent Baffle - A vent baffle includes a vent panel having a vent panel opening; a blowout panel carried by the vent panel and covering the vent panel opening; a plurality of fastener openings provided in the blowout panel; a plurality of tear slits communicating with the plurality of fastener openings, respectively; and a plurality of panel fasteners extending through the plurality of fastener openings, respectively, and engaging the blowout panel. A vent baffle system for an aircraft and a method of venting an air flow path between a sidewall monument or structure and an aircraft sidewall in an aircraft fuselage of an aircraft are also disclosed. | 11-27-2008 |
| 20090014590 | HATCH EQUIPPED WITH AT LEAST ONE LOCKING SOCKET CAPABLE OF BEING ACTUATED ON EACH SIDE OF THE HATCH - The present invention relates to a hatch ( | 01-15-2009 |
| 20090152397 | SELECTIVE RELEASE LATCH - A selectively released latch securing a panel in position, but which resists release in response to sudden movement of the panel, yet allowing release in response to a slow and steady movement of the panel. | 06-18-2009 |
| 20090159748 | Decompression Device With Adjustable Release Pressure - The invention relates to a decompression element for pressure equalisation in a cabin of an aircraft, with a decompression element frame ( | 06-25-2009 |
| 20090166473 | Optimized aircraft manhole - The present invention relates to an aircraft manhole comprising a skin panel ( | 07-02-2009 |
| 20090173823 | Method and component for determining load on a latch assembly - A cowl assembly for an engine nacelle including a first and second cowl door mounted for movement between an open position and a closed position. A latch assembly retains the first and second cowl doors in the closed position by having a latch retained in a latch housing on the first cowl door to engage a keeper retained in a keeper housing on the second cowl door. A pin retains the latch to the latch housing. The pin defines an internal bore. A sensor in the internal bore determines a signal indicative of a load on the pin, wherein the signal is determinative of whether the cowl doors are in the open or closed position. A transmitter conveys the signal to a location remote from the sensor. The signal can also be used to set the pre-load on the latch assembly. | 07-09-2009 |
| 20090173824 | CLOSURE SYSTEM FOR A SUPPORT STRUCTURE - System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way. | 07-09-2009 |
| 20090179110 | Extended Decompression Flap Arrangement - The invention concerns an apparatus for producing a rapid air pressure equalisation between regions of an aircraft fuselage which are separated from each other by an aircraft fuselage structure and which have an air pressure difference relative to each other, in an aircraft, in particular a passenger aircraft, comprising at least one through-flow opening in the aircraft fuselage structure, a decompression flap ( | 07-16-2009 |
| 20090242702 | METHODS AND APPARATUS FOR OPTICAL PROPAGATION IMPROVEMENT SYSTEM - An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section. | 10-01-2009 |
| 20090294591 | Cover for an aircraft access opening - The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: | 12-03-2009 |
| 20090308976 | Cover panel for an aircraft, more particularly a landing gear cover panel for a cargo plane - The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap | 12-17-2009 |
| 20100006701 | DEVICE FOR AN AIRCRAFT POWER UNIT | 01-14-2010 |
| 20100096503 | OUTFLOW VALVE HAVING J-SHAPED BELLMOUTH AND CABIN PRESSURE CONTROL SYSTEM EMPLOYING THE SAME - An outflow valve is provided for use in conjunction with an actuator. In one embodiment, the outflow valve includes a frame and a first door rotatably coupled to the frame. The outflow valve is configured to be moved by the actuator between an open position and a closed position. The first door includes: (i) a main body having a sealing edge, and (ii) a J-shaped bellmouth fixedly coupled to the main body proximate the sealing edge. The J-shaped bellmouth is configured to condition fluid flow through the outflow valve when the first door is in the open position. | 04-22-2010 |
| 20100096504 | STRUCTURAL ELEMENT FOR COVERING AN ELONGATE GAP ON AN AERODYNAMIC SURFACE OF AN AIRCRAFT - A covering structural element is adapted to close an elongate gap provided on an aerodynamic surface of an aircraft. Such an element has a strip-shaped body made of metal material, including a fixing portion, adapted to be fixed along one of the longitudinal borders of the elongate gap; a sliding portion adapted to urge in a sliding manner on the other of the longitudinal borders of the strip-shaped gap; and a connection portion, connecting the sliding portion to the fixing portion, the thickness of which is so sized as to allow, in use, a controlled elastic bending of the structural covering element. The covering structural element has a profile so sized as to be tapered at the transition from the fixing portion to the connection portion and from the sliding portion to the connection portion, the covering structural element having a smooth surface on the side intended to face away from the elongate gap. | 04-22-2010 |
| 20100187358 | DECOMPRESSION DEVICE FOR AN AIRCRAFT - 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. | 07-29-2010 |
| 20100243809 | OPENING PLUG AND METHOD OF INSTALLING THE SAME - A device is used to plug an opening in a structure having a front side and a back side. The device includes a removable plug body for plugging the opening, and a retainer that is expandable into engagement with the back side of the structure to retain the plug in the opening. Means coupled with the retainer and the plug is provided for expanding the retainer. | 09-30-2010 |
| 20110073709 | METHODS AND APPARATUS FOR A FRANGIBLE SEAL FOR DEPLOYABLE FLIGHT STRUCTURES - A frangible seal includes a first region penetratable by a deployable structure configured to selectably extend through an opening in a housing and extend beyond an outer surface of the housing, and a second region configured to adhere to a portion of the outer surface of the housing surrounding the opening. The first region and the second region includes a polymer layer having a metalized surface (e.g., aluminized polyimide) and a non-metalized surface, and an ablative coating provided on the metalized surface of the polymer layer. | 03-31-2011 |
| 20110133034 | AIRCRAFT NACELLE INCORPORATING A DEVICE FOR PROTECTING AN ACCESS FLAP FOR A LOCKING SYSTEM - An aircraft includes a part defining an aerodynamic surface against which flows an air stream, with at least one hood able to block an opening made at the aerodynamic surface, kept in the closed position by at least one locking mechanism, and an access flap for the locking mechanism, pivoting relative to the hood around an axis substantially parallel to the flow direction of the air stream and including elements for keeping it flattened against the hood, characterized in that it includes a device for protection of the access flap that includes a coverage plate that pivots around an axis of rotation, and which is able to occupy a first position in which it projects relative to the aerodynamic surface and another position in which after pivoting around the axis of rotation, it is flattened against the outside surface of the access flap such that the protective device limits the appearance of a scoop phenomenon. | 06-09-2011 |
| 20110290941 | Attachment system of aircraft components - An attachment system for attaching a component ( | 12-01-2011 |
| 20110297787 | DUAL FUNCTION DOOR FOR AN AIRCRAFT ENGINE NACELLE - The invention relates to a door ( | 12-08-2011 |
| 20120025021 | PAYLOAD DOOR AND ELEVATOR SYSTEM - A payload door and elevator system for the translation of a payload such as a camera, from a stowed position within an aircraft fuselage to a deployed position projecting through an aperture formed in the wall of the fuselage. The system employs a translation component engaged to vertically translate the payload and operatively positioned inline with the aperture. Payload doors sealing the aperture horizontally translate in opposing directions once vertically translated from sealed engagement with the aperture. The horizontal translation alleviates much of the stress imparted to doors on aircraft which move to vertical positions in or extending from the aperture in the fuselage. | 02-02-2012 |
| 20120097794 | AIRCRAFT PANEL COMPRISING AN OPENING EQUIPPED WITH A SURROUND - The subject of the invention is an aircraft panel, notably a fuselage panel of the aircraft, comprising at least one opening equipped with a surround intended to accept a closing-off device that closes off the opening, the panel comprising at least one exterior surface, the surround surrounding the opening being fixed to the panel, forming an interface for fitting the closing-off device, and comprising at least one lip extending towards the centre of the opening, the lip supporting the closing-off device, and the surround having an external face interposed between the exterior surface of the panel and the closing-off device; the panel is characterized in that the surround comprises fixing means which work by gripping the edge of the opening of the panel. | 04-26-2012 |
| 20120280081 | APPARATUS FOR FACILITATING ACCESS TO A NACELLE INTERIOR - A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a mounting assembly including at least one power drive system. The fan cowl is movable with respect to the engine along the axis toward at least one of the inlet end and the exhaust end. | 11-08-2012 |
| 20120280082 | APPARATUS FOR FACILITATING ACCESS TO A NACELLE INTERIOR AND METHOD OF ASSEMBLING THE SAME - A nacelle for housing an engine includes a fan cowl sized to cover at least a first axial portion of the engine. The engine includes an inlet end, an exhaust end, and an axis extending through the engine from the inlet end through the exhaust end. The fan cowl is coupled to an engine mounting pylon via a slider-type mounting system that includes at least one slider track assembly defining at least one slot therein. The at least one slot is configured to receive at least one fan cowl slider fitting. | 11-08-2012 |
| 20120325967 | CLOSING MEMBER FOR OPENING - An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. | 12-27-2012 |
| 20130015294 | CLOSING MEMBER FOR OPENINGAANM Motohashi; HidetoAACI AichiAACO JPAAGP Motohashi; Hideto Aichi JP - An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. In a door body | 01-17-2013 |
| 20130020439 | SEPARATING ELEMENT FOR A PLATFORM CABIN COMPRISING A PUSH ROD MECHANISM FOR MOVING A LEAF - The separating element ( | 01-24-2013 |
| 20130056584 | METHOD FOR MOUNTING AN AIRCRAFT COMPONENT AND AIRCRAFT ASSEMBLY - A method for mounting an aircraft component, which in the mounted state is movable between a first and a second operating position and is taken up in its first operating position in a mounting area, comprises the measuring of the mounting area, in order to obtain data characteristic of the shape and/or the dimensions of the mounting area. The data characteristic of the shape and/or the dimensions of the mounting area are projected onto the aircraft component arranged in its second operating position. Finally, the aircraft component arranged in its second operating position is adjusted with reference to the projection of the data characteristic of the shape and/or the dimensions of the mounting area. | 03-07-2013 |
| 20140353428 | AIRCRAFT DOOR AND AIRCRAFT COMPRISING THE SAME - An aircraft door | 12-04-2014 |
| 20150108274 | DECOMPRESSION PANEL ASSEMBLY AND METHOD OF EQUALIZING AIR PRESSURE DIFFERENTIAL - Decompression panel assemblies and methods of equalizing air pressure differential are provided. The decompression panel assembly includes a panel comprising an opening defined therein, a vent cover coupled across the opening, and a latching mechanism. The vent cover is configured to move between a first position and a second position. The latching mechanism is configured to maintain the vent cover in the first position when a pressure differential across the panel is below a predetermined value and facilitate the vent cover moving to the second position when the pressure differential across the panel exceeds the predetermined value. | 04-23-2015 |
| 20150136907 | Deployable barrier arrangement for selectively blocking a passage in an aircraft cabin - A deployable barrier arrangement for selectively blocking a passage in an aircraft cabin, wherein the barrier arrangement comprises a substantially longitudinal barrier member and a joint unit for fixing the barrier member to an inner wall of the aircraft cabin. The joint unit is configured to allow for a movement of the barrier member between a stowed position in which the barrier member extends substantially parallel to the inner wall of the aircraft cabin and a deployed position in which the barrier member extends at an angle of approximately 60° to 120° to the inner wall of the aircraft cabin. The joint unit is further configured to allow for a rotational movement of the barrier member about a longitudinal axis of the barrier member. | 05-21-2015 |
| 20150291281 | METHOD AND DEVICE FOR FITTING OUT AN AIRCRAFT NOSE COMPARTMENT IN AN AVIONICS BAY - The subject matter disclosed herein relates to the field of aircraft systems installation. More specifically, the subject matter disclosed herein relates to the installation of avionics cabinets, electrical master boxes and IFE bays. Compared with the arrangements known from the prior art, the subject matter disclosed herein includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, the subject matter disclosed herein uses systems cabinets that incorporate a structural function. It thus allows a reduction in the aerodynamic drag of the aircraft. | 10-15-2015 |
| 20150353203 | ACOUSTICALLY DIFFUSIVE AUXILARY POWER UNIT INLET DOORS - An inlet door for an auxiliary power unit includes a door body with opposed interior and exterior surfaces. The interior surface of the inlet door is curved to diffuse sound waves received by the interior surface. | 12-10-2015 |
| 20160121992 | SHUTTER MECHANISM FOR COVERING A WING DEPLOYMENT OPENING - A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface. | 05-05-2016 |
| 20160130007 | WINDOW MOUNTED RAFT SYSTEM - An inflatable life raft system for an aircraft includes a window coupled to a fuselage portion of the aircraft. A mechanism is used to selectively detach the window from the fuselage. An inflatable life raft is deployable to the exterior of the aircraft upon detachment of the window from the aircraft. | 05-12-2016 |
| 20160176496 | DOOR FOR CLOSING OPENING IN STRUCTURE AND AIRCRAFT | 06-23-2016 |
| 20160201371 | QUICK RELEASE HINGE | 07-14-2016 |
| 20190145144 | HYDRAULIC PISTON ACTUATOR FOR A DOOR | 05-16-2019 |
