| Document |
Document Title |
|
WO/2015/167949A1 |
A positionally releasable vehicle armor arrangement includes, at least one plate positioned proximate a hatch of a hatchway of a vehicle configured to shield an occupant of the vehicle from projectiles, at least one retainer in operable ...
|
|
WO/2015/165651A1 |
The invention relates to an aircraft having a pusher propeller (18), a rear tail assembly (20) and a connection (22) by means of which the tail assembly (20) is fastened. According to the invention, the connection (22) comprises a sound-...
|
|
WO/2015/163764A1 |
An integrated panel made of interconnected laminates comprising stacked first and second metal layers (5, 5', 5") and fibre-reinforced adhesive layers (19) between adjacent metal layers. At the location of the transition from the outer s...
|
|
WO/2015/155477A1 |
The invention relates to a structural assembly (1) of an aircraft turbojet engine nacelle and a thermal protection mat (2) attached to the structure (1), the mat being attached to said structure (1) via at least one attachment device, th...
|
|
WO/2015/156856A1 |
An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configure...
|
|
WO/2015/155065A1 |
The present invention relates to retaining movable components on board an aircraft. In order to be able to transmit higher forces when retaining movable components, a retaining system (10) is provided, which comprises a support structure...
|
|
WO/2015/146690A1 |
The purpose of the present invention is to provide a lightweight composite material structure while limiting reduction in strength. In a composite material structure, which is configured as a fiber-reinforced plastic composite material t...
|
|
WO/2015/146528A1 |
A cap (9) is applied to a securing structure part (1) for securing structure elements (3, 3) using a fastener (5) passed through through-holes (3a) formed in the structure elements (3, 3), and a collar (7) fastened to the tip part (5a) o...
|
|
WO/2015/148690A1 |
A fastener system that includes a female fastener assembly with a housing having a channel defined therein and a switch member movable within the channel between removing and fastening positions. The switch member includes a receiver por...
|
|
WO/2015/142317A1 |
A rotary wing aircraft is provided including an airframe having a nose section located at a forward end. A window assembly is coupled to the nose section. The window assembly includes a frame and a transparent armored window. The frame h...
|
|
WO/2015/142171A1 |
The invention relaters to a connecting element for fastening an aircraft skin to an aircraft primary reinforcing element. The connecting element comprises a shear web and, integrally formed therewith, a frame stabilizing element. The con...
|
|
WO/2015/132167A1 |
The invention relates to a system (100) for mounting a cabin door (1) on a longitudinal aircraft fuselage (2) according to the invention makes it possible to enter and exit a cabin (101). The door (1) and the fuselage (2) have longitudin...
|
|
WO/2015/123004A1 |
An unmanned aerial vehicle (UAV) can be deployed from a small stowed package for flight and stowed back into the package after the flight is complete is disclosed. The UAV is retracted to a volume that is less than half of its fully depl...
|
|
WO/2015/117868A1 |
The invention relates to a soundproof panel having a sandwich structure, which includes two outer walls, a core, and modifying elements that are maintained in a fractal distribution by the core. The panel has an improved trade-off betwee...
|
|
WO/2015/115913A1 |
The invention relates to a multipurpose twin fuselage aircraft (17) that includes a central wing panel (1) which is releasably attached to each of the fuselages (12, 13) and is located between them. The central wing panel includes a nace...
|
|
WO/2015/114048A1 |
An aircraft interior door assembly (10, 20, 30) for selectively increasing usable space within an aircraft lavatory (1) adjacent a passenger doorway area (2) of the aircraft or in the passenger doorway area (2) adjacent the lavatory (1) ...
|
|
WO/2015/116439A1 |
An aircraft transparency assembly includes an aircraft transparency having at least one ply having an outer surface and an extended portion. The assembly also includes a pressure seal configured to engage the extended portion of the ply,...
|
|
WO/2015/109700A1 |
Disclosed is an unmanned aerial vehicle body. The unmanned aerial vehicle body comprises an upper plate and a lower plate opposite to the upper plate, and comprises a connection plate and a middle partition plate. The connection plate is...
|
|
WO/2015/109352A1 |
The invention relates to a device (1) for opening an aircraft door (2) provided in an aircraft fuselage (4), said device comprising: a support arm (3) that can be arranged in an articulated manner between the aircraft fuselage (4) and th...
|
|
WO/2015/105578A1 |
A method and system for monitoring a mandrel (108). A first plurality of transmitting devices (134) is positioned with respect to the mandrel (108). Signals (136) from a portion (150) of the first plurality of transmitting devices (134) ...
|
|
WO/2015/102706A2 |
A UAV includes a body. The body defines a payload opening (14). The payload opening is circular, but any shape may be used. A payload of the UAV is arranged in the payload opening. The payload may be a camera, sensors, a package, etc. A ...
|
|
WO/2015/094059A1 |
A stiffening element 11 comprising at least a first stiffening profile 1and at least a second stiffening profile 2. The first stiffening profile 1 comprises a profile member 4, at least one structural flange 8 is connected to the profile...
|
|
WO/2015/090263A1 |
In order to simplify an integration of systems on an aircraft fuselage, the invention provides a production method for producing a supporting fuselage panel (10) for a fuselage portion of an aircraft fuselage in a region of an aircraft c...
|
|
WO/2015/091674A1 |
The invention relates to acoustic panels. In order to provide a cabin panel that is as simple as possible to produce and has optimised acoustic properties, an acoustic cabin panel (10) is provided comprising a first (12) and a second lay...
|
|
WO/2015/090959A1 |
The invention relates to a passenger aircraft (10) comprising a pressurized cabin which has a crown volume (13) and a passenger deck (12), the passenger deck (12) having at least one passenger compartment (14) which is separated from the...
|
|
WO/2015/092513A1 |
A bonding structure of vehicle members includes a first member formed of resin in a shape of a panel and in which a ridge line is formed by an angular portion divided with respect to a curvature of other portion of a surface thereof, a s...
|
|
WO/2015/082833A1 |
The invention relates to a device (110) for retaining drained fluids for a propulsive assembly, comprising a cavity for storing the drained fluids and two walls (118, 120) mounted at the opening of said cavity, the cavity having a fluid ...
|
|
WO/2015/082799A1 |
The invention relates to a propulsion assembly comprising an engine surrounded by a nacelle (14), means for draining the fluids from the engine and means (18) for guiding said fluids to a retention box (17) arranged outside the engine an...
|
|
WO/2015/079730A1 |
This sheet material (30) comprises an FBL that is welded to one surface (36a) of flame-retardant urethane material (36) by melting the one surface (36a), and a dress cover (34) that is welded to the other surface (36b) of the flame-retar...
|
|
WO/2015/079124A1 |
This support (2) comprises: a frame (2.1); at least three suction cups (2.2); and connecting elements (2.4) for connecting an infrared emitter (4) to the frame (2.1). The frame (2.1) defines a closed outline. The support (2) further comp...
|
|
WO/2015/077313A1 |
An aircraft window mounting assembly having a pressure pane in abutting contact with an inner surface of an exterior pressure pane frame. A bezel is proximate a periphery of the pressure pane and defines an inner opening. The bezel inclu...
|
|
WO/2015/074090A1 |
The invention relates to an interior trim part (2, 3, 4, 5, 6) for the planar installation with similar interior trim parts for producing a wall covering inside an aircraft cell, wherein the interior trim part (2, 3, 4, 5, 6) can be rigi...
|
|
WO/2015/073621A1 |
A bracket that includes a main body portion having a first portion and a second portion that form a first angle therebetween. The first portion includes opposing front and rear surfaces and the second portion includes opposing upper and ...
|
|
WO/2015/069339A2 |
An aircraft window assembly (10) includes a first panel (12) having a first surface (14) and a second surface (16). In a first state in which there is no pressure difference between the first surface (14) and the second surface (16), the...
|
|
WO/2015/063657A1 |
Method to manufacture a plurality of hollow reinforcement structures (3) for panels (P) or aerostructures. The method comprises the following consecutive steps: a) positioning at least one mandrel (2) on the surface of a panel (P) in cor...
|
|
WO/2015/059406A1 |
The invention relates to laminated glazing comprising at least one outer sheet of glass and a polymer sheet, wherein the outer sheet of glass has a maximum thickness of 2 mm and a thermal expansion coefficient of less than 70.10-7 K-1.
|
|
WO/2015/060926A1 |
A decompression panel (206) includes a body portion (212) having a first end (214) and a second end (216) opposing the first end (214). The decompression panel (206) also includes a tab (218) extending along the first end (214) and a fla...
|
|
WO/2015/060925A1 |
A clamp device (30) includes a clamp portion (302) defining a threaded opening (310) therein. The clamp portion (302) is configured to contact a first side (354) of a beam (350). The clamp device (300) also includes a threaded fastener (...
|
|
WO/2015/061303A1 |
A modular floor track adapter system (20) including a plurality of adapter plates (24) laterally sized to span existing aircraft floor beams (22), each of the plurality of adapter plates shaped to interlock with an adjacent adapter plate...
|
|
WO/2015/060904A1 |
A decompression panel (206) for use in an aircraft assembly is provided. The decompression panel (206) includes a body portion (212) including a top end (214) and a bottom end (216), and an array (218) of openings (220) formed in the bod...
|
|
WO/2015/057269A1 |
Decompression panel assemblies and methods of equalizing air pressure differential are provided. The decompression panel assembly (502, 504) includes a panel comprising an opening (506) defined therein, a vent cover (508) coupled across ...
|
|
WO/2015/055834A2 |
A vehicle includes a reconfigurable door (104, 204, 304, 404) having a first surface (106A) and a second surface (106B). There is also an arrangement (112, 116, 117) for configuring the door so that in a first configuration at least part...
|
|
WO/2015/051436A1 |
This invention relates to an Unmanned Aerial Vehicle hereinafter called "Mother UAV" member (11) capable of carrying modules of Sub Unmanned Aerial Vehicle members (12) hereinafter called "Sub UAV" member. More particularly, the method a...
|
|
WO/2015/053836A1 |
Self-aligning fitting assemblies (100) and systems and methods including the same are disclosed herein. The self-aligning fitting assemblies include a barrel-side fitting (160) that includes a plurality of barrel-side attachment holes (1...
|
|
WO/2015/053901A1 |
A modular truss assembly for mechanically and electrically mounting system components of a modular equipment center (MEC 44, 46, 48). A plurality of MECs is spatially distributed throughout the vehicle (10) to service equipment loads. Th...
|
|
WO/2015/049895A1 |
Provided is a joint and an aircraft structure wherein it is possible to position a member relative to a preform with high accuracy. A groove part, into which a plate material (30) is inserted, is formed on a π-shaped joint (20) provided...
|
|
WO/2015/049898A1 |
A joint (20) joins a plate material (26) with a preform (22), wherein an inclined part (28), which is inclined relative to a surface that is orthogonal to a direction in which a tensile load is applied to the plate material (26), is form...
|
|
WO/2015/048695A1 |
An aircraft auxiliary fuel tank system comprising a master tank and a plurality of slave tanks connectable to the master tank. The slave tanks can be easily added or removed to adjust fuel capacity. A rail assembly is provided to assist ...
|
|
WO/2015/038042A1 |
The present invention regards an aeronautical structural section (3) provided for assembly with a mating section (3", 4), the section (3) comprises end portions (17a, 17b) adapted for join-up with said mating section (3", 4). The (3) com...
|
|
WO/2015/032276A1 |
A fuselage butt joint structure (10) connected to an aircraft vertical fin, the fuselage butt joint structure (10) comprising: a structural main body (20) provided with a plurality of reinforcing ribs (21); and a plurality of joints (30)...
|
