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WO/2008/125868A2 |
A wing structure for an aircraft comprises an inboard spar (30) pivotally mounted at an inboard end with respect to an aircraft fuselage, an outboard spar (32) pivotally coupled at one end to an outboard end of the inboard spar (30) a pl...
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WO/2008/124351A2 |
Methods and structures for a composite truss structure (102) are provided. The structure includes an upper chord member (202), a lower chord member (204), and a plurality of web members (206) extending therebetween. Each of the upper cho...
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WO/2008/124352A1 |
Methods and structures for a composite truss structure (102) are provided. The structure includes a web (206) formed of a plurality of sheets of composite material, each sheet including a first face and an opposing second face and each f...
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WO/2008/119664A2 |
The present invention relates to a leading edge (1) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement (2) firmly adhered to the mentioned inner face of the leading...
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WO/2008/121005A1 |
An aircraft with (I) a wing assembly primary each of three moulding, one providing a spar, a second most of the exterior including the leading edge, and a third at least most of the rear under surface and (II) a compatible fuselage. The ...
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WO/2008/112686A1 |
The present invention includes an embodiment defined as a flying vehicle having a pair of wings and a transition assembly partially housed within each of the pair of wings. The transition assembly has ends rotatable with respect to each ...
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WO/2008/105806A2 |
A wing panel structure (100) for an aerospace vehicle or the like may include an outer layer (102) of material having a predetermined thickness. A core structure (104) may be placed on at least a portion of the outer layer (102) of mater...
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WO/2008/103735A2 |
Modification or retrofit components for an aircraft having wing mounted engines. A replacement wing torque box has thickened spar webs machined with raised bosses around holes in the web to lower stress concentration. The spar caps have ...
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WO/2008/099097A2 |
The invention relates to an aircraft wing (1) including two members (2, 3) removably connected end to end by a coupling means (4) including: a male coupling part (5) with spaced opposed upper (7) and lower (8) faces, a first face being p...
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WO/2008/100299A2 |
The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement (1) member of the mounting device. In another aspect of the invention, a mounting device i...
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WO/2008/100286A2 |
An aircraft can include a wing (42) with a leading edge (64) and a trailing edge (66). The wing has a main body (74) and movable control surfaces (80, 82) coupled to the main body. The wing (42) generates lifting forces when the aircraft...
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WO/2008/097325A2 |
An airfoil for use with an aircraft having an engine (3) positioned such that exhaust from the engine flows under an underside of the airfoil. The airfoil includes an upper surface and a movable control element (14, 16). The upper surfac...
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WO/2008/087861A1 |
A leading edge structure of aircraft comprises a body part (11) constituting the leading edge part (1) of the aircraft and a surface part (12) which is formed on the outer surface of the body part (11) and on which a large number of pins...
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WO/2008/084260A2 |
A leading edge structure is disclosed for an aircraft wing in which a droop nose is articulated by a double hinge, in particular said leading edge structure comprising: a fixed leading edge structure (201); a movable leading edge structu...
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WO/2008/070944A2 |
A flight control system commands drag devices such as flight spoilers according to pilot or autopilot longitudinal command. Furthermore, the flight control system monitors a set of flight parameters (18 - 21) to determine whether the air...
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WO/2008/068472A1 |
An aerofoil member (10) comprising a 'smart core' (14) and a flexible skin (12). The core comprises sheet material elements (16) forming adjoining cells (18). The length of the elements can be changed, for example using the piezo-electri...
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WO/2008/068523A1 |
A composite structure comprising: a panel formed from two or more plies of composite material, the panel having a surface formed with a step where the thickness of the panel changes. Two or more stiffeners are attached to the surface of ...
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WO/2008/067460A2 |
A composite shear tie (500) for connecting a rib (504) in a wing of an aircraft to a skin panel (514). The shear tie includes a web (520) section having a first edge, a second edge, and a third edge. The web section is formed from a comp...
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WO/2008/054499A2 |
Embodiments of integral composite panels and joints for composite structures are described In one implementation, an integrated panel (104) spanning substantially the entire wingspan of an aircraft, includes at least a center portion (11...
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WO2007145718A9 |
An edge morphing arrangement for an airfoil having upper and lower control surfaces is provided with a rib element arranged to overlie the edge of the airfoil. The rib element has first and second rib portions arranged to communicate wit...
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WO/2008/048131A1 |
The airplane is provided with right (6) and left (7) wing tips mounted on the right (2) and left (3) half-wings thereof. Said wing tips (6, 7) are mountable on the end parts of a wing, in particular on the end rib (14) of the wing and co...
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WO/2008/037847A1 |
The invention relates to a curve element and to a wing, a control surface and a stabilizer for an aircraft. The curved element (7) is of a composite material and comprises surfaces (14, 21) provided with a plurality of profile reinforcem...
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WO2008001336B1 |
Adjusting device for adjusting a high-lift flap (2; 102) and airfoil wing provided with the same, comprising at lest one flap drive (20) for operating the flap (2; 102), and comprising several drive stations (3, 4, 5) which movably conne...
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WO/2008/029049A1 |
The invention relates to a panel assembly (100) in which two panels (101, 102) are connected together, in which assembly a surface of each of the two panels comprises a step (105, 106), in such a way as to form an upper level (112, 114) ...
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WO/2008/029048A1 |
The invention relates to a panel assembly in which the joint between two adjacent panels is closed by a seal (20), said assembly being characterized in that the seal comprises a central part (21) housed in a gap (19) formed between the t...
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WO/2008/024178A1 |
An improved powered hinge (20) with an automatic locking feature proximate the ends of permissible relative angular displacement of its two hinge sections broadly includes: a stationary member (23) having a pivotal axis (x-x), and having...
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WO/2008/022428A1 |
A transferable modified leading edge for a wing is detachably mountable to a parent wing. The parent wing may use a NACA 23000-series airfoil. A modified wing tip may be used in conjunction with the modified leading edge. The modified le...
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WO/2008/017134A2 |
It is described a non-movable aerodynamic device of fence type (F) installed on the leading edge of a wing (W) of an aircraft, close to a slat (S), however said fence is not fastened to said slat, so that when the slat (S) is extended or...
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WO/2008/012570A2 |
The present invention relates to a stringer for an aircraft wing and a method of forming such a stringer in which the stringer is formed from a single piece of material and then machined to optimise the dimensions and weight of the strin...
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WO/2008/012569A2 |
An aircraft wing box comprises a pair of half ribs (18, 20) joined to form a rib extending from an upper wing skin (12) to a lower wing skin (10). Each half rib (18) comprises a base (19) and a plurality of projections (4) that extend aw...
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WO/2008/009988A2 |
A method of manufacture of a structural member comprising, providing a number of internal elements (16,18,20), each having an aperture formed therein, sequentially assembling the internal elements onto a longitudinal element (14) such th...
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WO/2008/009921A1 |
A heated leading edge component for an aircraft and a method of manufacture thereof. The leading edge component includes an outer skin, a supporting rib for the outer skin, and a cavity located substantially in-between the outer skin and...
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WO/2008/006831A1 |
A trimmable horizontal stabilizer, which is provided adjacent to the fuselage (10) of an aircraft and has a predetermined aerodynamic profile, and adjacent to which a movable elevator (21) is arranged. The horizontal stabilizer (20) has ...
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WO/2008/007135A2 |
A wing cover panel assembly, wing cover and method of forming thereof are disclosed in which an attachment surface (205) of the wing cover panel is provided with a locating channel (302) into which a wing structural element (105) such as...
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WO/2007/144563A1 |
The present invention relates to a stringer (105) for an aircraft wing and a method of forming such a stringer in which the stringer (105) is formed form a single piece of material and has differential strength along its length.
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WO/2007/140147A2 |
An actuator and flap arrangement includes a flap, movable relative to a support structure, and two actuators. Each actuator has a portion fixed relative to the support structure, a portion movable relative to the fixed portion and connec...
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WO/2007/128997A1 |
A compression apparatus for compressing a curved region of a laminated element (2) having a first surface region following a first curved path and a second surface region opposed to the first surface region following a second curved path...
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WO/2007/126405A2 |
An airfoil for a micro air vehicle that includes components enabling the airfoil to adjust the angle of attack (AOA) of the airfoil in response to wind gusts, thereby enabling the airfoil to provide smooth flight. The airfoil may include...
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WO/2007/124014A2 |
A system for determining the position and/or velocity of an autonomous aircraft in a low-cost, low- weight manner independent of external technological dependencies such as satellites or beacons is claimed. The solution comprises a combi...
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WO/2007/117260A2 |
A blended wing body aircraft may include a blended wing configured to house a person, payload and/or cargo within the wing, a surface structure, and an actuator. The actuator may be configured to controllably cause the planar structure t...
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WO/2007/110586A1 |
A method of manufacturing an aircraft component such as a wing rib. The method comprises: providing a body with two or more connectors (19, 20) arranged in a line on the body, each connector having an arm (35, 41) extending from the body...
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WO/2007/109826A1 |
An inflatable aircraft buoyancy compartment or componentry support member for installation in conventional aircraft to reside in spaces or cavities between internal structural members of the aircraft fuselage, wings or tail section, the ...
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WO/2007/110518A1 |
The present invention relates to an aerodynamic or hydrodynamic profile (1) which can be deformed in a continuous and controlled manner, essentially consisting of a shell mounted on an infrastructure. The profile is characterized in that...
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WO2007071384B1 |
A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) wit...
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WO/2007/099297A1 |
An aircraft wing subassembly comprises an outer wing section (11, 12) for forming an exposed wing area, and an inner wing section (18, 19) for forming a portion of a wing box and formed as an extension to the outer wing section. The inne...
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WO/2007/099285A1 |
An aircraft wing (1) comprises a leading-edge slat (5), the slat including a main body portion (7) and a slat extension (9) arranged at a spanwise end of the main body portion (7). The cross-sectional area of the slat extension (9) is le...
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WO/2007/093636A1 |
The invention relates to a method for autoclave-free adhesive bonding of components (2-6) in order to form in particular, large-sized structural components (1) for aircraft. Since the curing of the least one adhesive film (16) in order t...
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WO2007071398B1 |
A device (1) for protecting an aircraft structure (5) comprises a skin (2) made of GLARE, which skin if a force acts on it deforms to absorb the force so that damage to the aircraft structure is prevented.
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WO/2007/091990A2 |
Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, an...
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WO/2007/082823A1 |
A component (1) for arrangement in the duct of a turbine engine is provided with a coating (5), which has a surface structure with scales (9) which overlap each other in the direction of flow (S).
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