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Patent Searching and Data


Matches 751 - 800 out of 2,628

Document Document Title
WO/2008/009988A3
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...  
WO/2009/007873A1
A method of manufacturing a wing structure (10) is described. A plurality of layers of preimpregnated material are laid on a first mould half (51) and on a second mould half (52) so as to form a first fresh skin (22) and a second fresh s...  
WO/2008/100286A3
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...  
WO/2009/004363A2
A composite material elongate structural member, such as a spar (102), for use in an aerospace structure, comprises a web (108) disposed between upper and lower flanges (104, 106). The web (108) may include a clockwise twist about an axi...  
WO/2009/004364A2
A composite material elongate structural member (102), such as a spar or stringer, for use in an aerospace structure, comprises a web (108) having an angled portion, for example in the form of a chamfer (107), which joins a foot (106) of...  
WO/2009/003954A1
The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover (18) arranged on the outer part of the aircraft skin (28), the ...  
WO/2009/004362A2
A multi layer composite L-shaped stringer (2) for use in an aerospace structure comprises a foot(6) and a web (8) extending from an edge of the foot. A first surface (10) on the foot is shaped to abut a structure to be stiffened. The foo...  
WO/2009/002279A2
A sequential wing construction for airplanes or wind turbines rotors. The wing comprises independent blades (5) rotably located on girders (1) of circular cross-section, which create, along with sideward positioned aerodynamic traverses ...  
WO/2009/000911A2
The invention relates to an integrated structure of a composite material multispar torsion box (1) for aircraft, comprising a lower skin (12), an upper skin (11), several spars (9) defining cells (14), the first cell (19) being the close...  
WO/2008/155720A2
H-beam carbon-resin spars for the horizontal stabilizers of aircraft are formed by using forming devices (60) each of which comprises an elongate core (61) of rectangular cross section fixed securely to a flat plate (62) which extends ar...  
WO/2008/156532A2
Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture t...  
WO/2008/150714A1
A closed hat stringer (102) for stiffening a composite structure includes opposing cavity walls (104) situated between a first flange (106) and a second flange (108), the cavity walls, first flange and second flange defining an elongated...  
WO/2008/150712A1
Techniques for manufacturing structures that include composite hat stringers (102) are disclosed. In one embodiment, a method of forming a composite structure includes placing a generally cured composite hat stringer (102) on a tool, the...  
WO/2007/140147A3
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...  
WO/2008/125868A3
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...  
WO/2008/054499A3
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...  
WO/2008/139214A1
A reinforced panel (1) comprising: a compositeskin (2); a plurality of stringers (3, 4) bonded to the skin; and one or more strain actuators (5), each positioned between an adjacent pair of stringers. A load is applied to the panel in th...  
WO/2007/117275A3
An airfoil family for a helicopter rotor blade, designated SC362XX. SC362XX essentially removes the large lower surface suction peak associated with 'drag creep' at moderate lift coefficients while reducing the peak Mach number and shock...  
WO/2008/138331A1
The present invention relates to a covering fabric for covering aircraft. The fabric itself is coated with one or more layers of a crosslinked anionic aliphatic polyester-polyurethane dispersion and/or is woven from coated fibres or fila...  
WO/2008/132050A1
A fibre metal laminate panel with a number of layers (101, 102), arranged in the form of a laminate, of a planar metal material (101 ) and a fibre material (102), the planar metal material (101) being joined at splices (105) by a metal-m...  
WO/2008/132251A1
The invention relates to a structure comprising a multispar torsion box made from composite material and intended for an aircraft, consisting of: a lower coating (12); an upper coating (11); multiple spars (9), each spar comprising a fla...  
WO/2008/132498A1
A composite structure which may form, for example, the skin of an aircraft wing or fuselage comprises a panel (20) and a series of stringers (21-23) bonded to the surface of the panel (20). Each stringer comprises a web (24) extending at...  
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...  
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...  
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...  
WO/2008/099097A3
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...  
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...  
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 ...  
WO2007071384A8
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...  
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 ...  
WO/2008/084260A3
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...  
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...  
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 ...  
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...  
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...  
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...  
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...  
WO/2008/054876A3
The present invention discloses a method for producing a wing structure comprising producing a machined metallic bottom skin by pre- machinmg, preforming or combinations thereof, finishing the skin which serves as a mold, placing a plura...  
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...  
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...  
WO/2008/067460A3
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...  
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...  
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...  
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 ...  
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...  
WO/2008/007135A3
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...  
WO/2007/117260A3
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...  
WO/2007/001715A3
The method of landing a flying wing type aircraft in a crosswind includes the steps of disengaging the nose landing wheel upon impact with the runway so that it is free to castor; and thereafter, engaging the nose wheel after a specific ...  
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...  
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...  

Matches 751 - 800 out of 2,628