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Patent Searching and Data


Matches 401 - 450 out of 2,628

Document Document Title
WO/2014/207732A1
Described herein is a multi-rotor aircraft (10; 200) including: - a load-bearing structure (10A; 200A); and - a plurality of propulsion assemblies (M1, M2, M3, M4, M5, M6; M1', M2', M3', M4') each including a rotor (R1, R2, R3, R4, R5, R...  
WO/2014/204243A1
The present invention relates to a wing for an unmanned aerial vehicle which is manipulated by a remote control. The wing for an unmanned aerial vehicle according to the present invention may comprise: a foaming resin support; an aluminu...  
WO/2014/200393A1
The present invention relates to a method and apparatus for manufacture of stringer reinforced composite skins. The method includes the consecutive steps of: providing a forming tool comprising elongated support members spaced apart by m...  
WO/2014/199371A1
Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary...  
WO/2014/195241A1
The invention relates to a winged structure and movable machines, particularly flying machines, comprising such a winged structure. The winged structure (1) comprises at least one front wing (5) and one rear wing (6) which are connected ...  
WO/2014/184814A1
Two panels (1 1, 12) of composite material are placed on a first plate (17) and a second panel (18). One or more intermediate spars (14a, 14b) of composite material are suspended above the first panel (12), said spars being arranged betw...  
WO/2014/176622A1
An aerospace plane (1) having an elongate body (2) supports a pair of wings (3). The wings are adapted to extend away from said body in opposing directions. A landing gear assembly is operatively associated with said body to be moveable ...  
WO/2014/175798A1
The invention regards a torsion-box type airfoil composite structure comprising a skin component (6, 206) and at least a first and a second stiffening element (8, 8', 208', 8'', 208'') arranged adjacent to each other longitudinally along...  
WO/2014/175799A1
The present invention regards a method for manufacture of a torsion-box type skin composite structure (1) mountable to a main sub-structure (5), the torsion-box type skin composite structure (1) comprises a skin component (7), a stiffene...  
WO/2014/175795A1
The present invention regards a method for manufacture of a torsion-box type skin composite structure (3) mountable to a main sub-structure (6), the torsion-box type skin composite structure (3) comprises a skin component (9), a stiffene...  
WO/2014/170692A1
A braided composite spar (10) or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar (10) or preform extends lengthwise from a root(10a) to a tip (10b), and the spar or prefor...  
WO/2014/170691A1
A braided composite spar (10) or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar (10) or preform has a centre line which extends lengthwise from a root (10a) to a tip (10b...  
WO/2014/170690A1
A braided composite spar or preform for a braided composite spar with a plurality of tubular plies of braided fibres. Each ply has a first set of fibres which wind in a clockwise direction in a first series of turns with a pitch between ...  
WO/2014/068572A3
A method for producing structures from composite materials, the method including forming a three-dimensional preform including at least one skin and a plurality of protrusions extending from the at least one skin, folding the three- dime...  
WO/2014/156369A1
The purpose of the present invention is to provide a fuel tank, main wings, an aircraft fuselage, an aircraft, and a moving body, which enable working hours and costs involved in a manufacturing process to be reduced, and weight increase...  
WO/2014/155107A1
Modern aircraft wings generally have a lower surface the rear part of which is concave over at least some of its length, for additional lift. Sometimes it is desirable to reduce the wing lift, for instance during turbulence. To this end ...  
WO/2014/156274A1
The purpose of the present invention is to provide a fuel tank, main wings, an aircraft fuselage, an aircraft, and a moving body, which enable working hours and costs involved in quality management to be reduced, and weight increases to ...  
WO/2014/134072A1
An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for sup...  
WO/2014/129761A1
Disclosed is an easy landing drone, including: a propeller for changing direction; a propeller tower for supporting the propeller; a body connected to the propeller tower; a main wing with both sides arranged symmetrically with reference...  
WO/2014/126855A1
A method of controlling a magnitude of a sonic boom caused by off-design condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds...  
WO/2014/120366A1
A method and apparatus comprising a sealing member (300), an integral structure (505) associated with the sealing member (300), and an engagement section (503) extending from the sealing member (300). The sealing member is configured to ...  
WO/2014/113888A1
A wind turbine blade assembly for a wind turbine having a root portion proximal to a hub of said wind turbine and a tip portion distal to said hub, comprising a primary airfoil having a primary leading edge and a secondary airfoil having...  
WO/2014/102082A1
The invention concerns a device for absorbing kinetic energy for an aircraft structural element that may undergo a dynamic impact, this device comprising: - an outer enclosure (21) made from a braided composite material capable of preser...  
WO/2014/074201A3
An aerodynamic lift structure (2) comprises unbalanced composite skin that couples twist and bending.  
WO/2014/094549A1
Disclosed is an aeroplane airfoil leading edge structure to satisfy an anti-bird impact function. The structure comprises three parts: a metal panel (1), a honeycomb sandwich layer (2) and a composite material lining (3), wherein the thr...  
WO/2014/097292A1
Wing deployment mechanism for deploying a pair of wings from an airborne body, wherein their deployment in motion, each one around an axis, defines the wings' deployment plane relative to the airborne body, and wherein the mechanism is c...  
WO/2014/085835A2
The present disclosure relates to a wing. More specifically, aspects of the invention relate to a variable shaped wing movable incrementally between a neutral configuration and a deformed configuration, wherein the wing takes a reflexed ...  
WO/2014/081356A1
The invention regards an airframe leading edge part designed to be replaceable fixed to a structural portion (20, 21, 33) which during use moves through the air, the airframe leading edge part (19, 19') comprises a first (39) and a secon...  
WO/2014/081380A1
The invention regards an airfoil article including a composite skin (5) having a first surface (S1) and a second surface (S2) opposite to said first surface,forming a leading edge (4). The leading edge (4) is during use subjected to a ai...  
WO/2014/081355A1
The invention regards an airfoil article including a composite skin (5) forming a leading edge (4), the composite skin (5) being during use subjected to an airflow (a) meeting the leading edge (4) at stagnation points (SP), where the air...  
WO/2014/076403A1
The invention concerns an aircraft comprising a fuselage (30) extending along a main longitudinal axis (AA), two wings (10, 20) positioned on either side of the fuselage, two propulsion units (11, 21), each fixed respectively to one wing...  
WO/2014/072593A2
The invention relates to a method for manufacturing a laminated product having a variable thickness and consisting of a heat-treated aluminum alloy, in which a variation in thickness of at least 10% lengthwise, between the thickest porti...  
WO/2014/074201A2
An aerodynamic lift structure comprises unbalanced composite skin that couples twist and bending.  
WO/2014/074182A1
A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region (220) adjacent to the fuselage and distant from the wi...  
WO/2014/070339A1
An aircraft wing tip device (107) includes a unitized, monolithic leading edge torque box that is formed of polymer matrix fiber- reinforced material. The leading edge torque box includes a skin (160) that defines a continuous, uninterru...  
WO/2014/068572A2
A method for producing structures from composite materials, the method including forming a three-dimensional preform including at least one skin and a plurality of protrusions extending from the at least one skin, folding the three- dime...  
WO/2014/070051A1
The present invention regards an aerial article comprising a composite skin (5), a leading edge (1) facing the airflow (a) during the use of the aerial article (3), an erosion resistant coating (7) comprising a metallic material, and an ...  
WO/2014/065719A1
The present invention relates to a torsion-box type airfoil structure. The structure (3) being formed by joined structural composite parts (5, 7, 9, 11) made of fiber reinforced plies (19) stacked onto each other. At least a first (11) a...  
WO/2013/060916A9
Optimized stringer run-out zones in aircraft components. These are arranged in a panel (11) of a composite material formed by a skin (13) and at least one reinforcing stringer (15) formed by a web (17) and a flange (19) connected to said...  
WO/2014/057960A1
The purpose of the present invention is to provide: a structural material for structures which is capable of attaining reductions in working time and cost in production steps and of preventing an increase in weight; a fuel tank; a main w...  
WO/2014/053816A1
The present invention provides an aircraft structure comprising a first sub-structure (110), having a first box cross-section, a second sub-structure (120), having a second box cross-section, and a joint joining a first end region of the...  
WO/2014/048731A1
The invention relates to a device for cooling a component (2) in a vehicle by means of a cooling air flow (4), wherein the device has at least one air inlet (11) and at least one air outlet (12), which are arranged such that the cooling ...  
WO/2014/048559A1
The invention relates to the production of a metal flow body, particularly a wing, which is produced from a metal sheet and a support structure. According to the method, a drop-like hollow cylinder is created by shaping a flat metal shee...  
WO/2014/041198A1
Embodiments of the present invention relate to an adaptable wing (112, 114) having a variable geometry for influencing aerodynamic performance, the wing (112, 114) comprising a jointed leading edge having a main pivot (116), and a wrist ...  
WO/2014/041221A1
The invention relates to a deformable aircraft wing (1) including a mobile upper surface, comprising a double skin (7) on the upper surface of the wing (1), one of the aforementioned skins (7) corresponding to the leading edge (2), while...  
WO/2014/033440A1
Method for bonding a T-section stiffener (100) to a surface (106) comprising the steps of: arranging an isolation layer (120) between two adjacent upright portions (102,104) of a T-section stiffener (100), arranging the stiffener (100) o...  
WO/2014/006422A3
An adjustable structure (1) comprising a first structural layer (10) defined by a first array of extendable and/or retractable rods or beams (11, 11a, 11b) pivotally connected to each other at their ends and a second structural layer (20...  
WO/2012/131335A9
A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs dispose...  
WO/2014/031043A1
The present invention relates to a reinforced structure (1) and a method for manufacturing a reinforced structure (1) of composite material. The reinforced structure (1) comprises a stiffening element (2) which is attached to the concave...  
WO/2014/030465A1
Heretofore it has been difficult with conventional methods to manufacture a rotary vane with a large diameter for use in a shroud-equipped rotary vane mechanism, a linear blower, or a linear wind-powered generator, and those which can be...  

Matches 401 - 450 out of 2,628