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WO/2015/190124A1 |
Provided is a morphing wing capable of greatly deforming the wing as a whole through a lightweight and simple mechanism without accompanying increases in structural complexity and size, thereby achieving a high wing area increasing effec...
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WO/2015/189242A1 |
The invention relates to a method, and wings (100) for an aircraft obtained by said method, for assembling a casing structure (100) including basic parts (230, 240, 321) that are assembled according to a sub-structure of stiffeners (230,...
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WO/2015/172869A1 |
The invention relates to a high-load gearing for a high-lift support (21) of an aircraft, wherein the high-load gearing comprises two outer segments (11) that cannot be rotated in relation to each other and an inner segment (12) that can...
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WO/2015/172892A1 |
The invention relates to a method for mounting an aircraft structure to a mounting frame, wherein the mounting frame is not part of an aircraft, and wherein in one step, structural parts and/or auxiliary structures of the aircraft struct...
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WO/2015/170090A1 |
An aircraft fuel tank(16), comprising: a plurality of tank walls enclosing a liquid storage space (14), the plurality of tank walls including a first tank wall (10) (e.g. an external skin of the aircraft) and a second tank (8) wall (e.g....
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WO/2015/162399A1 |
An aircraft comprises a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configu...
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WO/2015/163855A1 |
A propeller blade is provided including a leading edge and a trailing edge. The trailing edge is arranged opposite the leading edge to form an airfoil there between. At least one of the leading edge and the trailing edge include at least...
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WO/2015/160394A2 |
An asymmetric aircraft (1) and an aircraft (1) that can operate from small ships (8) and be stored in high density with three aircraft or more in one helicopter hangar (107) without needing a landing gear or wing fold. These aircraft sli...
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WO/2015/150835A1 |
A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) comprising an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ...
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WO/2015/150817A1 |
An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip d...
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WO/2015/150816A1 |
A passenger aircraft comprising a wing (1) and a wing tip device (3). The wing tip device (3) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the grou...
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WO/2015/150818A1 |
An aircraft (1) comprising a wing (5), the wing comprising an inner region (5a) and an outer region (5b), the inner and outer regions (5a, 5b) being connected by a hinge (11) defining a hinge line about which the outer region (5b) is fol...
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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...
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WO/2015/127902A1 |
A flying car comprises a body (3), a cockpit (26), a passenger cabin (24), a baggage compartment (22), an equipment compartment (18), a vehicle body tail (16), wheels (21, 27), airfoils (5) and a propeller (11). As the combined longitudi...
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WO/2015/124556A1 |
The invention relates to an aircraft comprising a fuselage (1), a plurality of propeller units (3) that can pivot in relation to the fuselage (1), and wings (5) that can pivot at least partially in relation to the fuselage (1) and indepe...
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WO/2015/120833A1 |
The invention relates to flying robots which can cover large distances between arrangements of smooth or curved surfaces without requiring manual redeployment. This reduces the need for personnel and allows fully-automated maintenance of...
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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...
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WO/2015/119023A1 |
A composite material structure (10) is provided with first surface plates (1, 2), and a corrugated core (3) joined to the first surface plates (1, 2). The corrugated core (3) has at least one opening (4).
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WO/2015/119933A1 |
A gust alleviating aircraft wing includes a gust alleviating wing portion on the wing. The wing portion can have a leading edge, a trailing edge, and a downwardly sloping upper surface therebetween. At least one air passageway can extend...
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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...
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WO/2015/113148A1 |
A method for monitoring air pressure in a kite when kite boarding is described. The method involves a first step of connecting an air pressure sensor to one or more bladders of the kite. The method involves a second step of positioning a...
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WO/2015/114625A1 |
Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated ...
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WO/2015/094003A1 |
The invention relates to air transport and can be used in aircraft of various designs. The aircraft wing comprises a lifting surface and a turbojet engine (1). The lifting surface is the combination of a conventional aerodynamic wing (3)...
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WO/2014/184814A9 |
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...
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WO/2015/084435A1 |
An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Compo...
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WO/2015/073073A1 |
A stringer (52) having a runout (66) with a raised area (70) configured to reduces stress while improving drainage across the runout when utilized in a close structural component of a vehicle such as an aileron of an aircraft. In one or ...
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WO/2015/059231A1 |
Wind turbine blades comprising one or more deformable trailing edge sections, each deformable trailing edge section comprising a first and a second actuator, wherein the second actuator is arranged substantially downstream from the first...
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WO/2015/059232A1 |
Wind turbine blades comprising one or more deformable trailing edge sections having a multistable sheet comprising a plurality of bistable elements, each bistable element having two stable positions, wherein the multistable sheet is atta...
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WO/2015/057286A1 |
A manual wing-fold mechanism provides a means by which to reconfigure the wing of an aircraft between a flight configuration and one that can be easily stowed and transported. The folding mechanism includes an extension tube that enables...
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WO/2015/047480A2 |
According to various embodiments, a carbon fiber structure is presented. The carbon fiber structure may address loads presented to an engine component in various directions. For instance, non-planar surfaces of a composite comprising a s...
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WO/2015/037660A1 |
This dam for a fuel tank closes a gap that is formed between a first structural component and a second structural component. The dam for the fuel tank is equipped with: a first section that is disposed on the first structural component s...
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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...
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WO/2015/022711A1 |
The proposed convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft comprises : - a variable incidence front wing of variable span located below the fuselage and m...
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WO/2015/014370A1 |
A blade for a wind turbine defines an airfoil with a leading edge section and a trailing edge section, notably a flat-back trailing edge. A rounded connecting section interconnects a pressure side section of the airfoil and the trailing ...
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WO/2015/015152A1 |
An aircraft structure extending from a root to a tip, the root being adapted to be joined to an aircraft fuselage. The structure has a cover with an aerodynamic outer surface and an inner surface, a plurality of stiffeners, and a plurali...
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WO/2015/007258A1 |
The present invention relates to changes to wing profiles. In order to provide an aerodynamic structure that can be adjusted and changed in many ways with respect to the wing profile, it is provided that an aerodynamic structure (10) for...
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WO/2015/005125A1 |
This method for producing a reinforcing structure comprises: a step for preparing a stringer that has a fiber exposed surface; a step for arranging a conductive protective material so as to cover at least a part of the fiber exposed surf...
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WO/2015/006488A1 |
A composite component is disclosed. The composite component may comprise a metal plating deposited on a surface of the composite component, and a metallic feature adhesively bonded to the metal plating. The composite component may furthe...
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WO/2015/005126A1 |
This method for producing a reinforcing structure comprises: a step for preparing a stringer that has a fiber exposed surface; a step for arranging an insulating protective material so as to cover at least a part of the fiber exposed sur...
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WO/2014/186023A9 |
The lift and drag performance of all vehicles is strongly influenced by viscous effects, and in turn, laminar separation bubbles. This application employs an effective fluid boundary layer control strategy that reduces parasitic drag, al...
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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...
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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...
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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...
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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...
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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 ...
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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 ...
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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...
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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...
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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...
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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...
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