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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/2015/107367A1 |
A winglet (3) has an inner end (5) and an outer (7). The winglet (3) has a varying radius of curvature (R) which: (i) decreases along the winglet over a first distance d1; (ii) remains constant over a second distance d2; and (iii) increa...
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WO/2015/027990A1 |
The invention relates to a wing comprising a wing leading edge (1), a wing trailing edge (2), and a wing border (3) running between the wing leading edge (1) and the wing trailing edge (2) on the free end. According to the invention, a t...
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WO/2015/024601A1 |
A System for controlling boundary layer of a fluid flowing over the surface of a body (2) is described. The system comprises at least one nanosecond- dielectric/resistive barrier discharge plasma actuator (1) disposed on said surface of ...
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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/2014/188137A1 |
Reduction of the drag of a wall by an ultrasonic wave grating. A method for reducing the drag of an aircraft comprising at least one device for generating an ultrasonic interference grating on at least one shrouded wall of the aircraft, ...
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WO/2014/176431A1 |
A method of modifying a helicopter includes providing a tail boom of the helicopter. The tail boom includes a first side located on an opposite side of the tail boom from a second side of the tail boom. A main rotor blade of the helicopt...
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WO/2014/170693A1 |
A winglet (5) comprising a tubular main spar (10) with forward and aft main spar webs (12, 13) joined by upper and lower main spar caps (14, 15); a front spar (11) with a front spar web (16), an upper front spar cap (17), and a lower fro...
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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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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...
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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 ...
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WO/2014/165106A1 |
An aerodynamic or hydrodynamic wall surface has an array of fibrillar structures disposed on and extending from the wall surface, wherein each fibrillar structure comprises a stalk and a tip. The stalk has a first end and a second end, w...
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WO/2014/140590A1 |
A cavity system that tends to increase the thickness (28) of the shear layer (22), comprising: a cavity (2) and a plurality of rods (4), for example between two and six rods; the rods (4) are positioned in the proximity of a leading edge...
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WO/2014/140587A1 |
A cavity system that tends to increase the thickness (28) of the shear layer (22), comprising: a cavity (2) and a plurality of rods (4) extending away from the cavity base (3) to a height extending beyond the leading edge (14); the rods ...
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WO/2014/131055A1 |
Embodiments of the invention relate to a method and apparatus for providing high thrust density plasma, and/or high control authority plasma. In specific embodiments, such high thrust density, and/or high control authority, plasma can be...
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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 ...
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WO/2014/118508A1 |
An aircraft (1) comprising a wing (3), the end of the wing having a wing tip device (5), wherein the wing tip device comprises a moveable region (9) that is rotatable, about an axis of rotation (11) extending out of the plane of the wing...
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WO/2014/114988A1 |
A method and apparatus are disclosed that allow Conformal Vortex Generator art to improve energy efficiency and control capabilities at many points in a turbomachine or device processing aero/hydrodynamic Newtonian fluid-flows.
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WO/2014/104978A1 |
A turbine (100) comprising a nacelle (104); and at least one projection (108) provided on the nacelle, wherein the at least one projection comprises at least one edge configured to generate complementary vortices that collectively increa...
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WO/2014/084925A1 |
Apparatus and methods for forming and propagating a plurality of plasma armatures (160) along electrodes (110,120). In particular embodiments, the electrodes (110,120) are flush mounted to the surface and the plasma armatures (160) are f...
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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...
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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...
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WO/2014/068198A2 |
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WO/2014/065718A1 |
The present invention regards a structurally integrated curved structure (13, 13', 13'') comprising a curved transition region (15) being defined between a tip section (42) and a root section (11, 21), an upper and lower composite skin (...
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WO/2014/049328A1 |
An airflow modification patch (14) for reducing aeroacoustic noise generated by an aircraft assembly. The patch has a substrate (14a) and a plurality of airflow disruption elements (14b).
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WO/2014/046569A1 |
The proposed invention relates to the arts of rocket engineering, artillery and aviation and also to other arts involving the use of bodies which travel in gaseous and/or liquid environments, and makes it possible to enhance the aerodyna...
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WO/2014/039636A1 |
A multicant winglet has a first blade section having a leading and a trailing edge, a first lowermost edge and a first uppermost edge, and a first central plane defined by the edges, and a second blade section having a leading and a trai...
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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...
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WO/2014/008549A1 |
An aerolance system for an aerospace vehicle including a head for positioning adjacent a nose of the aerospace vehicle. The head includes a divergent section and a convergent section wherein a base of the convergent section is positioned...
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WO/2013/187830A1 |
A miniature vortex generator for delaying transition to turbulence in a flow of a fluid over a surface in vicinity of a leading edge, wherein the fluid has a kinematic viscosity v and the flow has a free-stream velocity U ∞, wherein th...
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WO/2013/151810A1 |
An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modif...
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WO/2013/117797A1 |
The object of the invention is a method for generating lift for an airborne flying device, which has a wing part and/or a fuselage part generating lift by means of interactive movement between the air and the device. In the method, in th...
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WO/2013/088068A1 |
The invention relates to a pylon (30) capable of securing a turbine engine (10) to a structural element (40) of an aircraft, said pylon (30) having an aerofoil defined by two opposite surfaces (36, 38) and longitudinally delimited betwee...
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WO/2013/083570A1 |
An aircraft propulsion system acting on the wingtip vortex consisting of a fixed shaft (2) placed at the end chord or wingtip of each of the wings of the aircraft and a plurality of propellers (4,5,6) mounted on each of the shafts (2). B...
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WO/2013/037379A9 |
The invention relates to aviation technology and can be used for improving the lift-drag ratio of helicopters and aeroplanes, including classically configured large airliners, and amphibious craft, aerodynamic ground-effect craft and hov...
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WO/2013/066690A1 |
A system and method for improving the lift-drag ratio of an aerodynamic surface or hydrodynamic surface such as a wing or blade-structure of a propeller, rotor or a turbine, in a fluid such as air or water, is disclosed. The aerodynamic ...
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WO/2013/064768A2 |
A turbo engine attachment pylon, configured to connect a turbo engine to a structural element of an aircraft, said pylon (30) having an aerodynamic profile defined by two opposing lateral faces and delimited longitudinally between a lead...
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WO/2013/056300A1 |
A vortex generator (9) is formed in a nozzle (9) having an inlet (10) and an outlet (11). A toroidal chamber (13) is provided in the midsection (12) of the nozzle, opening into the inner surface (15) of the nozzle through a narrow circum...
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WO/2013/040847A1 |
A through-flow air suspension platform comprises at least two through-flow blower fans (4). The through-flow blower fans (4) are arranged on the same plane. Each through-flow blower fan comprises a cylindrical blower fan shell (2). Two o...
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WO/2013/014082A2 |
Disclosed is awind turbine blade and a method for retrofitting a wind turbine blade, the wind turbine bladeextending in a longitudinal directionalong a pitch axisand having a tip end and a root endas well as a blade length, the wind turb...
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WO/2013/014015A2 |
A particular arrangement of vortex generators for an airfoil is described. The vortex generators are provided in pairs, preferably on a wind turbine blade, wherein by arranging the vortex generators according to specified characteristics...
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WO/2013/014080A2 |
A method of retrofitting vortex generators on a wind turbine blade is disclosed, the wind turbine blade being mounted on a wind turbine hub and extending in a longitudinal direction and having a tip end and a root end, the wind turbine b...
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WO/2013/007396A1 |
A wingtip device (W; W1, W2, W4, W5, W6, W7, W8) for a wing (T; 10a, 10b), which has an inner end (E1) and an outer end (E2), and in which the local dihedral of the wingtip device (W; W1, W2, W4, W5, W6, W7, W8) increases or reduces from...
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WO/2012/175928A1 |
An aircraft wing assembly comprising a wing (2) having a wing box structure including an upper wing cover (7) and a lower wing cover (8), and a wing tip device (1) attached to the outboard end of the wing, the wing tip device including a...
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WO/2012/171023A1 |
A split winglet is disclosed having a first generally upward projecting wing end, and a second generally downward projecting wing end. The second generally downward projecting wing end may be integrally formed with the first generally up...
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WO/2012/171034A1 |
The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second ho...
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WO/2012/140385A1 |
The invention relates to the field of propulsion devices (1) having an unducted upstream rotor (8) and a counter-rotating and coaxial downstream rotor (9). At least one blade (13) of the upstream rotor (8) is configured so as to generate...
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WO/2012/132420A1 |
A high-lift device (3) for an aircraft comprises: a flap main body (11) provided at the trailing edge portion of the main wing (2) of the aircraft so as to be able to be expanded and housed and extending along the wing span direction of ...
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WO/2012/122925A1 |
An aircraft wingtip device, comprising a transition part (1) and a wingtip part (2); the inner end of the transition part (1) is connected to the far end of an aircraft wing, and the outer end of the transition part is connected to the w...
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WO/2012/110845A1 |
An aircraft (10) with improved aerodynamic performances, adapted to keep the directional stability and a very good aerodynamic behaviour at medium-high incidence. Said aircraft (10) comprises a fuselage (12) to which shaped wings (18, 20...
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