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WO/2003/051713A1 |
A flap (12) for an aircraft having a movable plate (21). The movable plate (21) is disposed at a position near to the rear edge of the flap (12). A support shaft (22) rotatably supports the movable plate. The movable plate is connected t...
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WO/2003/039949A2 |
Wing able to enhance lift power by inner air flow, is solution of wing that results in increased and changeable lift power, with lesser increase of aerodynamic resistance than with conventional wings. In the invention basic embodiment, t...
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WO/2003/035469A1 |
The invention relates to a carrying or guiding device (1) for aircraft components, especially for a landing flap which is arranged on an aircraft wing. The inventive device comprises a carrier (2) having an essentially U-shaped profile a...
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WO/2003/026961A1 |
A notched blade seal (10, 100) for covering a gap between a wing and a wing flap of a high performance aircraft includes a bottom seal strip (12, 112) of a flexible, resilient material having a plurality of spaced-apart notches (14, 114)...
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WO/2003/016133A1 |
A system for controlling an aircraft includes an airframe, a first airfoil (40), and a second airfoil (50). At least a portion of the first airfoil (40) and the second airfoil (50) are controllably deflectable so that, during a roll mane...
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WO/2003/008266A1 |
The invention relates to a lift-flap mechanism for the operation of a lift-flap (2) on a flap support (3) of a lifting wing (1), by means of a drive system (6), whereby the lift-flap mechanism (4) comprises a main connector mechanism (7)...
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WO2001076941A9 |
Disclosed is an aircraft (101), configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The ai...
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WO/2002/102660A1 |
An aircraft (1), e.g. an aeroplane or missile, has fins (6, 17) attached to tube (3) encircling the aircraft fuselage. When fins (6, 17) are pivoted, a predetermined difference in size or pitch of fin (6) relative to fin (17) will cause ...
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WO/2002/094655A2 |
The current invention relates primarily to the control of rotary wing and fixed wing aircraft where a small electric actuator (7, 104) changes the pitch on a small aerodynamic surface (5, 66) and the resulting airloads on said small aero...
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WO2002059148A9 |
Described is a method for identification, isolation and production of hyperimmune serum-reactive antigens from a specific pathogen, a tumor, an allergen or a tissue or host prone to autoimmunity, said antigens being suited for use in a v...
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WO/2002/062660A1 |
An aircraft flag extension mechanism including a flap positioning mechanism (30) comprising a carriage (50) and track system (40) suitable for use with variable radius or multiple curvature tracks.
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WO/2002/038442A2 |
Micro-electro-mechanical (MEM) translational tabs (26) are introduced for enhancing and controlling aerodynamic loading of lifting surfaces. These microtabs (26) are mounted at or near the trailing edge (24) of lifting surfaces, deploy a...
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WO/2002/006909A2 |
A flight control module with integrated acutator spoiler control electronics, where the flight control functions have been integrated into the integrated modular avionics through the use of a flight control module ('FCM') (302) , the FCM...
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WO/2001/074660A1 |
A vane-airfoil combination for shifting forces associated with an airfoil. The vane-airfoil combination includes an airfoil (53) moving through a fluid, such as air. A plurality of vanes (55) is positioned in front of the airfoil to dive...
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WO/2001/046008A1 |
The present invention relates to an arrangement in a rudder (1) intended for an aircraft or watercraft. The rudder is arranged at the trailing edge (3a) of a wing-shaped structure (3), extending largely in one plane (2), and capable of t...
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WO/2001/026965A1 |
The invention relates to a hinge for movable control surfaces in an aircraft. The hinge comprises two hinge lugs placed at a distance from one another. The hinge lugs include connecting lugs with an elongated connecting piece therebetwee...
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WO/2001/019673A1 |
The invention concerns a convertible aircraft (1) with tilting rotors (9), flying in aeroplane mode as well as in helicopter mode, with high fixed wings (5), raised with respect to the fuselage (2) and in positive dihedral supporting the...
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WO/2001/008777A1 |
An electric remote-control aircraft comprises a tail which is formed V-shape. An automatic compensation mechanism of a steering aerodynamic lift is arranged on each of the left and right sides of the tail, respectively. The automatic com...
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WO/2001/008971A1 |
The present invention provides an actuator system (10, 100, 200) for use in an aircraft control or operating system, comprising control means (12) operable in response to an input for generating a control signal, and an electrical actuat...
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WO/2001/005654A2 |
A trailing edge control surface (12) is pivotal about a pivot axis (16) fixed relative to the vehicle and is deflected to create control forces, and a tab (24) is pivotally mounted to an aft end of the control surface. An aft end of a li...
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WO/2000/007875A1 |
The fin (12) has an end plate (16) mounted at its upper end and the end plate covers the upper end of the rudder, so that the rudder (14) seals against the end plate at all rudder deflections. The fin and rudder lift curved slopes are in...
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WO/2000/007876A1 |
The slat (16) is mounted to extend and retract relative to the aerofoil (10) and a data line (28) supported on a mounting cable (20) extends between the slat (16) and the aerofoil (10). The data line (28) is arranged to wrap around the l...
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WO/1999/061803A1 |
The present invention relates to a pneumatic control for pneumatic ailerons known from WO 98/03398 and/or wing flaps of a fixed wing airplane, which can be manually actuated by means of a lever. The adjustment lever is connected to a thr...
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WO/1999/052768A2 |
In accordance with the present invention, there is provided an aerodynamic control device (10) for integrated use with an aircraft (12) having an inboard lifting member (18). The inboard lifting member (18) having a leading edge (20), a ...
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WO/1999/030967A1 |
An aircraft aileron system (10, 10) is comprised of two panels (12, 14, 28, 30, 62, 70) located at the rear portion of the wing (W24, 54), in a spanwise direction and aligned with the wing's trailing edge. The panels are independently hi...
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WO/1999/025613A1 |
An airfoil (20) is provided with a seamless control surface (30) which comprises upper and lower skins (32 and 38) fixed to a spanwise extending spar (24) and extending chordwise to a trailing edge (66) and having an outer surface which ...
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WO/1999/024317A1 |
The invention concerns a method for controlling an aeroplane control surfaces to counter ground lateral drift during landing or an interrupted take-off, which consists in producing an unbalanced exit of the aileron control surfaces.
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WO/1999/015403A2 |
A flight control system (20) comprises trailing edge airfoil members (32) pivotally mounted at the trailing edge (30) of each wing (26) of an aircraft (22) and selectively movable on a laterally extending axis between raised and lowered ...
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WO/1999/000297A1 |
An active control method and apparatus for encouraging the early destruction of trailing vortices formed by a lifting body having at least two control surfaces (68, 70) on each side and creating multiple vortex pairs is provided. The met...
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WO/1998/047761A1 |
An aircraft wing, wing assembly and method of reducing drag are provided. The wing assembly includes a main wing portion (10) and a leading edge high lift portion (12). The high lift portion is movable between a retracted position in whi...
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WO/1998/023483A1 |
A mechanism for the streamwise deployment of an aircraft trailing or leading edge flap (4). The mechanism connects the spar (23) and flap (4). There are a pair of swivel links (50, 55) which pivotally connect the spar (23) to the flap (4...
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WO/1998/022338A1 |
A system for stabilizing (10) an aircraft includes sensors (40) positioned and disposed at predetermined locations on the aircraft and structured for sensing external forces acting on the aircraft at the sensor locations as a result of r...
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WO/1998/017529A1 |
A substantially unswept wing (14, 26) that achieves the same cruise speed of Mach=0.78 as jet airplanes with higher sweep (1) with the same lift but lower velocities over the top (83) of the wing. With very low sweep and this type of cru...
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WO/1997/049607A1 |
A leading edge flap system for an airplane includes a flap (20) which is rotated about a single hinge point (80) between (i) a retracted position, (ii) an intermediate extended position for high speed maneuvering, and (iii) a fully exten...
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WO/1997/038900A1 |
A variable camber wing mechanism comprises a main wing section (1) having a leading edge (3) and a slat member (2) that is connected to the main wing section by at least two swing arm members (4). Each swing arm member (4) is pivotally c...
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WO/1997/032779A1 |
A two-way slotted rudder in particular for aircraft is described. It comprises a carrier element (1) which is rigidly attached to the vehicle or aircraft and has carrier surfaces and in relation to which a rudder element (2) is attached ...
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WO/1997/026039A1 |
A chemical (coating and reduction)/mechanical/electrical treatment of ion-exchange materials (preferably ion-exchange membranes) to convert them to artificial muscles. The figure is a perspective view of an actuator of the invention show...
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WO/1997/012804A1 |
In an aircraft (1) according to the invention the engine drives a blower and the compressed air is used to increase the lift of the wing (18) and the canard (22) using jet flap propulsion. The airfoil profile has maximum thickness just f...
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WO/1996/036532A1 |
A passive porosity airfoil lift management device employed on a leading edge region (19) of the airfoil (1) whereby the lift on the airfoil (1) may be varied and controlled by passively transferring air pressure between the upper surface...
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WO/1996/009955A1 |
A leading edge (slat) and/or a trailing edge (flap) lift enhancing surface for an aircraft or a marine craft wing is connected to the wing by a linkage system. This system has at least two parallel spaced apart swing arms (12) with one e...
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WO/1995/016607A1 |
A reverse delta aerodynamic wing has a basic reverse delta wing portion bounded by a leading edge (30) and by a pair of trailing edges (10) extending from respective ends of said leading edge (30) toward a trailing apex point (P) and res...
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WO/1995/013214A1 |
A leading edge slat/wing combination (100) where the slat (104) is mounted to a pair of circularly curved carrier tracks (122) positioned within the outer surface contour of the fixed wing (102). In moving from the cruise configuration t...
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WO/1995/011159A1 |
An aircraft flight control system in which wing-mounted flight control output devices are employed in a multipurpose role. The system in one form includes wing-mounted port and starboard output assemblies (24, 25) of yaw and roll control...
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WO/1995/009764A1 |
A method of producing lift for a heavier-than-air aircraft by directing a generated flow of gas onto the aerodynamic surface, with regulation of the angle between the direction of gas outflow and the aerodynamic surface.
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WO/1994/001325A1 |
A wind turbine (10) has a rotor (20) with at least one blade (16) which has an aileron (26) which is adjusted by an actuator. A hinge has two portions, one for mounting a stationary hinge arm (98) to the blade, the other (96) for couplin...
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WO/1993/024363A1 |
A rudder device for water-going craft or aircraft, where there is provided in the vessel a cavity (21) which is open to the outside of the vessel. In the cavity there is provided a body (2) which can rotate about an axis (3), which exten...
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WO/1991/005699A1 |
The present invention provides an aircraft wing (10) having a main portion (20) with a trailing edge (20b) and a movable flaperon (22) hingedly secured at the trailing edge. A movable flaperon seal (40) is hingedly attached at its leadin...
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WO/1991/000824A1 |
A flap assembly includes a flap member (2) located at the trailing edge of an aircraft wing (4). A bracket (12) extends down from the flap member (2), and a mounting arm (8) extends rearwardly from the lower surface of the wing. Two link...
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WO/1990/009921A1 |
Drive device with variable torque-limiting system. When a setting mechanism (17) forming part of a crank mechanism (23) is actuated in order to displace a carrier waggon (19) to which a hydrofoil component (2) is fastened, large forces a...
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WO/1990/002079A1 |
The lateral blowing of air modifies the aerodynamic field about the wings and, according to the importance of the blown air flow rate, it improves the aerodynamic efficiency of the wings or even provides for the propulsion of the aircraf...
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