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WO/2020/059155A1 |
[Problem] To provide an aircraft in which safe and efficient transition from hovering to level flight has been made possible. [Solution] An aircraft according to the present invention is equipped with a lift generating unit such as a pri...
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WO/2020/055588A1 |
A method of deploying an unmanned aerial vehicle (UAV) includes launching a UAV and deploying at least one portion of a wing assembly from a stowed configuration to a deployed configuration in which the at least one portion of the wing a...
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WO/2020/038807A1 |
Disclosed is flap support (11) for supporting a flap (9) of a wing (5) for an aircraft (1), the flap support (11) comprising a load bearing fairing shell (13) and a reinforcement structure (31) at least partially received in the interior...
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WO/2020/000690A1 |
A fixed-wing unmanned aerial vehicle and an empennage (10) thereof, comprising: a fixing member (100), a steering rudder (200), a first mounting member (310), a steering engine connector (320), a transmission member (340) and a steering ...
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WO/2019/244096A1 |
A method for manufacturing prestressed shells having tunable bistability, characterized in that, in order to determine the appropriate prestress to be applied to the bistable structure/shel, it provides: clamping a shell by applying a pr...
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WO/2019/239103A1 |
An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be movea...
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WO/2019/228917A1 |
The invention relates to an aircraft wing (4) comprising a mobile leading edge flap (16) associated with a guiding device (40) arranged at the front of a front spar (32) of a wing box, and including: - a pivoting member (42) having one e...
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WO/2019/202321A1 |
A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device(103), a second actuator (104A)for actuating a second aerodynamic device (102), a first drive path (109B) c...
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WO/2019/203673A1 |
A personal flight apparatus with vertical take-off and landing conceived as a biplane apparatus constituted by two distinct parts articulated there between, the first distinct part consisting of the cockpit (1), which is hinged to the se...
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WO/2019/181365A1 |
The purpose of the present invention is to suppress an increase in pressure of internally contained lubricating oil and to reduce leakage of the lubricating oil. This actuator (1) is provided with: an accumulator (4) which has a gas comp...
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WO/2019/172072A1 |
A high-lift device 11 provided to the main wing 10 of an aircraft 1, the high-lift device 11 comprising a slat 15 and a slat moving mechanism 16 that moves the slat 15 between a deployed position and a storage position. The slat 15 has a...
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WO/2019/167846A1 |
A high-lift device (1) is provided with: a flap (2) disposed at a front edge (50a) of a main wing (50), and configured to be stored in the lower surface of the front edge (50a) and to be extended forward of the front edge (50a); a first ...
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WO/2019/156604A1 |
The present invention regards a hollow load-bearing beam structure (1) and a method for manufacturing of the structure. The structure (1) comprises fiber-reinforced composite material. The structure (1) comprises a first plurality of lam...
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WO/2019/154698A1 |
Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5), a slat (7), and a connection assembly (9) movable connecting the slat (7) to the main wing (5), wherein the connection assembly (9) comprises an elongate slat track...
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WO/2019/139654A1 |
There is provided a dual rack and pinion rotational inerter system (500) for damping movement (694) of a flight control surface (122) of an aircraft (100). The system (500) has a flexible holding structure (506) disposed between the flig...
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WO/2019/139653A1 |
There is provided a translational inerter assembly (500) for damping movement (606) of a flight control surface (122) of an aircraft (100). The assembly (500) has a press fit element (510) fixedly disposed within a first end (502a) of th...
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WO/2019/125789A1 |
A buoyant aerial vehicle includes: a balloon configured to store a gas; a pay load coupled to the balloon; and a propulsion unit coupled to the payload by a tether. The propulsion unit includes: a fuselage having a substantially longitud...
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WO/2019/074349A1 |
The invention relates to aviation equipment. An object of this invention is to develop a new non-conventional aerodynamic apparatus that can increase the efficiency of the air flow power use to generate lifting force, control moments and...
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WO/2019/063600A1 |
The invention relates to an aircraft (1) in kite configuration, with a fuselage (2), an aerofoil (5), a horizontal stabiliser (7), which is distanced from the aerofoil (5) via a tail assembly (6), is arranged in the region of the tail (3...
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WO/2019/056053A1 |
A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control su...
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WO/2019/056052A1 |
A vertical take-off and landing (VTOL) aircraft (10) includes a fuselage and first and second forward wings (20, 22), each wing (20, 22) having a fixed leading edge and a trailing control surface (50) which is pivotal about a generally h...
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WO/2019/041004A1 |
Noise-abatement for a leading edge wing slat is provided by a noise-abatement airflow shield integral with the lower trailing edge of the slat, wherein the shield is reciprocally autonomously curvable from a substantially planar configur...
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WO/2019/041003A1 |
A noise-abatement systems (10) provide noise abatement to a wing assembly (Wp) provided with a forward edge slat (ES) and include an elongated shield element (20) which is unconnected but positionable adjacent to a lower trailing edge (1...
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WO/2019/041252A1 |
A power device (100) comprises a duct (1), a main rotor (2), and at least two lattice fins (3). The main rotor (2) is positioned in the duct. The main rotor (2) is used to drive a fluid to flow in the duct to generate power. The lattice ...
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WO/2019/034851A1 |
The present invention provides a vehicle comprising: a rotor and a stator; at least one planar control surface coupled to the rotor, wherein the rotor is configured to rotate relative to the stator such that, in use, the at least one pla...
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WO/2019/025343A1 |
The invention relates to a fastening unit (100) for movably fastening an aircraft component (300) to a support structure (400) of an aircraft (500). The fastening unit (100) has a connection element (5) having a hole (5a). The fastening ...
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WO/2019/024398A1 |
A coupling device for inner and outer flaps, comprising: a piston cylinder assembly (2); a piston rod assembly (1), which is provided in the piston cylinder assembly and is radially fixed and axially movable relative to the piston cylind...
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WO/2019/012297A1 |
Embodiments relate to reconfigurable unmanned vehicles (100). Such vehicles (100) comprise a fuselage (102) presenting a bay (118) for receiving a plurality of components (120-128), each of the plurality of components (120-128) relating ...
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WO/2019/000545A1 |
Disclosed are an unmanned aerial vehicle and a fixed wing thereof. The fixed wing (10) comprises a body (11), control surfaces (12), a stretching reinforcement member (13) and a shearing reinforcement member (14), wherein the control sur...
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WO/2018/234104A1 |
A wing and flap system for an aircraft comprising: a wing; and a deployable flap connected to the wing, the flap being moveable between a first position in which a trailing edge portion of the wing substantially overlaps the flap and the...
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WO/2018/229761A1 |
According to the presently disclosed subject matter there is provided an in-flight UAV retrieval system mountable on an aircraft and configured to execute a UAV retrieval process for retrieving one or more in-flight UAVs into the aircraft.
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WO/2018/217667A1 |
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors,...
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WO/2018/211233A1 |
A structural assembly (900) and method of fabricating the same, the method comprising: providing a first member (204) comprising a bond surface (800) and a plurality of protrusions (802) extending from the bond surface (800), a length of...
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WO/2018/211232A1 |
A stiffening structure for an aircraft panel or door and method for fabricating the same, the method comprising: providing a thermoplastic continuous fibre-reinforced composite material comprising a plurality of continuous fibres embedde...
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WO/2018/197265A1 |
The present invention relates to a wing(2) for an aircraft, comprising: a main wing (4) having an outer skin (6) defining an interior space (8) of the main wing, a slat (10), and a connection assembly (12) for movably connecting the slat...
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WO/2018/197649A1 |
The present invention relates to a wing (3, see Fig.1) for an aircraft (1, see Fig.1), comprising a main wing (5, see Fig.1), a slat (7, see Fig.1), and a connection assembly (9, see Fig.1) movable connecting the slat (7, see Fig.1) to t...
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WO/2018/145675A1 |
Tail sitter aircraft, comprising a fuselage (4) and a pair of wings (5), each wing having a leading edge (50) and a trailing edge (55), wherein each of the wings (5) is provided with a propeller propulsion unit and a plurality of control...
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WO/2018/145173A1 |
A device (10) for adjusting the control surfaces (40) of an aircraft (50) is described, comprising an elongate structural body (20) formed by a base (201) arranged on a first end (22) and attached to the structure of the aircraft (50) an...
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WO/2018/144915A1 |
A system and method for resisting an uncontrolled descent or uncontrolled flight condition of an aerial vehicle. The system includes a control system, sensors, an inflation device, and a descent-restraint system. The control system detec...
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WO/2018/138034A1 |
The invention relates to an assembly (20) for an aircraft comprising a fuselage portion (5a) of the aircraft and an adjacent movable trailing edge flap (16), the flap comprising an inner end secured to an actuation shaft (22) for the fla...
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WO/2018/134756A1 |
The invention relates to an aircraft having a tailless fuselage. The fuselage has a body which includes a transverse trailing edge. The aircraft further includes a wing having two sides which protrude from opposite sides of the fuselage....
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WO/2018/109582A1 |
A slat (50) for an aircraft wing comprises a leading edge (51) defining a leading edge line (61), a trailing edge (52) defining a trailing edge line (62), the leading and trailing edges line defining a slat plane, the chord distance (69)...
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WO/2018/111488A1 |
An aircraft including a wing system, a plurality of control surfaces, a camera mounted on a camera pod, and a control system. The camera pod is configured to vary the orientation of the camera field of view only in yaw, relative to the a...
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WO/2018/104251A1 |
An aircraft wing assembly (5) is presented comprising a main wing portion (21), a high-lift device (9) comprising a flow surface with an upper skin portion (25) and a lower skin portion (27), wherein the high-lift device is movable betwe...
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WO/2018/098993A1 |
Disclosed are a dual-axis vector servo steering device for a propeller and a vertical take-off and landing of an unmanned aerial vehicle with fixed wings. The dual-axis vector servo steering device comprises a fixed steering engine fixed...
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WO/2018/089583A1 |
Systems, devices, and methods for an extruded wing protection and control surface (126) comprising: a channel (206) proximate a leading edge (202) of the control surface, a knuckle (210) disposed about the channel, a leading void (212), ...
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WO/2018/083077A1 |
The present invention is concerned with actuating aircraft components to tailor their configuration to achieve improved performance in one or more flight phases. In general terms, the invention provides a method and system for actuating ...
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WO/2018/083145A1 |
The invention relates to an aircraft wing comprising a mobile trailing edge flap (16), the wing comprising a device (50) for moving said flap, the device being provided with: a beam (51) supporting a guide rail; a carriage (52a) movably ...
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WO/2018/083144A1 |
The invention relates to an aircraft wing comprising a stationary central wing body as well as at least one mobile leading edge flap (16) intended for being moved relative to the stationary central body between an extended position and a...
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WO/2018/059991A1 |
A system for driving and guiding of a trailing edge control surface (24) arranged on a trailing edge region (6) of a wing (2) of an aircraft comprises a first guide device (9) attachable to the wing (2) and coupled with the control surfa...
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