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Matches 1 - 50 out of 1,214

Document Document Title
WO/2021/009060A1
The invention relates to a wing (3) for an aircraft (1), comprising a main wing (5), a slat (7), and a connecting assembly (9) movably connecting the slat (7) to the main wing (5), such that the slat (7) is movable between a retracted po...  
WO/2021/004110A1
A water-air amphibious cross-medium bionic robotic flying fish, comprising a body, pitching pectoral fins (4), structure variable pectoral fins (5), a tail propulsion module, a detection sensor and a controller. The present invention con...  
WO/2021/005050A1
A movable flow body device for an aircraft is proposed, comprising an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a se...  
WO/2020/260391A1
A leading-edge arrangement for an aircraft is proposed, comprising a plurality of movable flow bodies, a supply duct, an air transfer duct, and at least one perforated tube, wherein the movable flow bodies are arranged in a consecutive a...  
WO/2020/254560A1
Disclosed is an actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1), the actuation unit (15) comprising a motor (17) configured to be mounted to a fixed wing (5) for an aircraft (1), a driv...  
WO/2020/245549A1
A space aircraft (1) comprises a fuselage (3), two wings (4A, 4B) arranged on either side of the fuselage (3), and two nacelles (7A, 7B) arranged at the ends of the wings (4A, 4B) and each carrying a horizontal tail (8A, 8B) and a vertic...  
WO/2020/239699A1
A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of th...  
WO/2020/239753A1
In order to reduce vibration of movable airfoil structures (38), such as rudders (22), elevators (24), and ailerons (20), a spring device (48), a leaf spring (50) for example, is mounted to an airfoil mounting structure (28), such as a v...  
WO/2020/237529A1
Provided are a flight control method and apparatus for an unmanned aerial vehicle, and an unmanned aerial vehicle. The method comprises: acquiring a flight mode switching command, the flight mode switching command instructing an unmanned...  
WO/2020/216737A1
An embodiment of the present invention provides an aerostructure assembly of an aircraft comprising a first aerostructure portion (201) extending in a direction between a first position (bl) and a second position (b2) and comprising stru...  
WO/2020/212568A1
The invention concerns a spar structure (11) for connecting a moveable component (4) to an aircraft. The structure is formed from a single continuous body of material defining a plurality of attachment/actuation brackets (10A-10F) and a ...  
WO/2020/196524A1
[Problem] To provide a flying vehicle capable of improving drive feelings and ride comfort for a person on board. [Solution] A flying vehicle which a person can get on board and which moves by floating above the ground is provided with a...  
WO/2020/196525A1
[Problem] To provide a flying vehicle capable of improving drive feelings and ride comfort for a person on board. [Solution] A flying vehicle which a person can get on board and which moves by floating above the ground is provided with a...  
WO/2020/187092A1
An unmanned aerial vehicle control device, comprising a master controller (11) and a rudder surface control structure (12). The rudder surface control structure comprises a driving controller (121), a driving mechanism (122), a transmiss...  
WO/2020/186305A1
A vertical take-off and landing (VTOL) aircraft (100) having: a wing structure having right and left side forward wings (20, 22); and right and left side rearward wings (30, 32), each of the right side wings (20, 30) being connected, and...  
WO/2020/187094A1
An unmanned aerial vehicle control device, comprising a main controller (11), a control surface control structure, and an angle detecting module; the control surface control structure comprises a drive controller (121), a drive mechanism...  
WO/2020/185947A1
A winged vertical take-off and landing aircraft with compound control surfaces comprising flaps and ailerons which can be operated simultaneously with each other offers improved aerodynamic performance and maneuverability. Configuration ...  
WO/2020/174084A1
A wing leading-edge device (2, 42) is proposed, which comprises a slat body (4, 42) having a front side (6) with a forward skin (8) and a back side (10) with a rearward skin (12), and at least a drive arrangement (14) having at least one...  
WO/2020/157052A1
The invention relates to an aircraft (1). Said aircraft is characterized by a wing (2) which, viewed in section, is delimited on one side by a first profiled surface (4), which is at the bottom when the aircraft (1) is operated as intend...  
WO/2020/142416A1
Technologies for providing blended wing body aircraft control surfaces are described herein. In some examples, one or more of the control surfaces have angular configurations that reduce the formation of air vortexes when in upward or do...  
WO/2020/107581A1
A movable platform (10) and steering engine thereof. The steering engine (10) comprises: an upper cover (110), a lower cover (130), and a middle shell (120) disposed between the upper cover (110) and the lower cover (130), wherein a top ...  
WO/2020/097357A1
Devices and systems of the inventive concept provide an aircraft flap system is deflected to achieve minimum drag in cruise, maximum coefficient of lift (CL) at low speed, and minimum download in hover. It does so by opening a gap or slo...  
WO/2020/059703A1
[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, a thrust gen...  
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...  
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...  
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...  
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 ...  
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...  
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...  
WO/2019/203673A4
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...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  
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...  
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...  
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...  
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...  
WO/2018/057828A3
A communications infrastructure (RSU) 30 with its airspace controller 32 provides a geo-fencing system that is capable of adaptive and progressive levels of control authority over the unmanned aircraft system (UAS) e.g., drone 20. The co...  
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...  
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...  
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...  
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...  
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...  
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...  
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 ...  
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...  

Matches 1 - 50 out of 1,214