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Matches 1 - 50 out of 2,199

Document Document Title
WO/2019/028871A1
A frame assembly (10) and an unmanned aerial vehicle (100). The frame assembly (10) comprises a frame (12), a support frame (14), and a connecting mechanism (16). The frame (12) comprises a central frame (122) and struts (124) movably co...  
WO/2019/024200A1
Disclosed are a foot stand (10) and an unmanned aerial vehicle (100). The foot stand (10) is used in the unmanned aerial vehicle (100), wherein the unmanned aerial vehicle (100) comprises a fuselage and a fuselage foot stand (20) connect...  
WO/2019/026350A1
A landing gear for a rotary-wing aircraft according to one embodiment of the present invention comprises two skid-tubes, and a cross-tube for linking the two skid-tubes and attaching the two skid-tubes to a fuselage of the rotary-wing ai...  
WO/2019/021564A1
A multicopter 10 comprises a multicopter body M and a leg unit 36 attached to the multicopter body M. The leg unit 36 includes four legs 38. Each of the legs 38 includes a leg body 46 and a reinforcing member 48. A gap C1 between the leg...  
WO/2019/007133A1
A landing gear and an unmanned aerial vehicle (UAV) having the same. The landing gear (20) comprises a driving assembly (210), and a landing gear body (220), wherein the driving assembly comprises a connecting member (213) and a driving ...  
WO/2019/007130A1
A landing gear and an unmanned aerial vehicle (UAV) having the same. The landing gear (20) comprises a driving assembly (210) and a landing gear body (220), wherein the driving assembly (210) comprises a connecting member (213) and a dri...  
WO/2019/007835A1
A hovering air vehicle (HAV) comprising a main body (1) with a plurality of actuators each with a rotor, at least one payload unit (2) on a gimbal (3), the main body is connected by a rotating element (4) to an undercarriage (5), the HAV...  
WO/2019/000549A1
Provided is a support frame, comprising a locking assembly (1) and at least two support rods (2), wherein the locking assembly (1) comprises a first locking frame (11) and a locking block (12); the at least two support rods (2) are arran...  
WO/2019/002285A1
This locking device for an electromechanical actuator comprises a rod (3) that is movable relative to a cylinder (2) under the action of a motor actuating the rod, an assembly of at least one hook (10) that can be moved between a locked ...  
WO/2019/005748A1
The present invention comprises an aircraft tire moistening system that provides for aircraft tires to be lubricated with fluid prior to spin up on landing. The resulting lubricity reduces the friction and heat caused by spin up and, the...  
WO/2018/228033A1
Landing gear (20) of an unmanned aerial vehicle, comprising a power assembly (200) arranged in a fuselage (10) and a landing gear body (201) connected to the power assembly (200). The power assembly (200) comprises a first connecting pie...  
WO/2018/231321A2
An expendable rotary wing unmanned aircraft capable of storage in a cylindrical housing includes a longitudinally extending body having an upper end and a lower end; and a pair of counter-rotating coaxial rotors each located at respectiv...  
WO/2018/224058A1
The invention concerns a system of wheel suspension for motor vehicles and/or airplanes with a suspension mechanism for attaching a wheel and attached to a frame, where suspension mechanism (1) arranged in plane (3) of the suspension of ...  
WO/2018/224947A1
A composite crushable member (10) comprising a reinforcing composite (12) is disclosed herein. The composite crushable member comprises a reinforcing region (16) and a trigger region (18a-18e) and at least one of a first physical propert...  
WO/2018/222388A1
We describe an aircraft design, which is capable of vertical takeoff and landing and also high-speed cruise on a fixed wing. The aircraft comprises a fuselage with a probe-deployment mechanism, which deploys a sample-gathering probe, loc...  
WO/2018/214626A1
Disclosed is a landing gear for a vertical takeoff and landing aircraft, comprising: a top portion connection plate (1) for connection with a vertical takeoff and landing aircraft; and a bottom portion connection plate (5) arranged oppos...  
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,...  
WO/2018/216825A1
The present invention relates to a hybrid unmanned aerial vehicle capable of driving and flying, particularly comprising: a main body which is arranged at the center so as to form a frame and has driving apparatus connection arms extendi...  
WO/2018/209428A1
A low noise aircraft comprising a fuselage comprising a nose section, a cabin and a tail comprising an empennage, the profile of the fuselage tightening towards the tail, two wings mounted on opposite sides of the fuselage, two engines, ...  
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...  
WO/2018/213190A1
An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on...  
WO/2018/203036A1
An unmanned aerial vehicle (2) comprising: a fixed wing (6); a pair of nacelles (10) connected to the wing (6) and spaced laterally either side of a centreline of the wing (6), wherein each nacelle (10) comprises a stationary portion (14...  
WO/2018/197772A1
The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). At least two w...  
WO/2018/197448A1
The invention relates to a method for attenuating vibrations of an aircraft wheel/brake assembly arising during braking, the brake comprising rotor discs (2b) rotationally driven with the wheel by means of bars (5) secured to the wheel a...  
WO/2018/192629A1
The invention relates to a method for monitoring the state of a mechanical brake of an aircraft, characterized by the following steps: a. measuring the temperature T of the brake at at least one point in time t2 during a landing process ...  
WO/2018/189324A1
An unmanned airborne vehicle (UAV) recovery system (10) for in-flight recovery of a fixed wing UAV (16) is described. The recovery system (10) comprises a catching device (12) and a plurality of hover-capable drones (14), such as multi-r...  
WO/2018/189299A1
An uplock (101) for use with an aircraft component. The uplock comprises a hook (102) configured to engage a capture pin (126) mounted on the aircraft component. The hook (102) is mounted for movement between a closed position and an ope...  
WO/2018/182883A1
Methods, devices, and systems of various embodiments are disclosed for operating a propeller assembly for use with a UAV. Various embodiments include a propeller assembly including a pivotal arm, a propeller mounted on the pivotal arm, a...  
WO/2018/178145A1
The invention concerns a mechanical reduction gear (156) comprising: - an input shaft (158) rotated by a motor, - an output shaft (160) coaxial with the input shaft (158), - an endless screw (250) mounted coaxially on the input shaft (15...  
WO/2018/182496A1
A device configured to deploy a retractable landing gear having a main landing gear (110) and a secondary landing gear (120) is provided. The device comprises an electrical motor (130) in driving connection with a drive shaft (140) conne...  
WO/2018/173765A1
This control device (C) controls a linear actuator (1) that raises and lowers a landing gear (L) on the basis of the stroke displacement of the linear actuator (1) as detected by a stroke sensor (10). When the landing gear (L) is to be s...  
WO/2018/166436A1
Disclosed is an unmanned aerial vehicle sliding-type mechanical arm device comprising a mechanical arm (1), a mechanical arm seat (2), and an electric motor impeller assembly (3) mounted on the mechanical arm (1), wherein the mechanical ...  
WO/2018/158255A1
A control system (20) has both a first and second processing modules (22, 24) for controlling retraction and extension of a landing gear assembly (14) on an aircraft (10). The processing modules can operate independently of each other an...  
WO/2018/150748A1
Provided is an agricultural multicopter in which legs (skids) for supporting a body can be reinforced by using a supporting structure for work devices, such as tanks. This agricultural multicopter comprises: a body; a plurality of arms w...  
WO/2018/141072A1
An inflatable, amphibious landing gear comprising one or more inflated pontoons with wheels attached and with one or more air bladders below each inflated pontoon. When the air bladders are inflated, they extend below the wheels and prov...  
WO/2018/133192A1
Provided are a stand assembly (100) and an unmanned aerial vehicle (200). The stand assembly (100) is applied in the unmanned aerial vehicle (200). The stand assembly (100) comprises a fixing assembly (20) to be connected to a vehicle bo...  
WO/2018/133006A1
A landing gear control method and device for an unmanned aerial vehicle, user equipment unit, unmanned aerial vehicle, and unmanned aerial vehicle system. The method comprises: detecting whether a ground height of an unmanned aerial vehi...  
WO/2018/121804A1
An electric drive system of a gyroplane (28) comprising a support rotor (11), a primary engine (7) connected with a pusher propeller (8) for movement in air, and an electric motor (1) for movement on road, wherein the primary engine (7) ...  
WO/2018/120890A1
An unmanned aerial vehicle (100), comprising a body (10) and an undercarriage (20); the undercarriage (20) is entirely received in the body (10) in a folding state; the undercarriage (20) is entirely received in the body (10) when folded...  
WO/2018/120044A1
An unmanned aerial vehicle and a landing gear system thereof. The landing gear system (1) comprises: a drive mechanism (2), a transmission mechanism (31) and a plurality of landing gear mechanisms (3); the drive mechanism (2) comprises a...  
WO/2018/108148A1
An unmanned aerial vehicle, comprising a fuselage (1) and multiple arms (2) disposed at left and right sides of the fuselage (1), said unmanned aerial vehicle also comprising a sliding mechanism; open grooves (3,11) are provided on the f...  
WO/2018/111924A1
Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods. A representative system includes a first, carrier aircraft having an airframe a propulsion system carried by the airframe and positioned to support ...  
WO/2018/107561A1
A method for controlling landing of an unmanned aerial vehicle (400, 500), comprising: an unmanned aerial vehicle (400, 500) measures N distances from N undercarriages (12, 13, 14, 15) to the ground when the unmanned aerial vehicle (400,...  
WO/2018/095214A1
Disclosed are an unmanned aerial vehicle (10) and a landing gear device (2) thereof. The landing gear device (2) comprises a landing gear body (21) and a power assembly (22) mounted on a fuselage (1). The power assembly (22) comprises a ...  
WO/2018/095238A1
An unmanned aerial vehicle (200) and an undercarriage device (100) thereof. The undercarriage device (100) comprises an undercarriage body (40), a power mechanism (10), a first connecting mechanism (20), and a second connecting mechanism...  
WO/2018/090810A1
Disclosed are a landing gear (100) and an aircraft. The landing gear (100) is mounted on the aircraft and is used for take-off and landing of the aircraft. The landing gear (100) comprises: an elastic buffer member connected to the aircr...  
WO/2018/091475A1
The invention relates to an electrohydraulic module (1) for driving at least one component of an aircraft, in particular an airplane, wherein the electrohydraulic module (1) comprises at least one electric motor (2) and at least one comp...  
WO/2018/085902A1
The present invention provides an inflation system (12) for use in a buoyancy system (14). The buoyancy system is adapted to be fitted to an aircraft (15) for recovering and retaining the aircraft (15) at the surface of a body of water (...  
WO/2018/088915A1
The purpose of the present invention is to cool the brakes of the landing gear of an aircraft. For this purpose, the air of the air-conditioning system of the aeroplane is used. Pre-conditioned air from the outside can be supplied to the...  
WO/2018/087934A1
Provided is a control system for an aircraft that increases diagnostic precision of an oil pressure system (1). An oil pressure system (1) of this control system is provided with: a drive device (11) for driving a landing member (2); a c...  

Matches 1 - 50 out of 2,199