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序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
121	External airbag protection system for helicopters	EP03029665.1	1998-03-12	EP1403180A2	2004-03-31	Rotman, Israel; Rosenberg, Gideon
An airbag protection system for helicopters. Airbags (14) are inflated either automatically or manually, or a combination of both, prior to the helicopter (10) striking the ground, thus avoiding or ameliorating a crash. Proximity sensors (32) detect a fast descent to trigger inflation of the airbags (14) located beneath the helicopter (10) fuselage so that they can cushion the impact with the ground. Venting of the gas from the airbags (14) is also provided to release the gas from the airbags so as to prevent rebound of the helicopter (10) from the ground.
122	Train d'atterrissage auxiliaire avant pour aéronef	EP00403433.6	2000-12-07	EP1106501A1	2001-06-13	Dazet, Francis; Ciprian, Danilo; Chaumel, Pascal
Le train avant d'un avion comprend un groupe principal d'au moins une roue (10) en contact permanent avec le sol et un groupe secondaire d'au moins une roue (12) normalement écarté du sol, lorsque l'avion est au sol. En cas de freinage d'urgence consécutif à un décollage avorté, ou en cas de crevaison d'un pneumatique (11) d'une roue (10) du groupe principal, la ou les roues (12) entrent en contact avec le sol. Un surdimensionnement du train avant est ainsi évité.
123	External airbag protection system for helicopters	EP98104489.4	1998-03-12	EP0869058A3	1999-06-09	Rotman, Israel; Rosenberg, Gideon
An airbag protection system for helicopters (10). Airbags (12,14,16) are inflated either automatically or manually, or a combination of both, prior to the helicopter striking the ground, thus avoiding or ameliorating a crash. Proximity sensors (24) detect a fast descent to trigger inflation of the airbags (12,14,16) located beneath the helicopter fuselage (10) so that they can cushion the impact with the ground. Venting of the gas from the airbags (12,14,16) is also provided to release the gas from the airbags (12,14,16) so as to prevent rebound of the helicopter (10) from the ground.
124	NOSE WHEEL WATER SPRAY DEFLECTOR.	EP81902719	1981-09-25	EP0089947A4	1984-12-11	GLASENAPP RUDI KARL HEINZ; MCCULLOCH ANDREW JOHN
A nose landing gear supported deflector (20) for preventing ingestion of nose wheel side spray into wing mounted engines. The deflector (20) extends horizontally with respect to the runway surface (200) and in front of the nose wheels (10) and (12) while permitting landing gear and deflector (20) retraction into the nose gear wheel well (600).
125	Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations	US15491701	2017-04-19	US10112707B1	2018-10-30	John V. Howard
An unmanned rotorcraft has a lift module having a propulsion system and coaxial rotors driven in rotation by the propulsion system. The rotorcraft includes a payload support system adapted to couple an external payload directly to the lift module. The rotorcraft is devoid of provisions for human passengers.
126	UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF	US16005309	2018-06-11	US20180281935A1	2018-10-04	Tao Wang; Tao Zhao; Shaojie Chen; Zhigang Ou
The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
127	Perching attachment for unmanned aircraft	US15080265	2016-03-24	US10081421B2	2018-09-25	William Semke; Weston Swetich
An aerial vehicle system includes a flight system configured to generate propulsive force and lift, a protective framework, and an attachment mechanism secured to the protective framework and configured to selectively attach to a structure to provide stable perching of the aerial vehicle system. The attachment mechanism is an electro-permanent magnet device or a talon-like grip. The flight system is at least partially enclosed by the protective framework.
128	Aerial vehicle with frame assemblies	US15294517	2016-10-14	US10046844B2	2018-08-14	Tao Wang; Tao Zhao; Hao Du; Mingxi Wang
Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.
129	Unmanned aerial vehicle	US14944418	2015-11-18	US10040547B1	2018-08-07	Samuel Pedigo
An unmanned aerial vehicle includes a vehicle body and a vehicle wing on the vehicle body. A front motor assembly is provided in the vehicle body and the vehicle wing. A front vertical air discharge pathway and a front horizontal air discharge pathway communicate with the front motor assembly. A front air diverter is disposed between a retracted position unblocking the front vertical air discharge pathway to impart vertical lift to the vehicle and an extended position blocking the front vertical air discharge pathway to impart horizontal thrust to the vehicle. A pair of rear motor assemblies is provided in the vehicle wing and each includes a rear vertical air discharge pathway and a rear horizontal air discharge pathway communicating with the rear motor assembly. A rear air diverter is disposed between a retracted position unblocking the rear vertical air discharge pathway to impart vertical lift to the vehicle and an extended position blocking the rear vertical air discharge pathway to impart horizontal thrust to the vehicle.
130	ADAPTIVE LANDING GEAR ASSEMBLY FOR ROTARY WING AIRCRAFT	US15580204	2016-06-24	US20180141644A1	2018-05-24	Peter James Waltner
An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.
131	Device for moving aircraft along the ground	US14898128	2014-06-11	US09932129B2	2018-04-03	Emmanuel Joubert; Charles Nespoulous; Bruno Rechain; Hichem Smaoui
A device for moving aircraft along the ground includes at least one runway and at least one aircraft. The aircraft is secured to a tractor element having a magnetic mass formed mainly of type II superconductor material and the runway includes stator coils arranged in the runway with at least one line of coils parallel to an axis of the runway. A command/control system supplies power to the stator coils to generate a magnetic field that levitates the tractor element, magnetized beforehand into a phase II superconducting state, above the runway.
132	EXTERNAL ANCHORING HARPOON FOR AIRCRAFT	US15714049	2017-09-25	US20180086482A1	2018-03-29	Olivier BISTUER; Jean Paul RENAUD; Patrice GARCIN; Pierre PRUD'HOMME LACROIX
An external anchoring harpoon for an aircraft in order to anchor the aircraft on an anchor grid of a platform, the external anchoring harpoon comprises a frame connected to the aircraft, a harpoon head, and a deployment device for deploying the harpoon head. The deployment device comprises a cable, a movement device for moving the cable connected to the frame, the cable being connected to the harpoon head and to the movement device. The deployment device also comprises a main telescopic strut and two secondary telescopic struts so as to enable the harpoon head to be centered under the aircraft and so as to enable the harpoon head to be anchored to the anchor grid.
133	PULSED LOCOMOTOR	US15533611	2015-01-12	US20170370344A1	2017-12-28	EDOUARD KASSIANOFF
A Pulsed Locomotor (120), for propelling media, fluids and crafts, in fluids and on land, comprising a blade (124) securely connected to a drive shaft (122). Upon reciprocation, the ambient medium is forced towards the trailing edge of the blade (124) thereby causing a reactive locomotion of the apparatus, substantially along the plane of the blade. Apparatus is secured to motor M by fastening through aperture (130). The apparatus can be operated directly by motor M, and indirectly by the reaction momentum imparted to a supporting platform P. Thrust is directed by steering handle (128) about a bearing (126), rotatably coupling to platform P and base C. Lubricant L is supplied to outlets (134) via conduit (136) and inlet (132), to coat the apparatus with a lubricant cavity, for drag reduction. The blade (124) planes along a figure 8 reciprocation path s1e1s2e2s1. Crafts are embodied.
134	AIRCRAFT SYSTEM AND METHOD FOR VERTICAL TAKEOFF AND LANDING	US15633174	2017-06-26	US20170369163A1	2017-12-28	Casey Joseph CARLIN; Luca RIGAZIO; Alexander Joseph ROMELFANGER
An aircraft having a fixed wing is operative to perform vertical takeoff and landing while positioned in a nose-down orientation. The aircraft has a fixed wing having a leading edge and a trailing edge; a propulsion system operative to selectively provide forward propulsion and rearward propulsion; and a controller operative to control operation of the propulsion system. The propulsion system provides rearward propulsion during takeoff of the aircraft to move the aircraft in a direction of the trailing edge of the fixed wing, and provides forward propulsion during flight of the aircraft to move the aircraft in a direction of the leading edge of the fixed wing. The aircraft maintains the wing substantially vertical with the trailing edge facing upwards during takeoff, and transitions to having the wing substantially horizontal during flight. A vertical landing procedure is also provided.
135	Amphibious vertical take off and landing unmanned device with AI data processing apparatus	US15345308	2016-11-07	US20170300051A1	2017-10-19	Dylan T X Zhou; Tiger T G Zhou; Andrew H B Zhou; Zhou Tian Xing
An amphibious VTOL unmanned aerial device, comprising, the cameras is adapted for providing a real-time first-person video and a real-time first-person view and normal footage video recording and 360-degree panoramic video recording used for virtual reality views and interactive video, the communication system to communicate with plurality of other devices Plurality of rotors, the rotors are adapted for creating the thrust, the solar panel is adapted for converting the solar energy to electrical use,the rear propeller is adapted for horizontal flight and also used as wind turbine to charge the batteries. The Al control device to control the various control surfaces and communication system, plurality of sensors, to detect the location of the drones, the stabilization system to stabilize the camera and the drone during the flight.
136	Vertical Take-Off-And-Landing Unmanned Aerial Vehicle System Capable of Landing on Uneven or Sloped Terrain	US15081163	2016-03-25	US20170274988A1	2017-09-28	Hoa G. Nguyen; Aaron B. Burmeister
A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot.
137	AERIAL VEHICLE WITH FRAME ASSEMBLIES	US15294517	2016-10-14	US20170096210A1	2017-04-06	Tao Wang; Tao Zhao; Hao Du; Mingxi Wang
Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.
138	Adjustable landing gear assembly for unmanned aerial vehicles	US14661955	2015-03-18	US09592908B2	2017-03-14	Nicholas Kristofer Gentry
This disclosure describes a configuration of an unmanned aerial vehicle (UAV) landing gear assembly that includes adjustable landing gear extension that may be extended or contracted so that the body of the UAV is contained in a horizontal plane when the UAV is landed, even on sloping surfaces. For example, when a UAV is landing, the slope of the surface may be determined and the landing gear extensions adjusted based on the slope so that the body of the UAV remains approximately horizontal when the UAV lands and is supported by the landing gear extensions.
139	VTOL symmetric airfoil fuselage of fixed wing design	US14849814	2015-09-10	US09567079B2	2017-02-14	Jonathon Thomas Johnson; Elizabeth V. M. Johnson
Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.
140	UAV docking system and method	US14272125	2014-05-07	US09561871B2	2017-02-07	Ramanathan Sugumaran
An aerial vehicle docking system includes a landing pad and an aerial vehicle. The landing pad has a concave landing surface and a depression. The aerial vehicle has landing gear and a protrusion. The protrusion is shaped to mate with the depression. The protrusion and the landing gear are positioned on a bottom surface of the aerial vehicle.

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