| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | VERTICAL TAKE-OFF AND LANDING, AERODYNAMICALLY SELF-SUSTAINED HORIZONTAL FLIGHT HYBRID AIRCRAFT | EP98962657.7 | 1998-12-09 | EP1037796B1 | 2002-07-17 | Capanna, Franco |
| The invention concerns a vertical take-off and landing, aerodynamically self-sustained horizontal flight hybrid aircraft (1; 11) comprising a propulsion system providing at least a fixed blade propellor/rotor (2; 12) on the front part of the aircraft, connected to the main engine(s) of the aircraft, and at least one auxiliary engine (3; 13), placed in the rear part of the aircraft, said auxiliary engine being progressively tiltable and swingable between two limit positions, respectively a vertical and a horizontal position, the piloting cabin (4; 14) and the passenger area (5; 15) being realised as swingable modules, in such a way to continuously maintain the horizontal position of the pavement and of the ceiling parallel with respect to the ground during each flying phase, i.e. during the take-off, the transition phase and the horizontal flight, and vice versa, said aircraft taking-off with a vertical attitude (front portion upward) and progressively changing the attitude by the help of the rear auxiliary tiltable engines, reaching a completely horizontal attitude, and vice versa, and coming back in the vertical attitude during the landing. | ||||||
| 162 | VERTICAL TAKE-OFF AND LANDING, AERODYNAMICALLY SELF-SUSTAINED HORIZONTAL FLIGHT HYBRID AIRCRAFT | EP98962657.7 | 1998-12-09 | EP1037796A1 | 2000-09-27 | Capanna, Franco |
| The invention concerns a vertical take-off and landing, aerodynamically self-sustained horizontal flight hybrid aircraft (1; 11) comprising a propulsion system providing at least a fixed blade propellor/rotor (2; 12) on the front part of the aircraft, connected to the main engine(s) of the aircraft, and at least one auxiliary engine (3; 13), placed in the rear part of the aircraft, said auxiliary engine being progressively tiltable and swingable between two limit positions, respectively a vertical and a horizontal position, the piloting cabin (4; 14) and the passenger area (5; 15) being realised as swingable modules, in such a way to continuously maintain the horizontal position of the pavement and of the ceiling parallel with respect to the ground during each flying phase, i.e. during the take-off, the transition phase and the horizontal flight, and vice versa, said aircraft taking-off with a vertical attitude (front portion upward) and progressively changing the attitude by the help of the rear auxiliary tiltable engines, reaching a completely horizontal attitude, and vice versa, and coming back in the vertical attitude during the landing. | ||||||
| 163 | An unmanned vertical take-off and landing, horizontal cruise, air vehicle | EP93310646.0 | 1993-12-31 | EP0661206B1 | 2000-03-01 | Ebbert, Marvin D.; Gustin, Russell G.; Horbett, Edward C.; Edwards, Jack J.; Adcock, Clifton L. |
| 164 | THRUST VECTORING FREE WING AIRCRAFT | EP93907455.5 | 1993-03-12 | EP0629164B1 | 1999-05-26 | SCHMITTLE, Hugh J. |
| The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66). | ||||||
| 165 | LOCKABLE FREE WING AIRCRAFT | EP92925289.8 | 1992-11-20 | EP0621843B1 | 1999-03-24 | SCHMITTLE, Hugh J. |
| 166 | THRUST VECTORING FREE WING AIRCRAFT. | EP93907455 | 1993-03-12 | EP0629164A4 | 1995-07-12 | SCHMITTLE HUGH J |
| The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66). | ||||||
| 167 | Unmanned aerial vehicle (UAV) having vertical takeoff and landing (VTOL) capability | US15168842 | 2016-05-31 | US10137983B2 | 2018-11-27 | David Horn |
| An unmanned aerial vehicle (UAV), or drone, includes a fuselage, left and right airfoil-shaped wings connected to the fuselage to generate lift in forward flight, a left thrust-generating device supported by the left wing, and a right thrust-generating device supported by the right wing. The UAV further includes a vertical stabilizer, a top thrust-generating device mounted to a top portion of the vertical stabilizer, and a bottom thrust-generating device mounted to a bottom portion of the vertical stabilizer. An onboard power source is provided for powering the thrust-generating devices. The left, right, top and bottom thrust-generating devices provide forward thrust during forward flight and also provide vertical thrust to enable the unmanned aerial vehicle to take-off and land vertically when the fuselage is substantially vertical and further enabling the unmanned aerial vehicle to transition between forward flight and vertical take-off and landing. | ||||||
| 168 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS | US16027848 | 2018-07-05 | US20180312248A1 | 2018-11-01 | Markus Leng |
| An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control. | ||||||
| 169 | EFFICIENT VTOL RESOURCE MANAGEMENT IN AN AVIATION TRANSPORT NETWORK | US15961806 | 2018-04-24 | US20180308366A1 | 2018-10-25 | Nikhil Goel; Jon Petersen; John Badalamenti; Mark Moore |
| A transport network management system identifies a service objective for a plurality of VTOL aircraft and retrieves VTOL data including locations of the plurality of VTOL aircraft. An estimate of demand for transport services to be provided at least in part by one of the VTOL aircraft is generated and routing data for the plurality of VTOL aircraft is determined based on the estimated demand and the service objective. Routing instructions based on the routing data are sent to at least a subset of the VTOL aircraft. | ||||||
| 170 | AN AIR VEHICLE AND IMAGING APPARATUS THEREFOR | US15768729 | 2016-10-28 | US20180305009A1 | 2018-10-25 | David Julian Wright; Nicholas Giacomo Robert Colosimo; Clyde Warsop |
| An air vehicle (10) comprising a main body (12) and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12) having a principal axis orthogonal to the longitudinal axis (20) of said wing members, at least a first propulsion device (16a) associated with a first of said wing members arranged and configured to generate a linear thrust relative to the main body in a first direction, and a second propulsion device (16b) associated with a second of said wing members arranged and configured to generate linear thrust relative to said main body in a second, substantially opposite, direction such that said wing members and said main body are caused to rotate about said principal axis, in use, the air vehicle further comprising an imaging system (100) configured to cover a substantially 360° imaging area about said principal axis and comprising at least one electro-optic sensor (102) mounted on a support member (104) and having a field of view (102a) covering a portion of said imaging area, said support member being mounted on said air vehicle, said imaging system (100) further comprising a control module (400) configured to define an object or region of interest in relation to said air vehicle, determine a nominal sensor field of view incorporating said object or region of interest, and obtain sequential image data from a sensor having a field of view matching said nominal field of view as said air vehicle completes a rotary cycle. | ||||||
| 171 | Tail sitter vehicle with aerial and ground refueling system | US15070599 | 2016-03-15 | US10106274B2 | 2018-10-23 | Mark R. Alber; Charles Gayagoy; Jeffrey Parkhurst; Glenn D. Tiongson |
| An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations. | ||||||
| 172 | AUTONOMOUS FLIGHT VEHICLE CAPABLE OF FIXED WING FLIGHT AND ROTARY WING FLIGHT | US15608324 | 2017-05-30 | US20180290743A1 | 2018-10-11 | David Vorsin |
| An autonomous flight vehicle capable of both rotary wing flight and fixed wing flight may include a pair of rotary wing flight thrusters used during rotary wing flight and a smaller pair of hybrid flight thrusters used during both rotary wing flight and fixed wing flight. The larger rotary wing flight thrusters are skewed at an angle to reduce an apparent torque and improve the controllability of the autonomous flight vehicle, while using smaller, and so more efficient, thrusters during fixed wing flight. | ||||||
| 173 | Transportation Services for Pod Assemblies | US16001925 | 2018-06-06 | US20180281943A1 | 2018-10-04 | John Richard McCullough; Paul K. Oldroyd |
| In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly. | ||||||
| 174 | FLYING WING VERTICAL TAKE-OFF AND LANDING AIRCRAFT | US15544698 | 2015-11-19 | US20180281942A1 | 2018-10-04 | Mark W. Scott; Colin Kemater Bunting |
| A flying wing vertical take-off and landing (VTOL) aircraft is provided and includes an empennageless-fuselage from which foldable wings extend outwardly, an empennageless-nacelle supported on each of the wings and a rigid rotor propeller disposed on each empennageless-nacelle, each of the propellers being drivable to rotate about only a single rotational axis defined along a longitudinal axis of the corresponding empennageless-nacelle and being fully cyclically controllable. | ||||||
| 175 | Vertical take-off and landing (VTOL) aircraft with exhaust deflector | US14987295 | 2016-01-04 | US10077108B2 | 2018-09-18 | Timothy Fred Lauder |
| A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions. | ||||||
| 176 | DISTRIBUTED PROPULSION SYSTEM FOR VERTICAL TAKE OFF AND LANDING CLOSED WING AIRCRAFT | US15593575 | 2017-05-12 | US20180244376A1 | 2018-08-30 | Carlos Alexander Fenny; Rohn Lee Olson; Andrew James Zahasky |
| An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A plurality of hydraulic or electric motors are disposed within or attached to the closed wing, fuselage or spokes in a distributed configuration. A propeller is proximate to a leading edge of the closed wing or spokes and operably connected to each hydraulic or electric motor. A source of hydraulic or electric power is disposed within or attached to the closed wing, fuselage or spokes and coupled to each hydraulic or electric motor disposed within or attached to the closed wing, fuselage or spokes. A controller is coupled to each hydraulic or electric motor, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors. | ||||||
| 177 | VERTICAL TAKE OFF AIRCRAFT | US15896894 | 2018-02-14 | US20180237135A1 | 2018-08-23 | Stephen MORRIS |
| An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight mode, and transition the aircraft from the vertical flight mode to the horizontal flight mode. | ||||||
| 178 | SIX DEGREE OF FREEDOM AERIAL VEHICLE WITH A RING WING | US15435121 | 2017-02-16 | US20180229839A1 | 2018-08-16 | Gur Kimchi; Louis LeRoi LeGrand, III; Dominic Timothy Shiosaki; Ricky Dean Welsh |
| Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation. | ||||||
| 179 | DISTRIBUTED PROPULSION SYSTEM | US15593458 | 2017-05-12 | US20180215462A1 | 2018-08-02 | Carlos Alexander Fenny; Rohn Lee Olson |
| The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors. | ||||||
| 180 | EXTRUDED WING PROTECTION SYSTEM AND DEVICE | US15807939 | 2017-11-09 | US20180186443A1 | 2018-07-05 | Pavel Belik; John Peter Zwaan |
| Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface. | ||||||
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