| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | WING STRUCTURE AND FAIRING DEVICE | EP10822101.1 | 2010-10-07 | EP2487371A1 | 2012-08-15 | KIMURA, Yukihide; MORIMOTO, Tomoaki |
The invention provides a wing structure 1 including: a main wing 2 that extends in a second direction intersecting a first direction as a fluid flow direction; and an auxiliary wing 3 that is disposed so as to be separated from the main wing 2 and faces the main wing 2 at the front part side of the main wing 2, wherein a wing chord length of the auxiliary wing 3 is shorter than a wing chord length of the main wing 2. According to the invention, a fluid contacts the auxiliary wing 3 which is formed at the front part side of the main wing 2, the fluid is guided between the auxiliary wing 3 and the main wing 2, and the fluid is compressed when passing between the auxiliary wing 3 and the main wing 2, thereby appropriately forming a fluid compression process region on the surface of the main wing 2 and increasing an acting force. |
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| 62 | Robotic Vehicle | US15578627 | 2016-05-18 | US20180312023A1 | 2018-11-01 | Adam Braithwaite; Talib Alhinai; Mirko Kovac |
| A robotic vehicle has legs and propellers to enable it to walk, fly, and or swim. | ||||||
| 63 | Remotely Controlled Modular VTOL Aircraft And Re-Configurable System Using Same | US15143625 | 2016-05-01 | US20180265193A1 | 2018-09-20 | Jeffrey Kyle Gibboney; Pranay Sinha |
| A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle system which has removable wing sections which allow for re-configuration with different wing section types, allowing for configurations adapted for a particular flight profile. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability. | ||||||
| 64 | ENHANCED NET PITCHING MOMENT MULTI-WING VTOL COMPACT PERSONAL AIRCRAFT | US15683870 | 2017-08-23 | US20180093765A1 | 2018-04-05 | BRENDAN GRAHAM |
| This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation. | ||||||
| 65 | Aircraft with Selectively Attachable Passenger Pod Assembly | US15200163 | 2016-07-01 | US20180002011A1 | 2018-01-04 | John Richard McCullough; Paul K. Oldroyd |
| In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween. | ||||||
| 66 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | US15327237 | 2015-07-16 | US20170158321A1 | 2017-06-08 | Mohamed Reza Mia |
| A vertical take-off and landing (VTOL) aircraft is provided comprising a fuselage (12) defining a forward end and an aft end, the fuselage accommodating at least one engine (56), a left wing (18) and a right wing (20) extending from either side of the fuselage, a lift fan drive system (22) accommodated within each wing, a forward thrust fan drive system (24) fitted proximate the aft end of the fuselage, and a stabiliser arrangement (26) proximate the forward thrust fan drive system. In an embodiment, each wing comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion, the wing tip portion being angled towards the rear and side of the aircraft. In an embodiment, the rotor housing portion comprises two rotor housings, one forward of the aircraft's centre of gravity and one aft of the aircraft's centre of gravity. | ||||||
| 67 | Stackable wing for an aerocar | US14872415 | 2015-10-01 | US09580167B2 | 2017-02-28 | Umesh N. Gandhi; Robert W. Roe |
| An aerocar includes a body and a multiple of wings. The multiple of wings can be selectively extendable away from a top portion of the body for a flight mode. The multiple of wings can be selectively retractable toward the top portion of the body for a roadable mode. | ||||||
| 68 | MODULAR INTELLIGENT TRANSPORTATION SYSTEM | US15185926 | 2016-06-17 | US20170025000A1 | 2017-01-26 | Paul J. Lagassey |
| A modular intelligent transportation system, comprising an environmentally protected enclosure, a system communications bus, a processor module, communicating with said bus, having a image data input and an audio input, the processor module analyzing the image data and/or audio input for data patterns represented therein, having at least one available option slot, a power supply, and a communication link for external communications, in which at least one available option slot can be occupied by a wireless local area network access point, having a communications path between said communications link and said wireless access point, or other modular components. | ||||||
| 69 | Aircraft Capable of Vertical Take-Off | US14915101 | 2014-08-29 | US20160207625A1 | 2016-07-21 | Michael JUDAS; Friederike STRATENBERG; Jan VAN TOOR; Werner SCHOLZ; Berthold KARRAIS; Wolfgang STANGL |
| The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive. | ||||||
| 70 | STACKABLE WING FOR AN AEROCAR | US14872415 | 2015-10-01 | US20160068253A1 | 2016-03-10 | Umesh N. Gandhi; Robert W. Roe |
| An aerocar includes a body and a multiple of wings. The multiple of wings can be selectively extendable away from a top portion of the body for a flight mode. The multiple of wings can be selectively retractable toward the top portion of the body for a roadable mode. | ||||||
| 71 | Stackable wing for an aerocar | US14194795 | 2014-03-02 | US09216814B2 | 2015-12-22 | Umesh N. Gandhi; Robert W. Roe |
| A wing includes an upper surface that forms a generally fixed shape and a lower surface adjacent to the upper surface. The lower surface is morphable between a stowed shape and a deployed shape. A method of morphing a wing includes morphing a lower surface between a stowed shape and a deployed shape. The lower surface curves toward the upper surface in the stowed shape and curves away from the upper surface in the deployed shape. | ||||||
| 72 | Vertical takeoff and landing roadable vehicle | US13545150 | 2012-07-10 | US09139299B2 | 2015-09-22 | Gert Magnus Lundgren |
| A roadable vehicle with a single nacelle assembly that contains a pair of inline counter-rotating propellers. Two inline counter-rotating engines are directly connected to the propellers. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the nacelle assembly permits thrust to be directed forward to back and left to right to control the vehicle position in the horizontal plane, when hovering. Varying the relative engine speeds controls yaw. The roadable vehicle is adaptable as an unmanned vehicle. The foldable wings equipped with automotive type wheels provide for travel off-road as well as on the highway. | ||||||
| 73 | Discoidal Seaplane | US14312447 | 2014-06-23 | US20150001334A1 | 2015-01-01 | Wendell Olson |
| A flying vehicle, comprising a discoidal secondary wing and two airfoil primary wings. The airfoil primary wings provide out-of-surface-effect lift that acts as the main lift force for the vehicle. The discoidal secondary wing provides lift via the surface effect, stabilizes the vehicle, provides a mounting surface for solar panels, and acts as a pontoon for water landings. The vehicle can also include a retractable toroidal or round balloon to provide additional lift. The vehicle is fully scalable, from children's toys to passenger vehicles. | ||||||
| 74 | VERTICAL TAKEOFF AND LANDING ROADABLE VEHICLE | US13545150 | 2012-07-10 | US20140014764A1 | 2014-01-16 | Gert Magnus Lundgren |
| A roadable vehicle with a single nacelle assembly that contains a pair of inline counter-rotating propellers. Two inline counter-rotating engines are directly connected to the propellers. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the nacelle assembly permits thrust to be directed forward to back and left to right to control the vehicle position in the horizontal plane, when hovering. Varying the relative engine speeds controls yaw. The roadable vehicle is adaptable as an unmanned vehicle. The foldable wings equipped with automotive type wheels provide for travel off-road as well as on the highway. | ||||||
| 75 | Personal Aircraft | US13764697 | 2013-02-11 | US20130214086A1 | 2013-08-22 | Ilan Kroo |
| A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | ||||||
| 76 | Discoidal Seaplane | US13460851 | 2012-05-01 | US20120292429A1 | 2012-11-22 | Wendell Olson |
| A flying vehicle, comprising a discoidal secondary wing and two airfoil primary wings. The airfoil primary wings provide out-of-surface-effect lift that acts as the main lift force for the vehicle. The discoidal secondary wing provides lift via the surface effect, stabilizes the vehicle, provides a mounting surface for solar panels, and acts as a pontoon for water landings. The vehicle can also include a retractable toroidal or round balloon to provide additional lift. The vehicle is fully scalable, from children's toys to passenger vehicles. | ||||||
| 77 | Variable stroke rear landing gear strut | US12550452 | 2009-08-31 | US08276843B2 | 2012-10-02 | Richard Wilby |
| A rear landing gear for an aircraft includes a strut configured to have a variable height at a lowered position. The strut is variable between a maximum height at which the aircraft has a substantially horizontal trim and a minimum height at which the aircraft has a nose-up trim, and includes a barrel and a shock absorber. The shock absorber bears a set of wheels and is slidably mounted in a passage of the barrel, the passage defining a variable-volume internal fluidic chamber. A source of fluidic power connects to the variable-volume internal chamber via a controllable shut-off member and is configured to fill or empty the variable-volume internal chamber with fluid, varying the height of the strut between the maximum height and the minimum height. | ||||||
| 78 | Double fuselage aircraft | US12252088 | 2008-10-15 | US08157204B2 | 2012-04-17 | Richard Wilby |
| Symmetric external parts of a front lower aircraft wing sweep forward such that lift generated by a rear upper wing is greater than lift generated by the front lower wing. The rear upper wing is in direct contact with rear upper parts of fuselages. A propulsion system of the aircraft has a turboprop engine and is carried by an internal part of the rear upper wing, with the propulsion system lying in a longitudinal mid-plane. | ||||||
| 79 | Personal Aircraft | US13229717 | 2011-09-10 | US20120012692A1 | 2012-01-19 | Ilan Kroo |
| A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight. | ||||||
| 80 | THREE WING, SIX-TILT PROPULSION UNIT, VTOL AIRCRAFT | US13230173 | 2011-09-12 | US20110315809A1 | 2011-12-29 | Richard David OLIVER |
| A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles. | ||||||
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