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1.发明授权公开(公告)号：US11613370B2
公开(公告)日：2023-03-28
申请号：US17388262
申请日：2021-07-29
申请人： JOBY AERO, INC.
发明人： Joeben Bevirt , Alex Stoll
摘要： An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The wing mounted rotor assemblies may have split nacelles, wherein a forward portion of the nacelle deploys along with the electric motor and the propeller.
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公开(公告)号：US11603194B2
公开(公告)日：2023-03-14
申请号：US17706445
申请日：2022-03-28
IPC分类号： B64C11/28 , B64C29/00 , B64D35/00 , B64C27/50 , B64C39/02 , B64C29/02 , B64C39/06 , B64D1/08 , B64D25/12
摘要： An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.
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3.发明授权公开(公告)号：US11597509B1
公开(公告)日：2023-03-07
申请号：US17453194
申请日：2021-11-02
摘要： An aircraft that closely integrates thrust and aerodynamics to achieve VTOL flight, forward flight, and smooth transitions from VTOL to forward flight. The invention combines a Box wing, Ducted Rotors and movable Flaperons for VTOL and sustained forward flight of an aircraft. In forward flight, the concept uses a plurality of fixed Ducted Rotors to not only provide thrust, but also enhance dynamic lift and controllability by interacting closely with the two fixed primary lifting bodies of each ducted wing section. In VTOL flight and transitioning to forward flight, the Ducted Rotors direct air through movable Flaperons attached to the trailing end of the ducted wings, providing smooth power, controllability, and aircraft orientation throughout transition. Throughout all phases of flight, differential actuation of Ducted Rotors and Flaperons provide control.
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公开(公告)号：US11485490B2
公开(公告)日：2022-11-01
申请号：US16833311
申请日：2020-03-27
发明人： Oleg Petrov , Konstantin Kisly , Yevgeniy Dukhovny , Pavel Markin
摘要： A vertical take-off and landing (VTOL) aircraft, that may be incorporated into a personal automobile, comprises a rectangular wing including an upper wing section having a right upper wing side and a left upper wing side, a lower wing section having a right lower wing side and left lower wing side, a right vertical wing section coupled to the right upper wing side and to the right lower wing side, and a left vertical wing section coupled to the left upper wing side and to the left lower wing side, the upper wing section having an upper wing cross section with a first asymmetrical airfoil shape configured to cause lift when in forward flight, the lower wing section having a lower wing cross section with a second asymmetrical airfoil shape for causing lift when in forward flight, each of the right vertical wing section and the left vertical wing section having a vertical wing cross section with a symmetrical shape to cause lateral stability when in forward flight; two elevons on at least one of the upper wing section and the lower wing section; at least one rudder on each of the right vertical wing section and the left vertical wing section; a support frame coupled to the rectangular wing; and a propulsion system coupled to the support frame.
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公开(公告)号：US20220204174A1
公开(公告)日：2022-06-30
申请号：US17694567
申请日：2022-03-14
申请人： Joby Aero, Inc.
发明人： JoeBen Bevirt , Alex Stoll
摘要： An aerial vehicle of a box wing design adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.
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公开(公告)号：US20220161927A1
公开(公告)日：2022-05-26
申请号：US17441007
申请日：2020-03-19
发明人： Andrew Dudley Moore , John Wilson
摘要： 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 each of the left side wings (22, 32) being connected in a box wing configuration; wherein each wing (20, 22, 30, 32) has a fixed leading edge (100) and at least one moveable trailing control surface (110), further wherein each wing (20, 22, 30, 32) has at least one motor pod (195), the motor pod (195) being pivotally mounted to an underside of the fixed leading edge (100), and fixedly secured to the trailing control surface (110).
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7.发明申请公开(公告)号：US20220144440A1
公开(公告)日：2022-05-12
申请号：US17388262
申请日：2021-07-29
申请人： JOBY AERO, INC.
发明人： JOEBEN BEVIRT , ALEX STOLL
摘要： An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The wing mounted rotor assemblies may have split nacelles, wherein a forward portion of the nacelle deploys along with the electric motor and the propeller.
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公开(公告)号：US11312487B2
公开(公告)日：2022-04-26
申请号：US16840292
申请日：2020-04-03
IPC分类号： B64C29/02 , B64C29/00 , B64C11/28 , B64D35/00 , B64C27/50 , B64C39/02 , B64C39/06 , B64D1/08 , B64D25/12
摘要： An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.
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公开(公告)号：US20220111957A1
公开(公告)日：2022-04-14
申请号：US17475280
申请日：2021-09-14
申请人： JETOPTERA, INC.
发明人： Andrei Evulet
摘要： A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tad conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.
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公开(公告)号：US20210206485A1
公开(公告)日：2021-07-08
申请号：US17135862
申请日：2020-12-28
申请人： Joby Aero, Inc.
发明人： JoeBen Bevirt , Alex Stoll
IPC分类号： B64C29/00 , B64C7/02 , B64D27/24 , B64C27/30 , B64C27/28 , B64C11/28 , B64C27/08 , B64C39/06
摘要： An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight.
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