公开(公告)号：US20230174232A1

公开(公告)日：2023-06-08

申请号：US17541944

申请日：2021-12-03

Applicant: WING Aviation LLC

Inventor： Evan Twyford ,  Ivan Qiu ,  James Juma

IPC: B64C39/02 ,  B64C29/00 ,  B64D13/00 ,  B64C1/26 ,  B64C5/02 ,  B64C11/00 ,  B64F1/36 ,  B60L53/00 ,  B64C1/38

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64D13/006 ,  B64C1/26 ,  B64C5/02 ,  B64C11/00 ,  B64F1/362 ,  B60L53/00 ,  B64C1/38 ,  B60L2200/10 ,  B64C2201/021 ,  B64C2201/108 ,  B64C2201/165 ,  H05K7/20509

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, electronics disposed with the fuselage, a heat sink, and a solar shield. The heat sink is thermally connected to the electronics and includes a cooling plate disposed on or extends through an exterior surface of the fuselage. The cooling plate is exposed to an external environment of the UAV to conduct heat from the electronics to the external environment via convection. The solar shield extends over the cooling plate and defines an air scoop within which the cooling plate is disposed. The air scoop directs airflow from the external environment across the cooling plate. The solar shield shades the cooling plate from solar radiation to prevent or reduce solar heating of the cooling plate.

公开(公告)号：US20190185155A1

公开(公告)日：2019-06-20

申请号：US16280021

申请日：2019-02-19

Applicant: DeLorean Aerospace, LLC

Inventor： Paul J. DeLorean

IPC: B64C29/00 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64D27/24 ,  B64C27/32

CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/028 ,  B64D27/24 ,  Y02T50/12 ,  Y02T50/64

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

公开(公告)号：US20180305019A1

公开(公告)日：2018-10-25

申请号：US15767650

申请日：2016-10-21

Applicant: Danielson Aircraft Systems

Inventor： Frédéric HUBSCHWERLEN

IPC: B64C39/06 ,  B64C21/02 ,  B64C23/06

CPC classification number: B64C39/068 ,  B64C21/02 ,  B64C23/076 ,  B64C2201/021 ,  B64C2230/08 ,  B64C2230/20 ,  Y02T50/164 ,  Y02T50/166

Abstract: The invention relates to an aircraft having at least one wing (5) including, at each end thereof, a fin (6) forming an angle of between 0° and 45° relative to the vertical. According to the invention, each fin (6) has a leading edge (7) that includes at least one slot (8) provided along said leading edge (7) and oriented so as to cause an air flow to flow via said leading edge (7) from an outer surface (6a) of the fin (6) to an inner surface (6b).

公开(公告)号：US20180305011A1

公开(公告)日：2018-10-25

申请号：US15768201

申请日：2016-10-28

Applicant: BAE Systems plc

Inventor： David Julian Wright ,  Nicholas Giacomo Robert Colosimo ,  Clyde Warsop

IPC: B64C39/02 ,  B64C29/00

CPC classification number: B64C39/024 ,  A63H27/00 ,  B64C29/00 ,  B64C29/0033 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/182 ,  B64C2201/201

Abstract: A rotary-wing air vehicle comprising a main body (12) and at least two rotor devices (16a, 16b) arranged and configured to generate propulsion and thrust, in use, to lift and propel said air vehicle, said rotor devices (16a, 16b) being arranged and configured relative to said main body (12) such that the blades thereof do not cross through a central vertical axis of said main body (12) defining the centre of mass thereof, wherein said main body (12) is provided with an aperture (100) that extends therethrough to define a channel about said central vertical axis.

公开(公告)号：US20180290742A1

公开(公告)日：2018-10-11

申请号：US15972448

申请日：2018-05-07

Applicant: Bell Helicopter Textron Inc.

Inventor： Paul K. Oldroyd ,  John Richard McCullough

IPC: B64C29/00 ,  B64C1/32 ,  B64C27/08 ,  B64C39/02 ,  B64D25/12 ,  B64D27/24

CPC classification number: B64C29/0033 ,  B64C1/32 ,  B64C27/08 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/108 ,  B64D25/12 ,  B64D27/24 ,  B64D27/26

Abstract: A propulsion assembly for an aircraft includes a housing having a gimbal coupled thereto that is operable to tilt about first and second axes. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades. The rotor assembly is rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector with a direction. The first axis of the gimbal is orthogonal to the second axis of the gimbal. Actuation of the gimbal tilts the propulsion system relative to the housing to change the rotational plane of the rotor assembly relative to the housing, thereby controlling the direction of the thrust vector within a thrust vector cone.

公开(公告)号：US20180222580A1

公开(公告)日：2018-08-09

申请号：US15456173

申请日：2017-03-10

Applicant: DeLorean Aerospace, LLC

Inventor： Paul J. DeLorean

IPC: B64C29/00 ,  B64D27/24 ,  B64C39/12 ,  B64C39/04 ,  B64C27/32 ,  B64C39/10

CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/028 ,  B64D27/24 ,  Y02T50/12 ,  Y02T50/64

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

公开(公告)号：US20180186464A1

公开(公告)日：2018-07-05

申请号：US15395996

申请日：2016-12-30

Applicant: X Development LLC

Inventor： Adam Woodworth ,  Greg Vulikh ,  John FitzSimons

IPC: B64D31/06 ,  B64C39/02 ,  B64D27/24 ,  H02P5/00

CPC classification number: H02P5/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64D2221/00 ,  H02P6/16

Abstract: An example unmanned aerial vehicle includes a power source, a processor module having one or more processors, and a plurality of boom arms, each boom arm being couplable to a printed circuit board (PCB) and a plurality of propellers. In the example UAV, a PCB of each boom arm includes a power hub electrically couplable to the power source and to corresponding propellers of the boom arm, and a signal hub electrically couplable to at least one processor of the processor module and to the corresponding propellers. Further, in the example UAV, the power hub of each PCB is configured to transfer power from the power source to the corresponding propellers, and wherein the signal hub of each PCB is configured to transfer signals from the processor module to the corresponding propellers such that the processor module controls the plurality of propellers.

公开(公告)号：US10005541B2

公开(公告)日：2018-06-26

申请号：US15052699

申请日：2016-02-24

Applicant: Karem Aircraft, Inc.

Inventor： Abe Karem ,  Benjamin Tigner

IPC: G05D1/00 ,  B64C39/02 ,  B64F5/00 ,  B64C3/42 ,  B64D27/24 ,  B64C3/16 ,  B64C11/28 ,  H02S10/40 ,  H02S40/38 ,  B64F5/10

CPC classification number: B64C3/42 ,  B64C3/16 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/165 ,  B64D27/24 ,  B64D2211/00 ,  B64F5/10 ,  G05D1/0011 ,  G05D1/0088 ,  H02S10/40 ,  H02S20/30 ,  H02S40/38 ,  Y02T50/12 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network.

公开(公告)号：US20180170517A1

公开(公告)日：2018-06-21

申请号：US15385573

申请日：2016-12-20

Applicant: Bio-Cellular Design Aeronautics, Inc.

Inventor： Jayant Ratti

IPC: B64C3/54 ,  B64C3/10 ,  B64C3/56 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64C3/546 ,  B64C29/0025 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/102 ,  B64D2041/005

Abstract: A hybrid wing autonomous aircraft having, an airframe, at least one hybrid wing member having an airframe end and an extended end, and having leading and trailing edges and a plurality of control structures, the airframe end coupled to the airframe, and the extended end further configured with a wing extension device, the wing extension device configured to extend a supplemental lifting surface from the extended end, an airframe actuator configured to cause the extension end of the hybrid wing member to move from a first position relative to the airframe to a second position relative to the airframe, wherein the second position is greater in distance from the airframe than the first position.

公开(公告)号：US20180155021A1

公开(公告)日：2018-06-07

申请号：US15827776

申请日：2017-11-30

Applicant: U.S.A. AS REPRESENTED BY THE ADMINISTRATOR OF NASA

Inventor： Michael D. Patterson ,  Jesse R. Quinlan ,  William J. Fredericks

IPC: B64C37/02 ,  B64C39/02 ,  B64C29/00 ,  B64C3/00

CPC classification number: B64C37/02 ,  B64C3/00 ,  B64C9/00 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2211/00 ,  B64D37/04

Abstract: A modular Unmanned Aerial System (UAS) includes an Unmanned Aerial Vehicle (UAV) parent module and UAV child modules. A main wing extends from a respective fuselage of the modules. The UAS includes docking mechanisms coupled to wingtips of the main wings. The child modules dock with the wingtips of the parent or an adjacent child module. Docking forms a linked-flight configuration, with undocking and separation from the parent or adjacent child module achieving an independent-flight configuration. The modules have booms arranged transverse to the main wings and parallel to the longitudinal axis, as well as front and rear rotors/propellers. The front and rear propellers have axes of rotation that are normal to a plane of the longitudinal axis in a vertical takeoff and landing (VTOL) configuration, with the axis of rotation of the rear propellers parallel to the longitudinal axis in a forward-flight configuration.