公开(公告)号：US20180251212A1

公开(公告)日：2018-09-06

申请号：US15759811

申请日：2016-09-06

Applicant: PRODRONE CO., LTD.

Inventor： Kiyokazu SUGAKI ,  Kazuo ICHIHARA

IPC: B64C25/34 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64C25/34 ,  B64C27/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/162

Abstract: To provide an unmanned aerial vehicle that can allow its airframe to approach a structure surface safely and is able to move on a surface of the structure, while keeping a constant clearance between the structure surface and the airframe. This is solved by an manned aerial vehicle including one or a plurality of rotors and a plurality of rotating bodies having one or more driving sources, wherein at least a part of each of the rotating bodies in their rotational radius direction extends forth on an air intake side of the rotors relative to a position of rotational planes of the rotors, and negative pressure produced on the air intake side of the rotors causes the airframe to adhere by suction to a structure surface, and in this state, by driving the plurality of rotating bodies, the vehicle is enabled to travel on the surface.

公开(公告)号：US20180237135A1

公开(公告)日：2018-08-23

申请号：US15896894

申请日：2018-02-14

Applicant: MARTIN UAV, LLC

Inventor： Stephen MORRIS

IPC: B64C29/02 ,  B64C11/00 ,  G05D1/08 ,  G05D1/10 ,  B64C9/00

CPC classification number: B64C29/02 ,  B64C11/001 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162 ,  G05D1/0858 ,  G05D1/102

Abstract: 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.

公开(公告)号：US20180178910A1

公开(公告)日：2018-06-28

申请号：US15852444

申请日：2017-12-22

Applicant: Korea Advanced Institute of Science and Technology

Inventor： Dongsoo HAR ,  Sang Min LEE

IPC: B64C29/00 ,  B64D27/24 ,  B64D41/00

CPC classification number: B64D27/24 ,  B64C3/385 ,  B64C5/02 ,  B64C11/001 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  B64D41/007 ,  F15B15/06 ,  F16H19/001 ,  F16H19/04 ,  F16H21/44 ,  Y02T50/62

Abstract: An aerial vehicle includes: a main body; two main wings arranged to the main body; two main wing tilting control units coupled to the main wings to control the main wings to tilt independently; two main propulsion units arranged to the main wings; tail wings arranged to a rear side of the main body; a rudder arranged to the tail wing; a rudder tilting control unit to control the rudder to tilt; a tail propulsion unit arranged to the rear side of the main body; a tail tilting control unit to control the tail propulsion unit to tilt; a power unit to provide power to the main and tail propulsion units; and a position control unit to control the main wing tilting control units, the main propulsion units, the rudder tilting control unit, the tail propulsion unit, the tail tilting control unit to adjust position of the aerial vehicle.

公开(公告)号：US20180147429A1

公开(公告)日：2018-05-31

申请号：US15576904

申请日：2016-05-26

Applicant: Gi Yeon WON ,  Kyung Wha KIM

Inventor： Gi Yeon WON ,  Kyung Wha KIM

IPC: A62C3/02 ,  A62C31/02 ,  A62C31/28 ,  A62C27/00 ,  A62C37/40 ,  B64C39/02 ,  B64D1/18 ,  B64D1/02 ,  B64C37/00 ,  B60F5/02 ,  B64C25/40

CPC classification number: A62C3/0242 ,  A62C3/025 ,  A62C27/00 ,  A62C31/02 ,  A62C31/28 ,  A62C37/40 ,  B60F5/02 ,  B64C25/405 ,  B64C37/00 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/02 ,  B64D1/18

Abstract: The present invention relates to a fire extinguishing firefighting drone which, in case of a fire in a house, a structure, a building, or the like, can be rapidly introduced and extinguish a fire in an early stage of the fire, and can be remotely operated in an unmanned manner through connection with a central control system. The fire extinguishing firefighting drone includes a flight unit configured to include propeller units, a disaster prevention turret unit configured to spray a fire-extinguishing chemical, a plurality of movement units configured to move a body unit, and a disaster prevention means unit configured to be provided with items adapted to spray a fire-extinguishing chemical, to launch a fire-extinguishing bomb, or to save lives.

公开(公告)号：US09975633B1

公开(公告)日：2018-05-22

申请号：US15151287

申请日：2016-05-10

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： Stephen D. Johnson ,  Barnaby S. Wainfan

IPC: B64C39/02 ,  B64C3/00 ,  B64C7/02 ,  B64C11/00

CPC classification number: B64C39/024 ,  B64C3/00 ,  B64C7/02 ,  B64C11/001 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/20

Abstract: A ducted fan UAV that can be collapsed into a stowed configuration and then deployed for flight by, for example, inflating the duct to a deployed configuration. The UAV includes a plurality of rotor blades, a plurality of struts and a plurality of control vanes each being pivotally mounted to a center body by a hinge so that the rotor blades, the struts and the control vanes can be folded into the stowed configuration to be substantially parallel to the center body and be unfolded into the deployed configuration to be substantially perpendicular to the center body. The UAV also includes a pressurization system providing a pressurant to a chamber within the duct so as to inflate the duct and cause the struts, the rotor blades and the control vanes to move from the stowed configuration to the deployed configuration.

公开(公告)号：US20180099742A1

公开(公告)日：2018-04-12

申请号：US15837614

申请日：2017-12-11

Applicant: Coriolis Games Corporation

Inventor： Jacob Apkarian

IPC: B64C29/00 ,  B64F5/10 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C27/20 ,  B64C27/52 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2211/00 ,  B64F5/10

Abstract: An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations.

公开(公告)号：US20180072414A1

公开(公告)日：2018-03-15

申请号：US15698516

申请日：2017-09-07

Applicant: Wal-Mart Stores, Inc.

Inventor： Robert L. Cantrell ,  John P. Thompson ,  David C. Winkle ,  Michael D. Atchley ,  Donald R. High ,  Todd D. Mattingly ,  John J. O'Brien ,  John F. Simon

IPC: B64C39/02 ,  B64C3/42 ,  B64C33/02 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C3/42 ,  B64C3/56 ,  B64C33/02 ,  B64C2201/021 ,  B64C2201/022 ,  B64C2201/025 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/14 ,  B64C2201/162

Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: retrieve a task profile for a task assigned to the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the task profile and the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.

公开(公告)号：US09902493B2

公开(公告)日：2018-02-27

申请号：US15550392

申请日：2016-02-08

Applicant: HUTCHINSON

Inventor： Jean-Michel Simon ,  Christophe Dominiak ,  Sebastien Andre

IPC: B64C27/08 ,  B64C29/00 ,  B64D35/06 ,  B64C39/02

CPC classification number: B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64D35/06 ,  B64D35/08

Abstract: Disclosed is an aerodyne including a supporting structure, to which are connected: at least one supporting axial blower, attached to the supporting structure; at least one main engine driving the supporting blower; at least three attitude blowers controlling roll and pitch, each attitude blower having an electrical motor and being attached, respectively, to one of the elongate arms that are distributed in a laterally, outwardly projecting manner around the supporting structure, to which each arm is connected by an inner end portion, the axis of rotation of each attitude blower being attached relative to the supporting structure, and all the attitude blowers being located outside the space centrally occupied by the supporting blower; at least one battery for supplying power to the electrical motors of the attitude blowers; a landing gear attached under the supporting structure; and a nacelle for holding the battery and a payload.

公开(公告)号：US20170259918A1

公开(公告)日：2017-09-14

申请号：US15066460

申请日：2016-03-10

Applicant: NICHOLAS K. CHRISTENSEN

Inventor： NICHOLAS K. CHRISTENSEN

IPC: B64D1/02 ,  B64C31/02 ,  B64C11/00 ,  B64C39/02

CPC classification number: B64C31/02 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/082 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/206

Abstract: One example includes a dual-aircraft system. The system includes a glider aircraft configured to perform at least one mission objective in a gliding-flight mode during a mission objective stage. The system also includes an unmanned singlecopter configured to couple to the glider aircraft via a mechanical linkage to provide propulsion for the glider aircraft during a takeoff and delivery stage. The unmanned singlecopter can be further configured to decouple from the glider aircraft during a detach stage in response to achieving at least one of a predetermined altitude and a predetermined geographic location to provide the gliding-flight mode associated with the glider aircraft, such that the glider aircraft subsequently enters the mission objective stage.

公开(公告)号：US20170240275A1

公开(公告)日：2017-08-24

申请号：US15456450

申请日：2017-03-10

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

IPC: B64C29/04 ,  B64C39/02 ,  B64C11/00 ,  B64C9/00 ,  B64C39/12 ,  B64D27/20

CPC classification number: B64C29/04 ,  B64C9/38 ,  B64C11/001 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/162 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0273 ,  Y02T50/166 ,  Y02T50/44

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, 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 is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.