公开(公告)号：US20180154270A1

公开(公告)日：2018-06-07

申请号：US15874792

申请日：2018-01-18

Applicant: University of Kansas

Inventor： Ronald M. Barrett ,  Robert B. Honea ,  Richard B. Bramlette

IPC: A63H27/00 ,  A63H33/00 ,  B64C25/06 ,  B64C29/02 ,  B64C39/02 ,  B64D27/02

CPC classification number: A63H27/12 ,  A63H27/02 ,  A63H33/003 ,  B64C25/06 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2203/00 ,  B64D27/02

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

公开(公告)号：US20180086462A1

公开(公告)日：2018-03-29

申请号：US15713169

申请日：2017-09-22

Applicant: AIRBUS DEFENCE AND SPACE GMBH

Inventor： Werner HOLZER

IPC: B64D1/22 ,  B64C29/02 ,  B64C25/52

CPC classification number: B64D1/22 ,  B64C17/02 ,  B64C17/04 ,  B64C25/52 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/18 ,  B64D9/00

Abstract: A fixed-wing aircraft includes a load element, which is coupled to a fuselage of the fixed-wing aircraft; and an actuator device, by which a position of the load element can be varied in relation to the fuselage during a flight of the fixed-wing aircraft in order to displace a center of gravity of the fixed-wing aircraft by the load element.

公开(公告)号：US20180072422A1

公开(公告)日：2018-03-15

申请号：US15389326

申请日：2016-12-22

Applicant: X Development LLC

Inventor： Trevor Shannon ,  Andre Prager

IPC: B64D1/22 ,  B64C39/02 ,  B66D1/60 ,  B66D1/12

CPC classification number: B64D1/22 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B66D1/12 ,  B66D1/60 ,  B66D2700/0141

Abstract: Described herein are methods and systems for picking up, transporting, and lowering a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the winch system may include a motor for winding and unwinding the tether from a spool, and the UAV's control system may operate the motor to lower the tether toward the ground so a payload may be attached to the tether. The control system may monitor an electric current supplied to the motor to determine whether the payload has been attached to the tether. In another example, when lowering a payload, the control system may monitor the motor current to determine that the payload has reached the ground and responsively operate the motor to detach the payload from the tether. The control system may then monitor the motor current to determine whether the payload has detached from the tether.

公开(公告)号：US09878257B2

公开(公告)日：2018-01-30

申请号：US14734864

申请日：2015-06-09

Applicant: University of Kansas

Inventor： Ronald M. Barrett ,  Robert B. Honea ,  Richard B. Bramlette

IPC: A63H27/00 ,  B64C25/06 ,  B64D27/02 ,  A63H33/00 ,  B64C29/02 ,  B64C39/02

CPC classification number: A63H27/12 ,  A63H27/02 ,  A63H33/003 ,  B64C25/06 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2203/00 ,  B64D27/02

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

公开(公告)号：US20180002003A1

公开(公告)日：2018-01-04

申请号：US15612671

申请日：2017-06-02

Applicant: AeroVironment, Inc.

Inventor： Henry Thome Won ,  Quentin Lindsey

IPC: B64C27/26 ,  B64C39/02 ,  B64C29/02

CPC classification number: B64C27/26 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/06

Abstract: Systems, devices, and methods for an aircraft having a fuselage (110); a wing (120) extending from both sides of the fuselage; a first pair of motors (132b, 133b) disposed at a first end of the wing; and a second pair of motors (142b, 143b) disposed at a second end of the wing; where each motor is angled (381, 382, 391, 392) to provide a component of thrust by a propeller (134, 135, 144, 145) attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

公开(公告)号：US09849983B2

公开(公告)日：2017-12-26

申请号：US15535431

申请日：2015-12-04

Applicant: ALFRED-WEGENER-INSTITUT

Inventor： Andreas Herber ,  Dirk Kalmbach ,  Ruediger Gerdes ,  Hans-Joerg Bayer

IPC: B64D3/02 ,  B64C39/02 ,  B64C3/16 ,  F41J9/10 ,  B64C1/00

CPC classification number: B64D3/02 ,  B64C3/16 ,  B64C39/022 ,  B64C2001/0045 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/206 ,  F41J9/10

Abstract: An aerodynamically shaped, active towed body includes a fuselage curved along its vertical and horizontal longitudinal plane. The fuselage has a unit chamber and a load chamber. A transverse plane of the fuselage is triangular, two upper corners being located on an upper face of the fuselage and a lower corner being located on a lower face of the fuselage. Each of two wings is subdivided into a small and a large segment. The small segment points downwards and is attached to the fuselage in a region of the lower corner and the large segment points upwards and is attached to the small segment. Each of the small segments comprise an additional load chamber. The towed body further includes a tail fin, rudders that are each adjustable by the control device and a coupling for the towing cable.

公开(公告)号：US20170364093A1

公开(公告)日：2017-12-21

申请号：US15628541

申请日：2017-06-20

Applicant: PARROT DRONES

Inventor： Marc Mari Mari ,  Gauthier Lavagen ,  Yoni Benatar

IPC: G05D1/08 ,  G05D1/02 ,  B64C13/16 ,  B64C27/26

CPC classification number: G05D1/0825 ,  B64C13/16 ,  B64C27/26 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/14 ,  B64C2201/165 ,  G05D1/0202 ,  G05D1/0808 ,  G05D1/085 ,  G05D1/0858

Abstract: A method for dynamically controlling the attitude of a rotary-wing drone. The method includes dynamically controlling the attitude of the drone when the drone is flying using lift of each of four wings of the drone, by controlling the attitude of the drone by sending differentiated commands to one or more propulsion units of the drone so as to rotate the drone about a roll axis and/or pitch axis and/or heading axis of the drone from a current angular position to a final angular position, the axes being defined in the reference point of the drone.

公开(公告)号：US20170349272A1

公开(公告)日：2017-12-07

申请号：US15175803

申请日：2016-06-07

Applicant: EZNOV

Inventor： Eric LAURENT ,  Thomas LEGRAND

IPC: B64C27/28 ,  B64C29/00 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The tricopter type rotary-wing drone includes three arms connected to a frame. Each of the free ends of the arms support a rotor with an axis perpendicular to the respective free end. The rotor is driven in rotation by a motor connected to power supply. The arms are pivotally mounted on the frame. Two arms automatically drive the rotor supported by their respective free ends into a position in which its axis forms an angle between −30° and +150° with the plane of the frame. The third arm automatically pivots, if necessary, into a position in which its free end is spaced apart from the apex being considered of the triangle by an angle between −60° and +60°.

公开(公告)号：US09815563B2

公开(公告)日：2017-11-14

申请号：US15090571

申请日：2016-04-04

Applicant: W. Morrison Consulting Group, Inc.

Inventor： William M. Yates ,  Robert Ussery ,  Byron Young

IPC: B64D39/00 ,  B64D5/00 ,  B64D27/24 ,  B64C39/02

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/187 ,  B64D5/00 ,  B64D27/24

Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of unmanned aerial vehicle (UAV) packs flying independent of and in proximity to the electric aircraft.

公开(公告)号：US20170320570A1

公开(公告)日：2017-11-09

申请号：US15168842

申请日：2016-05-31

Applicant: David Horn

Inventor： David Horn

IPC: B64C39/02 ,  G08G5/00 ,  B64C29/02 ,  B64D47/08

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D47/08 ,  B64D2211/00 ,  G08G5/0026

Abstract: 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.