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：US09988148B2

公开(公告)日：2018-06-05

申请号：US14795505

申请日：2015-07-09

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64C29/02 ,  B64D27/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64D27/02

Abstract: A vehicle is provided and includes a wing having opposite surfaces and opposite sides and first and second engines disposed to drive wing movement and being respectively supported asymmetrically on the opposite surfaces and at the opposite sides of the wing.

公开(公告)号：US20180134412A1

公开(公告)日：2018-05-17

申请号：US15566603

申请日：2016-04-29

Applicant: Chung Kiak POH ,  Chung How POH

Inventor： Chung Kiak POH ,  Chung How POH

IPC: B64F1/12 ,  B64C39/02 ,  H02S20/30

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/02 ,  B64F1/222 ,  H02S20/30

Abstract: The present invention generally relates to a system and method of a docking system (1) for fixed wing unmanned aerial vehicle, or non-fixed wing unmanned aerial vehicle (2) such as rotorcraft, or combination thereof, comprising at least a docking and/or launching pad capable of being arranged in an array or staggered manner; said pad has a surface (6) for said vehicle docking and launching, said docking and launching surface (6) comprising moveable pads (31) which include electromagnets that can be energized to capture a docking vehicle (2); and another energy harvesting surface (4) has photovoltaic panel to harness solar energy to generate electricity or hydrogen fuel for a variety of on-board applications such as to charge said vehicle (2) and to power the docking system and providing a safe stowage and protected storage for the said vehicle (2).

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：US09902489B2

公开(公告)日：2018-02-27

申请号：US14184542

申请日：2014-02-19

Applicant: AeroVironment, Inc.

Inventor： Christopher Eugene Fisher ,  Steven Bradley Chambers ,  Pavil Belik ,  Austin Craig Gunder ,  John Peter Zwaan

IPC: B64C9/00 ,  B64C5/02 ,  B64C39/02 ,  B64C3/10 ,  B64C5/06 ,  B64C39/00 ,  B64C39/12

CPC classification number: B64C5/02 ,  B64C3/10 ,  B64C5/06 ,  B64C9/00 ,  B64C39/00 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/22

Abstract: An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

公开(公告)号：US09902487B2

公开(公告)日：2018-02-27

申请号：US15388478

申请日：2016-12-22

Applicant: Area- I Inc.

Inventor： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC: B64C3/40 ,  B64C3/54 ,  B64C39/02 ,  B64C3/56 ,  B64C13/30

CPC classification number: B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2211/00 ,  Y02T50/14 ,  Y02T50/44

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

公开(公告)号：US20180043984A1

公开(公告)日：2018-02-15

申请号：US15233927

申请日：2016-08-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Frank Bradley Stamps

IPC: B64C3/10 ,  B64C9/00 ,  B64C39/02

CPC classification number: B64C3/10 ,  B64C9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/108 ,  B64C2201/126

Abstract: An inflight connection system for aircraft having at least one wing with a wingtip includes, for each aircraft, a primary connector selectively extendable from the wingtip, an alignment connector selectively extendable from the wingtip and a male and female connector assembly disposed proximate the wingtip. The primary connectors extend a greater distance from the wingtips than the alignment connectors such that the primary connectors form a first connection between the aircraft when the aircraft are flying in a connection pattern. Thereafter, retraction of the primary connectors reduces wingtip separation of the aircraft such that the alignment connectors form a second connection between the aircraft establishing coarse alignment therebetween. Thereafter, retraction of the primary and alignment connectors further reduces wingtip separation of the aircraft such that the male and female connector assemblies form a third connection between the aircraft establishing fine alignment therebetween.

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：US09862503B2

公开(公告)日：2018-01-09

申请号：US14028029

申请日：2013-09-16

Applicant: Jose Cruz Chavez, Jr.

Inventor： Jose Cruz Chavez, Jr.

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/182

Abstract: A retrieval device for an unmanned aircraft. The retrieval device may include a frame that supports a flexible material. The flexible material may form a receptacle portion shaped to receive the unmanned aircraft. The flexible material may absorb at least a portion of the energy exerted by the aircraft landing within the receptacle portion. Wheels may be connected to the frame to further control and absorb energy from the landing.