公开(公告)号：US20170372259A1

公开(公告)日：2017-12-28

申请号：US15195607

申请日：2016-06-28

Applicant: X Development LLC

Inventor： Jonathan Lesser ,  Michael Bauerly ,  James Ryan Burgess ,  May Cheng ,  Rue Song

IPC: G06Q10/08 ,  B64D1/08 ,  G01C21/16 ,  B64C39/02 ,  G06F3/0484 ,  G06F3/0482

CPC classification number: G06Q10/0832 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/128 ,  B64C2201/141 ,  B64D1/08 ,  B64D47/08 ,  G01C21/165 ,  G06F3/0482 ,  G06F3/0484

Abstract: Embodiments relate to a client-facing application for interacting with a transport service that transports items via unmanned aerial vehicles (UAVs). An example graphic interface may allow a user to order items to specific delivery areas associated with their larger delivery location, and may dynamically provide status updates and other functionality during the process of fulfilling a UAV transport request.

公开(公告)号：US09845153B2

公开(公告)日：2017-12-19

申请号：US15003088

申请日：2016-01-21

Applicant: Lockheed Martin Corporation

Inventor： Stephen M. Sekelsky

IPC: B64C39/02 ,  H02J7/02 ,  G05D1/08 ,  G01R33/032 ,  B60L11/18 ,  G05D1/02 ,  G05D1/10 ,  G01C21/20 ,  G01R1/067 ,  G01R31/02 ,  G01R31/08

CPC classification number: B64C39/024 ,  B60L11/182 ,  B60L11/1837 ,  B60L2200/10 ,  B60L2240/622 ,  B64C2201/021 ,  B64C2201/066 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/146 ,  G01C21/20 ,  G01R1/06705 ,  G01R31/021 ,  G01R31/085 ,  G01R33/032 ,  G05D1/0265 ,  G05D1/101 ,  H02G1/02 ,  H02J7/025 ,  Y02T10/7005 ,  Y02T10/7072 ,  Y02T10/7291 ,  Y02T90/121 ,  Y02T90/122 ,  Y02T90/128 ,  Y02T90/14 ,  Y02T90/16 ,  Y02T90/162

Abstract: A device includes a propulsion unit configured to move the device and a steering unit configured to control the direction of the device. The device also includes a power unit configured to provide power to the propulsion unit and a charging unit configured to use an electric field to provide electrical power to the power unit. The device further includes a first magnetic sensor configured to determine a vector of one or more magnetic fields and a processor communicatively coupled to the propulsion unit, the steering unit, the power unit, and the magnetic sensor. The processor is configured to receive, from the magnetic sensor, a time-varying signal indicative of a magnetic field and determine, based on the time-varying signal, that the magnetic field is associated with an electrical power transmission line. The processor is further configured to cause the steering unit to direct the device toward the electrical power transmission line.

公开(公告)号：US09836065B2

公开(公告)日：2017-12-05

申请号：US15401893

申请日：2017-01-09

Applicant: SUNLIGHT PHOTONICS INC.

Inventor： Sergey V. Frolov ,  John Peter Moussouris ,  Michael Cyrus

IPC: G05D1/10 ,  G05D1/00 ,  G05D1/02 ,  G05D1/06 ,  G08G7/02 ,  G08G5/00 ,  G08G5/04 ,  G08G5/02 ,  G08G5/06 ,  B64C3/56 ,  B64C29/00 ,  B64C37/02 ,  B64C39/02 ,  B64D1/02

CPC classification number: G05D1/104 ,  B64C3/56 ,  B64C29/0016 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/143 ,  B64C2201/145 ,  B64D1/02 ,  G05D1/0022 ,  G05D1/0027 ,  G05D1/005 ,  G05D1/0212 ,  G05D1/0669 ,  G05D1/102 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0017 ,  G08G5/0021 ,  G08G5/003 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025 ,  G08G5/045 ,  G08G7/02 ,  Y02T50/14

Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

公开(公告)号：US20170327214A1

公开(公告)日：2017-11-16

申请号：US15433697

申请日：2017-02-15

Applicant: Hood Technology Corporation

Inventor： Andreas H. von Flotow ,  Corydon C. Roeseler ,  Daniel Pepin Reiss

IPC: B64C27/32 ,  B64D3/00 ,  B64C27/26 ,  B64C39/02

CPC classification number: B64C27/48 ,  B64C25/08 ,  B64C27/001 ,  B64C27/08 ,  B64C27/26 ,  B64C27/32 ,  B64C39/024 ,  B64C2027/003 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/201 ,  B64D1/00 ,  B64D1/02 ,  B64D1/12 ,  B64D3/00 ,  B64D5/00 ,  B64D35/02 ,  B64F1/02 ,  B65D25/10 ,  B65D85/68 ,  B65D2585/687

Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

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.

公开(公告)号：US20170313442A1

公开(公告)日：2017-11-02

申请号：US15583226

申请日：2017-05-01

Applicant: CIRCOR AEROSPACE, INC.

Inventor： Russell S. SIRVIS ,  Christopher R. LOVASCO ,  Juan VASQUEZ ,  David W. GASS ,  Corey C. JORDAN ,  Liron DROR ,  John NELLIKUNNEL ,  Jeffrey HORNING ,  Christopher OLSEN

IPC: B64F1/06 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084

Abstract: An aerial vehicle launcher including a rail having a first end and a longitudinal axis and a piston movable in a passageway formed in the rail, the piston connected to a carriage by at least two elongate flexible members. The carriage having a support device for releasably engaging the aerial vehicle. Upon the carriage and the aerial vehicle approaching one end of the rail, the support device controllably disengaging the aerial vehicle, permitting the aerial vehicle to be launched. A device is connected to a pressurized gas source, the device controllably providing pressurized gas from the pressurized gas source to the passageway for drivingly moving the piston, the carriage, and aerial vehicle along the rail for launching the aerial vehicle. The device includes a reservoir for holding pressurized gas, the reservoir being a conduit, the pressurized gas in the reservoir providing the driving force for launching the aerial vehicle.

公开(公告)号：US20170297706A1

公开(公告)日：2017-10-19

申请号：US15338802

申请日：2016-10-31

Applicant: Ewatt Technology Co., Ltd.

Inventor： Guocheng ZHAO ,  Wei LUO

IPC: B64C39/02 ,  B64C25/58 ,  B64C1/06 ,  B64C5/02

CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C1/06 ,  B64C3/00 ,  B64C5/02 ,  B64C25/58 ,  B64C39/028 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187

Abstract: The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.

公开(公告)号：US20170297700A1

公开(公告)日：2017-10-19

申请号：US15402784

申请日：2017-01-10

Applicant: MARTIN UAV, LLC

Inventor： Stephen MORRIS

IPC: B64C29/02 ,  G05D1/08 ,  G05D1/10 ,  B64C11/00 ,  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：US20170291685A1

公开(公告)日：2017-10-12

申请号：US15388396

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

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.