公开(公告)号：US20230271701A1

公开(公告)日：2023-08-31

申请号：US17682736

申请日：2022-02-28

Applicant: Saudi Arabian Oil Company

Inventor： Khaled F. Abusalem ,  Soliman A. Al-Walaie ,  Osama Bakur Bahwal

IPC: B64C39/02 ,  B60L53/53 ,  B60L58/12

CPC classification number: B64C39/022 ,  B64C39/024 ,  B60L53/53 ,  B60L58/12 ,  B64C2201/066 ,  B64C2201/088

Abstract: An unmanned aerial vehicle (UAV) system energized by power lines includes a UAV, a charging mechanism and an electric circuit. The charging mechanism is operatively coupled to a body of the UAV. The charging mechanism can connect to power transmission lines deployed near an air space in which the UAV is airborne and operating. The charging mechanism can draw power from the power transmission lines to power a flight of the UAV. The electric circuit is onboard the UAV. The electric circuit can generate charging currents based on the power drawn from the power transmission lines to power the flight of the UAV while the UAV is airborne.

公开(公告)号：US20230192287A1

公开(公告)日：2023-06-22

申请号：US17558307

申请日：2021-12-21

Applicant: Bell Textron Inc.

Inventor： Steven R. Ivans ,  Berlin B. Benfield

IPC: B64C29/00 ,  B64C39/02 ,  B64C1/14

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C1/1415 ,  B64C2201/088 ,  B64C2201/04 ,  B64C2201/024

Abstract: There is disclosed in one example an unmanned vertical lift aircraft, comprising: an airframe; a drive system configured for vertical takeoff and landing (VTOL); a power plant to power the drive system; and an internal cargo bay comprising a fore aperture and an aft aperture, the fore and aft apertures having dimensions substantially conforming to a cross section of the internal cargo bay, and the internal cargo bay comprising a substantially linear and open volume between the fore and aft apertures.

公开(公告)号：US20190217969A1

公开(公告)日：2019-07-18

申请号：US16256465

申请日：2019-01-24

Applicant: LOON LLC

Inventor： Joseph Charles Benedetto ,  Olivia Hatalsky ,  John Frederick Udall ,  Liang-Shian Chen ,  Chase R. Haegele ,  Daniel Patrick Bowen ,  C. O. Lee Boyce, JR. ,  Shane Washburn ,  Keegan Gartner

IPC: B64F1/04 ,  B64B1/58 ,  B64F1/36 ,  B64B1/00 ,  B64F1/14 ,  B64B1/40

CPC classification number: B64F1/04 ,  B64B1/005 ,  B64B1/40 ,  B64B1/58 ,  B64C2201/022 ,  B64C2201/088 ,  B64C2201/122 ,  B64F1/14 ,  B64F1/36

Abstract: A portable launch rig (PLR) may include a support structure including two side supports defining an interior space for lifting and filling a balloon envelope of a balloon. Wheels on each of the side supports enable the PLR to be moved in various directions in order to prepare the PLR for launching the balloon. The side supports are connected by a lateral support beam having a pair of cranes arranged thereon. Each crane has an arm arranged over the interior space that is connected to a spreader beam. The spreader beam includes a lift assembly configured to lift and inflate the balloon envelope within the interior space. The PLR includes a platform and perch for supporting and moving the balloon envelope. A door assembly of the PLR includes a plurality of hangar doors configured to block wind from a respective direction of each hangar door entering the interior space.

公开(公告)号：US10053213B1

公开(公告)日：2018-08-21

申请号：US15589409

申请日：2017-05-08

Applicant: Pinnacle Vista, LLC

Inventor： Haofeng Tu

IPC: B64C27/22 ,  B64C27/26 ,  B64C27/82 ,  G05D1/08 ,  G05D1/02 ,  G05D1/04 ,  B64C39/02

CPC classification number: B64C27/26 ,  B64C27/82 ,  B64C29/0025 ,  B64C39/024 ,  B64C39/12 ,  B64C2027/8236 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165 ,  G05D1/0202 ,  G05D1/042 ,  G05D1/0858

Abstract: A multi-copter lift body aircraft has a push or pull propeller and a lift body that has a first airfoil shape on a front to rear cross-section and a second airfoil shape on a left to right cross-section. The lift body is made from a top shell and a bottom shell. The lift body has a nose and a tail. Multi-copter propellers are attached to the lift body. The multi-copter propellers provide a lift at low speeds and the lift body provides a lift at high speeds. Avionics can be stored in a hollow cavity of the lift body. The avionics may include a control circuit, batteries, and a radio receiver. The multi-copter has a lift body made from an upper shell and a lower shell. The lift body has an optimum attack angle at a cruising speed, and the lift body provides a combined lift mode.

公开(公告)号：US20180178899A1

公开(公告)日：2018-06-28

申请号：US15391700

申请日：2016-12-27

Applicant: Korea Advanced Institute of Science and Technology

Inventor： Dongsoo HAR ,  Celso MORAES ,  Dongsuk KUM

IPC: B64C3/38 ,  B64C29/02 ,  B64C9/20 ,  B64C13/50 ,  B64C39/02 ,  B64D27/24

CPC classification number: B64D27/24 ,  B64C3/385 ,  B64C5/02 ,  B64C11/001 ,  B64C13/50 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/62

Abstract: An aircraft includes: a fuselage having opposing leading and trailing extremities along a vertical axis; a fixed wing airframe having opposed at least two main wings connected to the fuselage and extending on a horizontal axis; at least two electric coplanar main wing motors respectively attached to the main wings; a duct frame attach to the trailing extremity of the fuselage; at least two horizontal stabilizers connected to the duct frame and extending on the horizontal axis; an electric tail motor fitted an inner side of the duct frame; multiple battery packs installed inside the fuselage and suitable for supply power to the main wing motors and the tail motor; and support beams suitable for connecting the duct frame to the fuselage.

公开(公告)号：US09988147B2

公开(公告)日：2018-06-05

申请号：US15638970

申请日：2017-06-30

Applicant: AEROVIRONMENT, INC.

Inventor： Dana J. Taylor ,  Phillip T. Tokumaru ,  Bart Dean Hibbs ,  William Martin Parks ,  David Wayne Ganzer ,  Joseph Frederick King

IPC: B64C29/00 ,  G05D1/08 ,  B64C27/26 ,  B64C39/02 ,  B64C11/32 ,  B64C29/02 ,  B64C27/605 ,  B64D27/24 ,  B64C27/54

CPC classification number: B64C29/0025 ,  B64C11/32 ,  B64C27/26 ,  B64C27/54 ,  B64C27/605 ,  B64C29/00 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  G05D1/0858

Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.

公开(公告)号：US09964960B2

公开(公告)日：2018-05-08

申请号：US15185809

申请日：2016-06-17

Applicant: Sikorsky Aircraft Corporation

Inventor： Cody Fegely ,  Stephen Kubik

IPC: G05D1/06 ,  G05D1/08 ,  B64C13/18 ,  B64C29/02

CPC classification number: G05D1/0676 ,  B64C13/18 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/18 ,  G05D1/0623 ,  G05D1/0858

Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, wings extending outwardly from the fuselage to define a wing plane and a prop-rotor operably disposed to generate thrust, a flight computer and controllable surfaces disposed on at least one of the fuselage, the wings and the prop-rotor. The controllable surfaces are controllable by the flight computer to position the wing plane in accordance with a predominant local wind direction.

公开(公告)号：US20180101169A1

公开(公告)日：2018-04-12

申请号：US15844207

申请日：2017-12-15

Applicant: Paul G. Applewhite

Inventor： Paul G. Applewhite

IPC: G05D1/00 ,  B64F1/04 ,  B64F1/06 ,  B64C39/02 ,  B64C27/82 ,  B64C29/02 ,  B64C29/00

CPC classification number: G05D1/0027 ,  B64C11/04 ,  B64C11/28 ,  B64C27/82 ,  B64C29/0083 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/126 ,  B64C2201/146 ,  B64F1/04 ,  B64F1/06 ,  G05D1/104 ,  G08G5/00 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0069

Abstract: An improved unmanned aerial vehicular system having a rotor head assembly with any balanced number of rotary wings or blades, a generally tubular body assembly, a gimballed neck connecting the head to the body, and a navigation, communications and control unit such as for military and humanitarian operations, including payload delivery and pickup. The vehicle is generally guided using a global positioning satellite signal, and by pre-programmed or real time targeting. The vehicle is generally electrically powered and may be launched by one of (a) hand-launch, (b) air-drop, (c) catapult, (d) tube-launch, or (e) sea launch, and is capable of landing on both static and dynamic targets. Once launched, unmanned aerial vehicles may be formed into arrays on a target area and find use in surveillance, warfare, and in search-and-rescue operations.

公开(公告)号：US20180093765A1

公开(公告)日：2018-04-05

申请号：US15683870

申请日：2017-08-23

Applicant: BRENDAN GRAHAM

Inventor： BRENDAN GRAHAM

IPC: B64C29/02 ,  B64C39/08 ,  B64C1/28 ,  B64C27/26 ,  G05D1/08 ,  G05D1/10

CPC classification number: B64C29/02 ,  B64C1/28 ,  B64C27/26 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  G05D1/0858 ,  G05D1/102

Abstract: This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation.

公开(公告)号：US09902494B2

公开(公告)日：2018-02-27

申请号：US15402784

申请日：2017-01-10

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: B64C29/00 ,  B64C29/02 ,  G05D1/10 ,  G05D1/08 ,  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.