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.

公开(公告)号：US20180022467A1

公开(公告)日：2018-01-25

申请号：US15543443

申请日：2015-11-16

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64D35/04 ,  B64D27/12 ,  B64C39/02 ,  B64C27/82 ,  B64D27/06 ,  B64C29/02

CPC classification number: B64D35/04 ,  B64C27/82 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  B64D27/06 ,  B64D27/12 ,  Y02T50/44

Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

公开(公告)号：US09873524B2

公开(公告)日：2018-01-23

申请号：US15466012

申请日：2017-03-22

Applicant: AeroVironment, Inc.

Inventor： Christopher Eugene Fisher ,  Jason Sidharthadev Mukherjee ,  William Arden Lott

IPC: B64F1/00 ,  B64C39/02 ,  B64C29/02 ,  B64F1/12

CPC classification number: B64F1/005 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/201 ,  B64F1/12

Abstract: A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system including: a rearward facing tang extending from a rear fuselage portion of a VTOL UAV; one or more metallic contacts disposed on an exterior surface of the tang; a UAV pod including a landing surface; and an opening disposed in the landing surface to receive the tang.

公开(公告)号：US09849977B2

公开(公告)日：2017-12-26

申请号：US14860072

申请日：2015-09-21

Applicant: Kabushiki Kaisha TOPCON

Inventor： Atsushi Tanahashi

IPC: B64C29/02 ,  B64C29/00 ,  G05D1/00 ,  B64C39/02 ,  B64D47/08 ,  E02F9/26 ,  G05D1/10 ,  G06K9/00 ,  E02F9/20

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/145 ,  B64D47/08 ,  E02F9/205 ,  E02F9/2054 ,  E02F9/262 ,  G05D1/0011 ,  G05D1/0027 ,  G05D1/0094 ,  G05D1/102 ,  G05D2201/0202 ,  G06K9/00637

Abstract: A site management system includes an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight, a working vehicle working in a civil construction site, a shape detection sensor provided in the unmanned airplane to detect a shape of the civil construction site, and an external control apparatus that controls flight of the unmanned airplane, driving of the working vehicle, and driving of the shape detection sensor. The external control apparatus moves the unmanned airplane to an observation area by performing the high speed flight. Further, the external control apparatus detects a shape of the observation area by driving the shape detection sensor while performing the high speed flight or by driving the shape detection sensor while performing low speed flight by switching from the airplane mode to the VTOL mode.

公开(公告)号：US09834305B2

公开(公告)日：2017-12-05

申请号：US14706905

申请日：2015-05-07

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

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.