公开(公告)号：US10011259B1

公开(公告)日：2018-07-03

申请号：US15832099

申请日：2017-12-05

Applicant: SPIN MASTER LTD.

Inventor： Mark Ladislao ,  Conor Forkan

IPC: B60V1/14 ,  B60V1/11 ,  B64C39/02

CPC classification number: B60V1/14 ,  B60V1/11 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/165

Abstract: In one aspect, there is provided a combination vehicle system, including a drone and a hovercraft body. The drone has a plurality of motor-driven rotors and a controller. The hovercraft body defines a ground-facing chamber having a hover air inlet, and includes a mount for the drone. The drone is removably connectable to the mount in a mounted position so as to form a hovercraft. The controller is programmed to drive the plurality of rotors to maintain stable flight of the drone without the hovercraft body connected thereto. The controller is programmed to drive the first rotor to at least partially lift the hovercraft off a support surface and to drive the second rotor to propel the hovercraft along the support surface.

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：US20180127093A1

公开(公告)日：2018-05-10

申请号：US15801790

申请日：2017-11-02

Applicant: California Institute of Technology ,  The Regents of the University of California

Inventor： Lance E. Christensen ,  Brendan J. Smith ,  Vlad Manzatianu

IPC: B64C39/02 ,  G01P5/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  G01P5/02

Abstract: Unmanned Aerial Systems (UAS) for use in the detection, localization, and quantification of gas leaks are provided. More specifically the use of an in-situ sensor mounted to a UAS such that the sensor is positioned in a region unaffected by prop wash that is relatively undisturbed by the effects of the propeller(s) and other environmental conditions when in use is described. Additionally, methods of determining the optimal placement of the in-situ sensor on any given UAS are also provided.

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：US20180093755A1

公开(公告)日：2018-04-05

申请号：US15689945

申请日：2017-08-29

Applicant: AeroVironment, Inc.

Inventor： Carlos Thomas Miralles

IPC: B64C13/16 ,  F41G7/22 ,  G05D1/12 ,  B64C39/02

CPC classification number: B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

公开(公告)号：US09889933B2

公开(公告)日：2018-02-13

申请号：US15401475

申请日：2017-01-09

Applicant: International Business Machines Corporation

Inventor： Brian S. Beaman ,  Eric V. Kline ,  Sarbajit K. Rakshit

IPC: G05D1/00 ,  B64D1/00 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64D1/00 ,  B64C27/08 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/143 ,  B64C2201/165

Abstract: Aspects include a system for transferring a payload between drones. The system includes a first drone having a first member and a first controller, the first member having a first coupling device on one end, the first member being configured to carry a payload, the first controller being configured to change a first altitude and orientation of the first drone. A second drone includes a second member and controller, the second member having a second coupling device on one end, the second member being configured to receive the payload, the second controller being configured to change a second altitude and orientation of the second drone. The controllers cooperate to change at least one of first and second orientations to operably engage the first coupling device to the second coupling device for transferring the payload from the first member to the second member.

公开(公告)号：US09884681B2

公开(公告)日：2018-02-06

申请号：US15405140

申请日：2017-01-12

Applicant: SZ DJI TECHNOLOGY CO., Ltd

Inventor： Tao Wang ,  Tao Zhao ,  Hao Du ,  Mingxi Wang

IPC: B64C1/06 ,  B64C39/02 ,  B64D47/08 ,  B64C27/08 ,  B64C25/32 ,  A63H27/00

CPC classification number: B64C1/063 ,  A63H27/12 ,  B64C1/00 ,  B64C1/061 ,  B64C25/32 ,  B64C27/08 ,  B64C39/024 ,  B64C39/028 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/146 ,  B64C2201/165 ,  B64D47/00 ,  B64D47/08 ,  G05D1/042

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

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：US20180022455A1

公开(公告)日：2018-01-25

申请号：US15655805

申请日：2017-07-20

Applicant: Dustin McCaslin

Inventor： Dustin McCaslin

IPC: B64D1/12 ,  B64C39/02 ,  B64D47/08

CPC classification number: B64D1/12 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64D47/08

Abstract: A dropping mechanism with universal mounting points includes a device for securing a payload to a drone, mechanically releasing it and mounting additional accessories that can be used during flight. The dropping mechanism can be attached to either the landing gear or body of the drone, in an orientation that allows contact between the release trigger and the drone's camera. A notch and groove system holds a sliding restraint in place, keeping the payload secure during flight. Once the release trigger is pushed, an energized member pulls the sliding restraint allowing the payload to drop. Since the camera is pointed down to actuate the trigger, the user can watch as the payload falls to the ground. The use of a mechanical dropping system makes this device compatible with drones that only have an electrical connection for the camera. Universal mounting points allow attachment of a wide variety of accessories.