公开(公告)号：US5277380A

公开(公告)日：1994-01-11

申请号：US903060

申请日：1992-06-22

Applicant: James P. Cycon ,  Kenneth M. Furnes ,  Fred W. Kohlhepp ,  Marvin D. Farrell ,  David F. Sandy

Inventor： James P. Cycon ,  Kenneth M. Furnes ,  Fred W. Kohlhepp ,  Marvin D. Farrell ,  David F. Sandy

IPC: B64C1/00 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06

CPC classification number: B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: An unmanned aerial vehicle having a toroidal fuselage structure that surrounds a pair of coaxial, multi-bladed, counter-rotating rotors. The toroidal fuselage structure is optimized to provide a highly efficient structure for reacting aerodynamic flight loads and rotor thrust loads of the UAV. The toroidal fuselage structure is further optimized to provide weight efficiency for minimizing power requirements.

Abstract translation: 一种具有环形机身结构的无人驾驶飞行器，其环绕一对同轴，多叶片，反向旋转的转子。 优化了环形机身结构，为空中动力学飞行载荷和无人机的转子推力载荷提供了高效的结构。 环形机身结构进一步优化，以提供重量效率以最小化功率需求。

公开(公告)号：US5082079A

公开(公告)日：1992-01-21

申请号：US519015

申请日：1990-05-04

Applicant: Peter B. S. Lissaman ,  Herman M. Drees ,  Charles J. Sink ,  William D. Watson

Inventor： Peter B. S. Lissaman ,  Herman M. Drees ,  Charles J. Sink ,  William D. Watson

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162

Abstract: A flight system capable of passively stable hover comprises an apparatus defining a vertical axis, and including multiple upright ducts spaced about the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts; and fluid flow deflector structure in the path of the downwardly flowing fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus.

Abstract translation: 能够被动地稳定悬停的飞行系统包括限定垂直轴线的装置，并且包括围绕该轴线间隔开的多个直立导管; 管道中的流体动量发生器以使流体在管道中向下流动; 以及在向下流动的流体的路径中的流体流动偏转器结构，并且成角度以使流体流离开轴线，以便提供装置悬停的稳定性。

公开(公告)号：US3669385A

公开(公告)日：1972-06-13

申请号：US3669385D

申请日：1970-10-08

Applicant: FAIRCHILD INDUSTRIES

Inventor： GLANTZ EARL ,  MCCOMAS JEAN W

IPC: B64C1/00 ,  B64C39/02 ,  B64D5/00 ,  B64C1/26

CPC classification number: B64D5/00 ,  B64C1/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/185

Abstract: An aircraft of improved of simplified construction having forward and aft generally cylindrical and substantially identical fuselage sections that are connected to a central fuselage section that houses an engine that has an inlet located above the forward fuselage section for powering the aircraft in flight. The central long axis of the aft fuselage section is located above the central long axis of the forward fuselage section. Wings are connected to the central fuselage section and a tail assembly is connected to the aft portion of the aft fuselage section. Many of the component parts of the aircraft are interchangeable and the aircraft is especially suited for use as a drone for towing aerial targets.

Abstract translation: 具有改进的简化结构的飞机具有前后大体上圆柱形和基本相同的机身部分，其连接到中央机身部分，该中央机身部分容纳具有位于前机身部分上方的入口的发动机，用于为飞行器提供动力。 后部机身部分的中心长轴位于前机身部分的中心长轴上方。 翼连接到中央机身部分，尾部组件连接到后机身部分的后部。 飞机的许多组成部分是可互换的，飞机特别适用于作为无人驾驶用于拖曳空中目标的飞机。

公开(公告)号：US20190202563A1

公开(公告)日：2019-07-04

申请号：US16332282

申请日：2017-09-15

Applicant: AirRobot GmbH & Co. KG

Inventor： Burkhard Wiggerich

IPC: B64D1/22 ,  B64C39/02 ,  B64C1/22

CPC classification number: B64D1/22 ,  B64C1/22 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/143 ,  B64C2201/162

Abstract: The invention relates to a device for airlifting an object comprising a support structure, wherein the support structure has an upper end region and a lower end region, wherein the upper end region and the lower end region have at least partly corresponding shapes.

公开(公告)号：US20180354624A1

公开(公告)日：2018-12-13

申请号：US15616926

申请日：2017-06-08

Applicant: Yongbiao Liu

Inventor： Yongbiao Liu

IPC: B64D1/18 ,  B64C39/02 ,  B64C27/08 ,  A01C21/00 ,  A01M7/00

CPC classification number: B64D1/18 ,  A01C21/00 ,  A01C21/002 ,  A01C23/047 ,  A01M7/00 ,  B64C39/024 ,  B64C2201/066 ,  B64C2201/12 ,  B64C2201/146 ,  B64C2201/162

Abstract: The present invention is a drone for spraying liquid such as pesticides, fungicides, herbicides, plant growth regulators, plant defoliators, and fertilizers over field crop. The drone comprises: a frame with a slender rigid beam in the middle and two base structures at the two ends, a rigid tube with an array of nozzles on elongated stems and the rigid tube is suspended below the beam structure with retractable wires, at least three propellers on motors with arms that are rotatably mounted to each of the two base structures of the frame, a power source positioned in one of the bases, at least one distance detector for measuring height of the drone above the ground, an antenna for sending and receiving communication signals, an electronic control system to operate motors and sensors, a container for a liquid material with a caped opening for refilling and an air pump to maintain a positive pressure in the container and electronic valve to allow liquid in the container under pressure to be released through a transfer line to be sprayed from the nozzles, and a remote controller for operating the drone. The invention provides a specialized drone that is able to spray liquid solutions over a wide strip of the field at a height close to crop canopy to achieve high efficiency and precision and reduced drift of sprays while the drone flies at a relatively high above the crop canopy for safe operation and avoid damage to crop by air turbulence.

公开(公告)号：US20180231016A1

公开(公告)日：2018-08-16

申请号：US15338035

申请日：2016-10-28

Applicant: Rolls-Royce Corporation

Inventor： Bronwyn Power ,  Jonathan M. Rivers

IPC: F04D29/28 ,  F04D29/34 ,  B64C11/06 ,  B63H1/16 ,  B23K101/00 ,  F04D29/32 ,  B64C11/00

CPC classification number: F04D29/282 ,  B23K2101/001 ,  B63H1/16 ,  B64C11/001 ,  B64C11/06 ,  B64C2201/162 ,  B64C2201/165 ,  B64D2027/005 ,  F01D5/143 ,  F01D5/225 ,  F02C9/58 ,  F02K3/04 ,  F02K3/072 ,  F04D29/326 ,  F04D29/329 ,  F04D29/34 ,  F05D2220/323 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2220/36

Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.

公开(公告)号：US20180194463A1

公开(公告)日：2018-07-12

申请号：US15328352

申请日：2015-07-22

Applicant: AIRBUS DEFENCE AND SPACE LIMITED

Inventor： Julian HASINSKI ,  Brian TURTON

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: Unmanned aerial vehicles (1), and methods of flying such, comprising at least four rotors (2) arranged such that the plane of rotation of each rotor (2) is co-planar with a face of a notional polyhedron, and wherein each face of the notional polyhedron is co-planar with the plane of rotation of at least one rotor (2). Such methods comprise: a first step of flying the vehicle (1) using a first rotor set (2a-c) to provide lift; and, a second step using a second rotor set (2d-f) to provide lift; wherein, the second rotor set (2d-f) includes at least one rotor (2) that is not used to provide lift in the first step or that operates so that airflow through the rotor (2) is in the opposite direction to that through the rotor (2) during the first step; and, wherein at least one of the first and second sets (2a-c, 2d-f) comprises a plurality of rotors (2).

公开(公告)号：US20180037317A1

公开(公告)日：2018-02-08

申请号：US15552364

申请日：2016-02-25

Applicant: PRODRONE CO., LTD.

Inventor： Kazuo ICHIHARA ,  Kiyokazu SUGAKI

IPC: B64C27/20 ,  B64C27/28 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64C27/20 ,  B64C27/08 ,  B64C27/28 ,  B64C29/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162

Abstract: To provide a multicopter that enables it to prevent generation of a vortex ring state of a rotor and control lift and thrust efficiently and elaborately. This is solved by a multicopter having a plurality of rotors installed radially to a frame, wherein at least one of the plurality of rotors is provided with a cylindrical duct surrounding and enclosing the rotor; and the duct is formed in a shape making an air flow from an air intake side to an air outlet side of the rotor imbalanced in a circumferential direction of the duct.

公开(公告)号：US20180022461A1

公开(公告)日：2018-01-25

申请号：US15530528

申请日：2017-01-25

Applicant: Brendon G. Nunes ,  Florentin Christoph von Frankenberg

Inventor： Brendon G. Nunes ,  Florentin Christoph von Frankenberg

IPC: B64D27/24 ,  B64B1/32 ,  B64C39/02 ,  B64B1/34

CPC classification number: B64D27/24 ,  B64B1/32 ,  B64B1/34 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64D2027/026 ,  Y02T50/62

Abstract: A hybrid airship (drone, UAV) capable of significantly extended flight times can use one of two technologies, or both together. The first technology uses a combination of a lifting gas (such as hydrogen or helium) in a central volume or balloon and multirotor technology for lift and maneuvering. The second technology equips the airship with an on board generator to charge the batteries during flight for extended flight operations, with an internal combustion engine (such as a high power to weight ratio gas turbine engine) driving the generator. A quadcopter or other multicopter configuration is desirable.

公开(公告)号：US20170369162A1

公开(公告)日：2017-12-28

申请号：US15372667

申请日：2016-12-08

Applicant: Saeid A. ALZAHRANI

Inventor： Saeid A. ALZAHRANI

IPC: B64C29/00 ,  B64C3/38 ,  B64C39/02 ,  B64C25/22 ,  B64C27/52

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C25/22 ,  B64C27/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162

Abstract: A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.