公开(公告)号：US06322021B1

公开(公告)日：2001-11-27

申请号：US09593229

申请日：2000-06-14

Applicant: Jeffrey A. Fisher ,  Edward V. Miller

Inventor： Jeffrey A. Fisher ,  Edward V. Miller

IPC: G64C3102

CPC classification number: B64C31/024 ,  B64C31/032 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64D5/00 ,  Y10S244/902 ,  Y10S244/903

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract translation: 可展开的机翼，其被折叠以便装配在诸如飞机的载体中，并且借助于降落伞来自动地部署和飞行给定距离而不需要辅助而不是转向以达到给定的目的地并由螺旋桨驱动的螺旋桨 气动发动机被致动以推动机翼延长距离。 护翼与螺旋桨相邻设置，以确保降落伞的线条不会缠绕到螺旋桨叶片中。

公开(公告)号：US5395073A

公开(公告)日：1995-03-07

申请号：US7130

申请日：1993-01-22

Applicant: Elbert L. Rutan ,  Hugh J. Schmittle

Inventor： Elbert L. Rutan ,  Hugh J. Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/187 ,  B64D2201/00 ,  Y10S446/901

Abstract: A VTOL/STOL free wing aircraft includes a free wing having wings on opposite sides of a fuselage connected to one another respectively adjacent fixed wing inboard or center root sections fixedly attached to the fuselage for free rotation about a spanwise access. Horizontal and vertical tail surfaces are located at the rear end of a boom assembly rotatably connected to the fuselage. A gearing or screw rod arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage in relation to the tail boom assembly to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight.

Abstract translation: VTOL / STOL自由翼飞机包括一个自由翼，机身相对两侧分别相邻的固定翼或固定在机身上的固定翼部分的机翼相对两侧的翅膀，用于围绕翼展向的自由旋转。 水平和垂直的尾部表面位于可旋转地连接到机身的悬臂组件的后端。 由飞行员或遥控操作员控制的传动装置或螺杆杆装置选择性地使机身相对于尾臂组件枢转，以使机身能够呈现倾斜或鼻部向上的构型，以使得垂直起落架/高空作业飞行。

公开(公告)号：US5070955A

公开(公告)日：1991-12-10

申请号：US583477

申请日：1990-09-17

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

Abstract: A flight system capable of passively stable hover and horizontal translatory flight, comprises an apparatus defining a vertical axis, and including multiple ducts with substantially vertical axes in hover mode, spaced the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts in hover; and fluid flow deflector structure in the path of the flowing duct fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus, as well as stability when the entire device is tilted through approximately 90.degree. to execute horizontal translatory flight.

Abstract translation: 能够被动地稳定悬停和水平平移的飞行系统包括限定垂直轴的装置，并且包括多个具有悬挂模式的基本垂直轴线的管道，该轴线间隔开; 管道中的流体动量发生器以在悬浮的管道中使流体向下流动; 以及在流动管道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，以及当整个装置倾斜通过时的稳定性 大约90°执行水平平移飞行。

公开(公告)号：US3053480A

公开(公告)日：1962-09-11

申请号：US84467359

申请日：1959-10-06

Applicant: PIASECKI AIRCRAFT CORP

Inventor： VANDERLIP EDWARD G

IPC: B64C27/54 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/54 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146

公开(公告)号：US11661191B2

公开(公告)日：2023-05-30

申请号：US17465365

申请日：2021-09-02

Applicant: Endurant Systems, LLC

Inventor： Gregory Leonard McAdoo

IPC: B64C39/02 ,  B64C27/08 ,  B64D27/24 ,  B64C27/26 ,  B64C29/00 ,  B64C39/04 ,  H02J7/14 ,  H02J7/34 ,  B64D45/00 ,  H02K7/18 ,  B64D27/02 ,  B64D27/04

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/26 ,  B64C29/0033 ,  B64C39/04 ,  B64D27/24 ,  B64D45/00 ,  H02J7/14 ,  H02J7/34 ,  H02K7/1815 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/141 ,  B64D27/04 ,  B64D2027/026 ,  B64D2045/0085 ,  B64D2221/00 ,  Y02T50/60

Abstract: UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

公开(公告)号：US20190241264A1

公开(公告)日：2019-08-08

申请号：US16387057

申请日：2019-04-17

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

IPC: B64C39/02 ,  B64D33/08 ,  B64D27/24 ,  B64D1/22 ,  B64D1/08 ,  B64F3/02 ,  G05D1/10 ,  B64D27/02 ,  B64C27/00 ,  B64C27/08

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

公开(公告)号：US20190024548A1

公开(公告)日：2019-01-24

申请号：US15736876

申请日：2016-06-17

Applicant: ORBITAL AUSTRALIA PTY LTD

Inventor： Stephen John KARAY ,  Mario Charles MUSCAT ,  Pouria MEHRANI

IPC: F01N1/08 ,  F01N13/18

CPC classification number: F01N1/083 ,  B64C39/024 ,  B64C2201/044 ,  F01N1/003 ,  F01N1/023 ,  F01N13/002 ,  F01N13/1833 ,  F01N13/1894

Abstract: A muffler devised particularly for a small, reciprocating-piston two-stroke internal combustion engine of the type used on unmanned aerial vehicles. The muffler comprises a body incorporating an inlet, an outlet, and a plurality of chambers for exhaust gas flow from the inlet to the outlet. The body is configured to present a compact profile for installation on the engine. The chambers are so configured that adjacent chambers communicate to facilitate exhaust gas flow from the inlet to the outlet via flow passages. The various chambers comprise an inner chamber, an outer chamber, and one or more intervening chambers disposed between the inner and outer chambers. The various chambers are disposed one about another in annular formation. This arrangement creates a long flow path from the inlet to the outlet incorporating various directional changes.

公开(公告)号：US20180002026A1

公开(公告)日：2018-01-04

申请号：US15606242

申请日：2017-05-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Paul K. Oldroyd ,  John Richard McCullough

IPC: B64D27/12 ,  B64D27/26 ,  B64C11/46 ,  B64C29/00

CPC classification number: B64D27/12 ,  B64C11/46 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2211/00 ,  B64D27/06 ,  B64D27/24 ,  B64D27/26 ,  B64D31/00 ,  B64D35/08 ,  B64D2027/026 ,  B64D2027/262 ,  Y02T50/62

Abstract: An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

公开(公告)号：US20180002010A1

公开(公告)日：2018-01-04

申请号：US15638267

申请日：2017-06-29

Applicant: Unmanned Innovation, Inc.

Inventor： Mark Patrick Bauer ,  Bernard J. Michini ,  Brett Michael Bethke

IPC: B64C29/00 ,  B64C39/02 ,  G08G5/00

CPC classification number: B64C29/0025 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/146 ,  G08G5/0013 ,  G08G5/0034 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/0086

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for an unmanned aerial system inspection system. One of the methods is performed by a UAV and includes obtaining, from a user device, flight operation information describing an inspection of a vertical structure to be performed, the flight operation information including locations of one or more safe locations for vertical inspection. A location of the UAV is determined to correspond to a first safe location for vertical inspection. A first inspection of the structure is performed is performed at the first safe location, the first inspection including activating cameras. A second safe location is traveled to, and a second inspection of the structure is performed. Information associated with the inspection is provided to the user device.

公开(公告)号：US20170305537A1

公开(公告)日：2017-10-26

申请号：US15133444

申请日：2016-04-20

Applicant: Pride Haley Smith ,  David Alma Lynn Lewis ,  Ryan Robert Walz

Inventor： Pride Haley Smith ,  David Alma Lynn Lewis ,  Ryan Robert Walz

IPC: B64C27/02 ,  G05D1/10 ,  B64D47/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/12 ,  B64C2201/143 ,  B64C2201/165 ,  B64D47/02 ,  G05D1/0094

Abstract: An un-manned aerial vehicle including a powered chassis having a top side and a bottom side. The powered chassis includes a fuel powered electricity generator. The vehicle includes a flight system functionally coupled to the powered chassis. The vehicle includes a flood light system functionally coupled to a bottom side of the powered chassis and oriented to project light downward therefrom. The flood light system includes a plurality of modular lights that are able to selectably couple to the bottom side of the powered chassis. The flood light system includes a programmable light control module that controls lighting. The vehicle includes an automated flight control system functionally coupled to the flight system that automatically directs light from the flood light system to a desired region.