公开(公告)号：US5035382A

公开(公告)日：1991-07-30

申请号：US339090

申请日：1989-04-17

Applicant: Peter B. S. Lissaman ,  W. Ray Morgan ,  Martyn B. Cowley ,  Charles J. Sink ,  William D. Watson

Inventor： Peter B. S. Lissaman ,  W. Ray Morgan ,  Martyn B. Cowley ,  Charles J. Sink ,  William D. Watson

IPC: A63H27/00 ,  A63H27/20 ,  B64C39/02 ,  B64D47/08

CPC classification number: A63H27/00 ,  B64C39/024 ,  B64D47/08 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2201/203

Abstract: A terrain surveillance, powered aircraft is disclosed to have an on-board video camera that is not gimballed relative to the aircraft, the aircraft typically comprising multiple components; the method of the invention including: assembling the components into aircraft configuration at or near a launch site; launching the aircraft at that site with no human pilot on board same; remotely controlling the flight path of the aircraft by radio or cable link, to fly to a location for terrain surveillance; operating the on-board video camera to survey the terrain while varying yaw of the aircraft to provide sweep viewing of the terrain; and recovering the aircraft by controlling its flight to steeply descend to a landing zone.

Abstract translation: 公开了一种地形监视，动力飞机，具有相对于飞机而不是游戏的车载摄像机，该飞机通常包括多个部件; 本发明的方法包括：将组件组装成发射场所处或附近的飞行器构型; 在该地点发射飞机，没有人造飞行员在船上; 通过无线电或有线链路远程控制飞机的飞行路径，飞到一个地形进行地形监视; 操作车载摄像机以在改变飞行器的偏航的同时对地形进行调查，以提供对地形的扫描观察; 并通过控制飞机陡降到着陆区来恢复飞机。

公开(公告)号：US4786008A

公开(公告)日：1988-11-22

申请号：US855238

申请日：1986-04-24

Applicant: Marshall J. Corbett

Inventor： Marshall J. Corbett

IPC: B64C39/02 ,  B64D27/22 ,  B64D27/00

CPC classification number: B64C39/024 ,  B64D27/22 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T50/44

Abstract: An unmanned aircraft is equipped with a helium-cooled Brayton cycle nuclear reactor. Heated helium gas drives turbines which in turn rotate propellers to maintain the aircraft aloft for a protracted period of time. After the helium gas expands in the turbines, it is passed through a closed loop including radiator tubes which radiate waste heat from the helium gas to space. The cooled helium gas is returned through the closed loop for repeat of the Brayton cycle.

Abstract translation: 一架无人驾驶飞机配备有氦冷却的布雷顿循环核反应堆。 加热氦燃气驱动涡轮机，这些涡轮机又旋转螺旋桨，以维持飞机高空飞行的持续时间。 在氦气在涡轮机中膨胀之后，它通过包括散热器管的闭合回路，辐射管将废热从氦气辐射到空间。 冷却的氦气通过闭环返回，重复Brayton循环。

公开(公告)号：US4194708A

公开(公告)日：1980-03-25

申请号：US944441

申请日：1978-09-21

Applicant: Daniel J. Tracy ,  John P. Palmer ,  Daniel J. O'Brien

Inventor： Daniel J. Tracy ,  John P. Palmer ,  Daniel J. O'Brien

IPC: B64C39/02 ,  B64C15/02 ,  B64D1/06

CPC classification number: B60V3/08 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/146

Abstract: A recoverable remotely piloted vehicle (RPV) having: a deflectable canard/elevator placed very close to the nose tip; a constant (cross) section fuselage; wings mounted low and well aft on the fuselage; elevons; a centrally positioned weapons/payload bay, with doors, located internal of the upper portion of the fuselage; and, inflatable landing skids. The weapon/payload is dropped from the RVP, while the RVP is in flight in an inverted position.

Abstract translation: 一种可恢复的遥控车辆（RPV），其具有：非常靠近鼻尖的可偏转的鸭子/电梯; 恒定（横）部分机身; 机身低矮，机身后方均匀; 电梯 一个位于中心的武器/有效载荷舱，带有位于机身上部内部的门; 和充气着陆滑行。 武器/有效载荷从RVP中丢弃，而RVP在倒置的位置飞行。

公开(公告)号：US20240109657A1

公开(公告)日：2024-04-04

申请号：US17957679

申请日：2022-09-30

Applicant: WING Aviation LLC

Inventor： Adam Woodworth ,  Giulia Pantalone ,  Michelle Suen ,  Luis Prado

IPC: B64C39/02 ,  B64C1/12 ,  B64C5/02 ,  B64C11/20

CPC classification number: B64C39/024 ,  B64C1/12 ,  B64C5/02 ,  B64C11/20 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, a pair of fixed wings attached to the fuselage, a tail assembly attached to an aft portion of the fuselage and including a pair of stabilizers, a plurality of distributed propulsion units having first propellers that rotate about first rotational axes positioned below the fixed wings, and a plurality of tail propulsion units having second propellers that rotate about second rotational axes each positioned inline with one of the stabilizers. The first propellers are mounted fore of the fixed wings and the second propellers are mounted fore of a corresponding one of the stabilizers. Three or more of the distributed propulsion units are mounted to each of the fixed wings.

公开(公告)号：US20190193839A1

公开(公告)日：2019-06-27

申请号：US13984688

申请日：2012-01-13

Applicant: Andreas Voss

Inventor： Andreas Voss

IPC: B64C17/02 ,  B64C39/02 ,  B64C39/10 ,  B64C3/30 ,  B64C11/00

CPC classification number: B64C15/00 ,  B64C17/04 ,  B64C39/024 ,  B64C39/028 ,  B64C39/066 ,  B64C39/068 ,  B64C2201/104 ,  B64C2201/165

Abstract: The invention pertains to a remote-controlled miniature aircraft with at least one lift surface (17), with at least one pair of propeller drives (12, 13) and with a weight element (20), the position of which can be varied in the longitudinal direction of the miniature aircraft (10) in order to change the center of gravity of the miniature aircraft (10). In order to realize a more compact and more robust construction with improved flying characteristics, the lift surface (17) of the miniature aircraft (10) is arranged above a plane defined by the rotational axes of the propeller drives (12, 13) in order to generate a lifting force for taking off and/or landing from a standstill.

公开(公告)号：US20180327114A1

公开(公告)日：2018-11-15

申请号：US16036604

申请日：2018-07-16

Applicant: AeroVironment, Inc.

Inventor： John Peter Zwaan ,  Robert James Johnston ,  Cris James Cornell ,  Philip Martin Finn ,  Glenn Arnold Blevins ,  David Wayne Ganzer

IPC: B64F1/02 ,  B63B17/00 ,  B64C39/02 ,  B63B35/52

CPC classification number: B64F1/02 ,  B63B17/00 ,  B63B35/52 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/025

Abstract: Systems, devices, and methods for impacting, by a small unmanned aerial vehicle (SUAV), a net having at least three sides; and converting the kinetic energy of the SUAV into at least one of: elastic potential energy of one or more tensioned elastic cords connected to at least one corner of the net, gravitational potential energy of a frame member connected to at least one corner of the net, rotational kinetic energy of the frame member connected to at least one corner of the net, and elastic potential energy of the frame member connected to at least one corner of the net.

公开(公告)号：US20180273158A1

公开(公告)日：2018-09-27

申请号：US15928355

申请日：2018-03-22

Applicant: Aurora Flight Sciences Corporation

Inventor： Christopher Courtin

IPC: B64C1/26 ,  B64C39/02

CPC classification number: B64C1/26 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2211/00

Abstract: Disclosed herein is a modular aerial vehicle system having a fuselage module configured to couple with a plurality of lift generation modules. The modular aerial vehicle system may comprise a fuselage module and a lift generation module. The fuselage module can include a first attachment interface, an avionics system operatively coupled with a power unit (e.g., via an ESC), and a communications system operatively coupled with the flight controller. The lift generation module can include a second attachment interface and a plurality of propulsors. The fuselage module may be configured to removably couple with the lift generation module via the first and second attachment interfaces. The first and second attachment interfaces may comprise (1) a plurality of electrical contacts to facilitate electrical communication between the fuselage module and the lift generation module and/or (2) one or more retention devices to couple structurally the lift generation module with said fuselage module.

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：US09994313B2

公开(公告)日：2018-06-12

申请号：US14554892

申请日：2014-11-26

Applicant: XCraft Enterprises, LLC

Inventor： Jerry Daniel Claridge ,  Charles Fischer Manning

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108

Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.