公开(公告)号：KR101287624B1

公开(公告)日：2013-07-23

申请号：KR1020130020070

申请日：2013-02-25

Applicant: 주식회사 네스앤텍

Inventor： 이기성

IPC: B64C29/02 ,  B64C13/20 ,  B64C3/38

CPC classification number: B64C27/28 ,  B64C3/38 ,  B64C3/58 ,  B64C9/323 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/185 ,  B64C2201/187

Abstract: PURPOSE: An unmanned aerial vehicle for easy landing is provided to enable easy landing without a parachute or airbag by switching the direction of a propeller upward and controlling the descending velocity thereof. CONSTITUTION: An unmanned aerial vehicle for easy landing comprises a propeller (100), a propeller tower (200), a body (300), main wings (400), auxiliary wings (500), and an actuator. The propeller tower supports the propeller. The body is connected to the propeller tower. The main wings are symmetrical with respect to the horizontal shaft of the body and have a pair of through holes (410). The auxiliary wings are located inside the through holes. The actuator is connected to a reference shaft fixed to the main wings through the auxiliary wings and controls the inclination of the auxiliary wings.

Abstract translation: 目的：提供一种易于着陆的无人驾驶飞行器，通过向上切换螺旋桨的方向并控制其下降速度，轻松着陆，无需降落伞或气囊。 构成：易于着陆的无人驾驶飞行器包括螺旋桨（100），螺旋桨塔（200），主体（300），主翼（400），辅助翼（500）和致动器。 螺旋桨塔支撑螺旋桨。 车身连接到螺旋桨塔。 主翼相对于主体的水平轴对称，并具有一对通孔（410）。 辅助翼位于通孔内。 致动器通过辅助翼连接到固定到主翼的基准轴，并控制辅助翼的倾斜。

公开(公告)号：US20230399096A1

公开(公告)日：2023-12-14

申请号：US16542098

申请日：2019-08-15

Applicant: Meta Platforms, Inc.

Inventor： Adrian Hachen ,  Oliver Ensslin ,  Eduardo Cabot

IPC: B64C25/16 ,  B64C39/02 ,  B64C25/14 ,  B64C25/20 ,  B64C25/50 ,  B64C25/44 ,  B64C25/34

CPC classification number: B64C25/16 ,  B64C39/024 ,  B64C25/14 ,  B64C25/20 ,  B64C25/505 ,  B64C25/44 ,  B64C25/34 ,  B64C2201/187

Abstract: The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

公开(公告)号：US09540101B2

公开(公告)日：2017-01-10

申请号：US14507198

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler ,  Adam Woodworth

IPC: B64C27/52 ,  B64C29/04 ,  B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C25/10 ,  B64D27/02 ,  B64D43/00

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

Abstract translation: 根据本发明的一个方面的垂直起飞（VTOL）飞机包括机身，具有位于机身尾端的全移动水平稳定器的尾翼，机身具有位于机身的大致中间位置 翼的远端​​，其中翼被配置成使用位于机身的每一侧上的倾斜铰链在基本上直的机翼构型和倾斜翼结构之间转换。 垂直起落飞行器还可以包括一个或多个可伸缩的弹簧支撑件，其中可伸缩的弹簧支撑构造成从翼的远端中的每一个展开。

公开(公告)号：US20150336666A1

公开(公告)日：2015-11-26

申请号：US14507198

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： JAMES DONALD PADUANO ,  PAUL NILS DAHLSTRAND ,  JOHN BROOKE WISSLER ,  ADAM WOODWORTH

IPC: B64C29/04

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

公开(公告)号：US09114871B2

公开(公告)日：2015-08-25

申请号：US13954362

申请日：2013-07-30

Applicant: Aurora Flight Sciences Corporation

Inventor： Adam John Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Scott Hollman

IPC: B64D27/00 ,  B64C1/30 ,  B64D27/26 ,  B64D9/00 ,  B64C19/00 ,  B64D1/14 ,  B64C15/00 ,  B64C39/02 ,  A63H27/00

CPC classification number: B64C1/30 ,  A63H27/001 ,  A63H27/02 ,  B64C15/00 ,  B64C19/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64D1/14 ,  B64D9/00 ,  B64D27/26

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract translation: 描述了一种无人驾驶飞机。 飞行器包括机身，连接到机身的后部的一对翼片，连接到机身的底部的一对二面支架，第一推力矢量（“T / V”）模块和第二T / V模块，以及电子模块。 电子模块向两个T / V模块提供命令。 两个T / V模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接连接的电动机作为T / V模块，使飞机能够在大范围的空速下执行紧半径的转弯。

公开(公告)号：US20150197335A1

公开(公告)日：2015-07-16

申请号：US14415433

申请日：2013-09-12

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Guy Dekel ,  Lior Zivan ,  Yoav Efraty ,  Amit Wolff ,  Avner Volovick

IPC: B64C27/52 ,  G05D1/08 ,  G05D1/04

CPC classification number: B64C27/52 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187 ,  G05D1/042 ,  G05D1/0808 ,  G05D1/0858 ,  G05D1/102

Abstract: A control system configured to control an acceleration of an air vehicle which comprises a tiltable propulsion unit that is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle, the control system comprising: (a) an input interface for receiving information indicative of a monitored airspeed of the air vehicle; and (b) a control unit, configured to issue controlling commands to a controller of the tiltable propulsion unit for controlling the acceleration of the air vehicle.

Abstract translation: 一种被配置为控制空中交通工具的加速度的控制系统，该控制系统包括可倾斜的推进单元，该倾斜推进单元可倾斜以提供方向至少相对于空气在一般的垂直推力矢量方向和一般纵向推力向量方向之间变化的推力 车辆，所述控制系统包括：（a）输入接口，用于接收指示所述空中交通工具的监控空速的信息; 以及（b）控制单元，被配置为向所述可倾斜推进单元的控制器发出控制命令，以控制所述空中交通工具的加速度。

公开(公告)号：US20150183520A1

公开(公告)日：2015-07-02

申请号：US14416035

申请日：2013-07-19

Applicant: Andrew Charles ELSON

Inventor： Andrew Charles Elson

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187

Abstract: A method of launching a powered unmanned aerial vehicle, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, wherein the vehicle is prevented from entering its flight mode during ascent, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract translation: 一种发射有功无人驾驶飞行器的方法，该方法包括通过从基本上地平面位置到高架高度附接到比轻空载体提升车辆，其中在上升期间车辆被阻止进入其飞行模式 ，当车辆相对于承运人的速度基本上为零时，导致车辆从载体上脱离，随后车辆随着其高度减小到能够防止任何进一步下降并能够开始独立持续飞行的速度 。

公开(公告)号：US08800936B2

公开(公告)日：2014-08-12

申请号：US13007515

申请日：2011-01-14

Applicant: Martyn Cowley ,  Matthew Todd Keennon

Inventor： Martyn Cowley ,  Matthew Todd Keennon

IPC: G05D1/00 ,  G05D1/06 ,  G05D1/12 ,  B64C11/08

CPC classification number: G05D1/0676 ,  B64C11/002 ,  B64C11/04 ,  B64C11/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/141 ,  B64C2201/187

Abstract: An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal.

Abstract translation: 一种空中飞行器，其构造成增加有效阻力，以经由传动轴转动方向反转（即，推力反转）来改变飞行中的空中飞行器的下降速率。

公开(公告)号：US20140110527A1

公开(公告)日：2014-04-24

申请号：US14126846

申请日：2011-06-17

Applicant: Robert L. Sing

Inventor： Robert L. Sing

IPC: B64D9/00

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

Abstract: The self-sustaining drone aircraft freight and observation system (5) comprises a fleet of jet-powered drone aircraft (10) designed to carry freight (12) only. The drones (10) operate from a separate airfield in outlying areas to decrease land costs and to avoid disturbing residential and business areas. Navigation is automated using guidance from GPS satellites (16), and the aircraft (10) can be assisted by a hydraulic catapult (13) during takeoff to reduce the fuel payload. The observation component (18) includes sensors that can observe weather conditions and emergency signals from boats, ships and other sources. The system (5) may include a large-scale energy production center and multi-acre vegetable, herb and flower production center (26). The energy production center includes solar panels (30), fuel cells (38), and batteries (44). Thus, the system (5) does not need to be connected to the public utility electrical grid.

Abstract translation: 自维持无人机飞机货运观察系统（5）包括一个仅用于运输（12）的喷气式无人机（10架）舰队。 无人机（10）从外围地区的独立机场运营，以降低土地成本，避免住宅和商业区域的不安。 导航使用GPS卫星（16）的指导进行自动化，飞机（10）可在起飞期间由液压弹射器（13）辅助以减少燃料有效载荷。 观察部件（18）包括能够观察船舶，船舶和其他来源的天气状况和紧急信号的传感器。 系统（5）可以包括一个大型能源生产中心和多英亩蔬菜，草药花卉生产中心（26）。 能源生产中心包括太阳能电池板（30），燃料电池（38）和电池（44）。 因此，系统（5）不需要连接到公共事业电网。

公开(公告)号：US08108085B2

公开(公告)日：2012-01-31

申请号：US13110692

申请日：2011-05-18

Applicant: Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

Inventor： Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

IPC: G06F17/00 ,  B64C13/00

CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract translation: 用于控制飞机飞行的系统具有传感器，接收器和数字控制系统，所有这些系统都携带在飞行器上。 传感器确定飞机相对于地球的位置和飞机的惯性运动。 接收器接收传送参考车辆相对于地球的位置和运动的传送数据。 控制系统使用来自传感器和接收器的数据来计算飞机相对于参考车辆的位置和速度，然后命令飞机上的飞行控制装置以维持选定位置和/或速度的方式操纵飞行器 相对于参考车辆。 该系统允许使用图形或触觉的用户界面。