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公开(公告)号：US09682774B2
公开(公告)日：2017-06-20
申请号：US14507313
申请日：2014-10-06
Applicant: Aurora Flight Sciences Corporation
Inventor： James Donald Paduano , Paul Nils Dahlstrand , John Brooke Wissler , Adam Woodworth
IPC: B64C13/16 , 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.
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公开(公告)号：US09650138B2
公开(公告)日：2017-05-16
申请号：US14882254
申请日：2015-10-13
Applicant: Flight of the Century, Inc.
Inventor： William M. Yates
CPC classification number: B64D3/00 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/104 , B64C2201/127 , B64C2201/187 , B64D33/00 , B64D39/00
Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, and method of deploying and retrieving secondary aircrafts.
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公开(公告)号：US09340299B2
公开(公告)日：2016-05-17
申请号：US13852315
申请日：2013-03-28
Applicant: William M. Yates , Robert Ussery , Byron Young
Inventor： William M. Yates , Robert Ussery , Byron Young
CPC classification number: B64D39/00 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64C2201/104 , B64C2201/127 , B64C2201/146 , B64C2201/187 , B64D5/00 , B64D27/24
Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of an unmanned aerial vehicle (UAV) flying independent of and in proximity to the electric aircraft. The electric aircraft and methods of operating and recharging same may involve establishing, in-flight, an electrical connection between the aircraft and the UAV flying in proximity to the aircraft and transferring electricity from an electricity source associated with the UAV to the aircraft through the electrical connection.
Abstract translation: 电动飞机，包括飞行中可充电电动飞机，以及运行电动飞机的方法，包括通过使用独立于飞机和附近飞行的无人飞机（UAV）对飞行中的电动飞机进行充电的方法。 电动飞机及其操作和再充电的方法可能涉及在飞行中建立飞机与飞行器附近飞行器之间的电气连接，并将电力从与UAV相关联的电源通过电气传输到飞行器 连接。
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公开(公告)号：US20160001878A1
公开(公告)日：2016-01-07
申请号：US14768476
申请日：2014-02-06
Applicant: NES&TEC CO.,LTD.
Inventor： Ki-Seong LEE
CPC classification number: B64C27/28 , B64C3/38 , B64C3/58 , B64C9/323 , B64C39/024 , B64C2201/088 , B64C2201/108 , B64C2201/185 , B64C2201/187
Abstract: Disclosed is an easy landing drone. The drone includes: a propeller changing direction; a propeller tower supporting the propeller; a body connected to the propeller tower; a main wing arranged left-right symmetrically with respect to a horizontal axis of the body and having a pair of holes around a center of gravity of the body; a pair of auxiliary wings disposed in the pair of holes, respectively; and an actuator connected to a base shaft fixed to the main wing through the pair of auxiliary wings and controlling angles of the pair of auxiliary wings.
Abstract translation: 披露了一个简单的降落无人机。 无人机包括：螺旋桨改变方向; 支撑螺旋桨的螺旋桨塔; 连接到螺旋桨塔的主体; 主翼相对于主体的水平轴对称地布置，并且具有围绕主体的重心的一对孔; 一对辅助翼分别设置在该对孔中; 以及致动器，其通过所述一对辅助翼连接到固定到所述主翼的基轴，并且控制所述一对辅助翼的角度。
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5.发明申请SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE 有权长寿命垂直起落架及吊车的系统，装置及方法公开(公告)号：US20150336663A1
公开(公告)日：2015-11-26
申请号：US14507313
申请日：2014-10-06
Applicant: Aurora Flight Sciences Corporation
Inventor： JAMES DONALD PADUANO , PAUL NILS DAHLSTRAND , JOHN BROOKE WISSLER , ADAM WOODWORTH
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。
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Patent Agency Ranking
公开(公告)号：US08951086B2
公开(公告)日：2015-02-10
申请号：US13954218
申请日：2013-07-30
Applicant: Aurora Flight Sciences Corporation
Inventor： Adam John Woodworth , James Peverill , Greg Vulikh , Jeremy Scott Hollman
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.
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7.发明申请SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR MANEUVERING OF AN AIR VEHICLE WITH TILTABLE PROPULSION UNIT 有权系统，方法和计算机程序产品，用于使用可倾斜的推进装置运行空中的车辆公开(公告)号：US20140339372A1
公开(公告)日：2014-11-20
申请号：US14372060
申请日：2013-01-10
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Guy Dekel , Lior Zivan , Yoav Efraty , Amit Wolff , Avner Volvoick
CPC classification number: B64C27/26 , B64C19/00 , B64C29/00 , B64C29/0033 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/086 , B64C2201/104 , B64C2201/162 , B64C2201/165 , B64C2201/187 , G05D1/0676 , G05D1/0858
Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units 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.
Abstract translation: 一种被配置为控制包括至少一个可倾斜推进单元的至少一个可倾斜推进单元的空中交通工具的减速过程的控制系统，所述至少一个可倾斜推进单元中的每一个可倾斜以提供其方向至少在一般的垂直推力矢量方向 和相对于空中车辆的总纵向推力向量方向。
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8.发明申请公开(公告)号：US20140284429A1
公开(公告)日：2014-09-25
申请号：US14274938
申请日：2014-05-12
Applicant: Aurora Flight Sciences Corporation
Inventor： ADAM WOODWORTH , Brandon Suarez
CPC classification number: B64C15/00 , B64C29/0033 , B64C39/02 , B64C39/028 , B64C2201/028 , B64C2201/042 , B64C2201/127 , B64C2201/18 , B64C2201/187 , B64C2201/201 , B64C2211/00
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 module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring 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 thrust vectoring 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。 飞机包括机身，连接到机身后部的一对翅片，连接到机身底部的一对二面支架，第一推力矢量模块和第二推力矢量模块以及电子模块。 电子模块向两个推力矢量模块提供命令。 两个推力矢量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。 使用直接铰接的电动机作为推力矢量模块使飞机能够在宽范围的空速下执行紧半径的转弯。
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公开(公告)号：US08464981B2
公开(公告)日：2013-06-18
申请号：US12931230
申请日：2011-01-26
Applicant: James Goldie , Nicholas Vitale , George A. Downey , Kevin Leary , William Hafer
Inventor： James Goldie , Nicholas Vitale , George A. Downey , Kevin Leary , William Hafer
IPC: B64F1/00
CPC classification number: B64F1/02 , B64C39/024 , B64C2201/021 , B64C2201/182 , B64C2201/187
Abstract: A UAV recovery system including a recovery cart; a guide mechanism for defining the path of the cart; a base station for capturing a UAV tailhook; a momentum transfer system driven by the inertia of the UAV through the arresting member to move the recovery cart along the guide mechanism away from the base station in the same direction as the UAV; an acceleration control device for converging the speeds and positions of the UAV and cart for enabling engagement of the cart and UAV as their relative speeds approach zero; and a brake system for stopping the recovery cart when the cart and UAV are engaged. Also disclosed is a UAV having a tailhook pivotably mounted on the UAV at the center of gravity of the UAV.
Abstract translation: 包括恢复车的无人机恢复系统; 用于限定推车路径的引导机构; 用于捕获无人机尾钩的基站; 动力传递系统由无人机通过阻挡构件的惯性驱动，以沿着与UAV相同的方向沿导向机构移动回收车辆远离基站; 加速控制装置，用于会聚无人机和推车的速度和位置，以使得能够在其相对速度接近零时使卡车和无人机接合; 以及用于在推车和UAV接合时停止回收车的制动系统。 还公开了一种具有可枢转地安装在无人机的重心的UAV上的尾钩的UAV。
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10.发明申请公开(公告)号：US20120181388A1
公开(公告)日：2012-07-19
申请号：US13007515
申请日：2011-01-14
Applicant: Martyn Cowley
Inventor： Martyn Cowley
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。
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