公开(公告)号：US09409644B2

公开(公告)日：2016-08-09

申请号：US14333462

申请日：2014-07-16

Applicant: Ford Global Technologies, LLC

Inventor： Joseph F. Stanek ,  John A. Lockwood

IPC: B64C39/02 ,  G05D1/00 ,  B60R16/02 ,  G08C17/00

CPC classification number: G05D1/0276 ,  B60R16/02 ,  B60W30/00 ,  B64C29/0008 ,  B64C29/0091 ,  B64C29/02 ,  B64C39/00 ,  B64C39/02 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/02 ,  B64C2201/08 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/12 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/141 ,  B64C2201/18 ,  B64C2201/182 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/20 ,  B64C2201/208 ,  B64C2230/00 ,  G05D1/0022 ,  G05D1/0088 ,  G05D1/0094 ,  G05D1/0202 ,  G05D1/0212 ,  G05D1/0231 ,  G05D1/0242 ,  G05D1/0255 ,  G05D1/0257 ,  G05D1/028 ,  G05D2201/0213 ,  G08C17/00 ,  G08G1/012 ,  G08G1/091

Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.

Abstract translation: 本公开总体上涉及一种汽车无人机部署系统，该系统至少包括车辆和可部署的无人机，其配置为从车辆附接和分离。 更具体地，本公开描述了当车辆以自主驾驶模式操作时彼此保持通信的车辆和无人机交换信息，使得车辆在自主驾驶模式下的性能得到增强。

公开(公告)号：US20160179097A1

公开(公告)日：2016-06-23

申请号：US14901661

申请日：2013-06-24

Applicant: SINGAPORE TECHNOLOGIES AEROSPACE LTD ,  DSO NATIONAL LABORATORIES

Inventor： Chee Nam Chua ,  Junwei Choon ,  Kok Yong Lim

IPC: G05D1/06 ,  G05D1/00 ,  B64C25/32 ,  B64C39/02

CPC classification number: G05D1/0676 ,  B64C13/18 ,  B64C25/32 ,  B64C39/024 ,  B64C2201/146 ,  B64C2201/187 ,  G05D1/0011 ,  G05D1/0808

Abstract: Various embodiments provide a method for landing an unmanned aerial vehicle (UAV) in the presence of a wind. The method comprises: performing a first flare-maneuver whilst the UAV is flying. The flare-maneuver causes a front portion of the UAV to rise with respect to a rear portion of the UAV. The method also comprises steering the UAV along a path heading into a direction of the wind. The method further comprises performing a second flare-maneuver before the UAV impacts a landing surface to land. Various embodiments provide a corresponding UAV.

Abstract translation: 各种实施例提供了一种在存在风的情况下着陆无人驾驶飞行器（UAV）的方法。 该方法包括：在无人机飞行时执行第一次火炬弹。 火炬机动使无人机的前部相对于无人机的后部上升。 该方法还包括沿着朝向风向的路径转向无人机。 该方法还包括在UAV撞击着陆面到达之前进行第二次火炬弹。 各种实施例提供相应的无人机。

公开(公告)号：US20160031564A1

公开(公告)日：2016-02-04

申请号：US14882254

申请日：2015-10-13

Applicant: Flight of the Century, Inc.

Inventor： William M. YATES

IPC: B64D33/00 ,  B64C39/02

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.

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，包括为飞行中的电动飞机充电的方法，以及部署和检索二次飞机的方法。

公开(公告)号：US09169014B2

公开(公告)日：2015-10-27

申请号：US13569360

申请日：2012-08-08

Applicant: Andrew Charles Elson ,  Peter Davidson

Inventor： Andrew Charles Elson ,  Peter Davidson

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of launching a powered unmanned aerial vehicle at an altitude of at least 13,000 m, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, 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: 一种在至少13000米的高度上发射供电的无人驾驶飞行器的方法，该方法包括通过将空载承载装置从基本上地平面的位置附近提升到升高的高度，使车辆 当车辆相对于承载件的速度基本上为零时，车辆离开载体，然后车辆随着其高度减小到能够防止任何进一步下降并且可以开始独立的持续飞行的速度。

公开(公告)号：US09057609B2

公开(公告)日：2015-06-16

申请号：US13260471

申请日：2009-03-27

Applicant: Qifeng Yu ,  Zhihui Lei ,  Xiaohu Zhang ,  Yang Shang ,  Heng Zhang ,  Xiang Zhou

Inventor： Qifeng Yu ,  Zhihui Lei ,  Xiaohu Zhang ,  Yang Shang ,  Heng Zhang ,  Xiang Zhou

IPC: G01C11/00 ,  G01C21/10 ,  G05D1/06 ,  G08G5/02 ,  G08G5/00 ,  G01S5/16

CPC classification number: G01C11/00 ,  B64C2201/187 ,  G01C21/10 ,  G01S5/16 ,  G05D1/0676 ,  G08G5/0026 ,  G08G5/025

Abstract: A ground-based videometrics guiding method for aircraft landing or unmanned aerial vehicles recovery is provided. The method comprised the following steps: setting videos(1,2,3,4,5,6) near the landing area of the aircraft or unmanned aerial vehicles; real-time imaging the aircraft or unmanned aerial vehicles during their final approaches; and real-time measuring the trajectory, velocity, acceleration, post and other motion parameters of the aircraft or unmanned aerial vehicles by analyzing the video images and using videometrics technology, so as to provide guiding information for the aircraft landing or unmanned aerial vehicles recovery.

Abstract translation: 提供了一种用于飞机着陆或无人驾驶飞行器恢复的地面视觉数据指导方法。 该方法包括以下步骤：在飞机着陆区域或无人机上设置视频（1,2,3,4,5,6）; 在飞机或无人驾驶飞行器的最终进场期间实时成像; 并通过分析视频图像和使用视频数据技术实时测量飞机或无人机的轨迹，速度，加速度，后置等运动参数，为飞机着陆或无人机恢复提供指导信息。

公开(公告)号：US20140061384A1

公开(公告)日：2014-03-06

申请号：US13954278

申请日：2013-07-30

Applicant: Aurora Flight Sciences Corporation

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

IPC: B64C1/30

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.

公开(公告)号：US20130206921A1

公开(公告)日：2013-08-15

申请号：US13397569

申请日：2012-02-15

Applicant: James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler

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

IPC: B64C29/00

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.

公开(公告)号：US20130175390A1

公开(公告)日：2013-07-11

申请号：US13567015

申请日：2012-08-04

Applicant: Adam Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Hollman

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

IPC: B64D27/26 ,  B64C19/00 ,  B64D9/00

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：US20110248123A1

公开(公告)日：2011-10-13

申请号：US13140233

申请日：2009-12-01

Applicant: Abraham Abershitz

Inventor： Abraham Abershitz

IPC: B64C39/02 ,  B64C39/10 ,  B64C5/00

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187

Abstract: The present invention relates to an unmanned air vehicle (105), comprising a body having front (121) and rear (122) sections with at least one pair of end plates (110) connected to said body, wherein one end plate within said at least one pair of end plates is connected to the left side of said body and another end plate within said at least one pair of end plates is connected to the right side of said body, each end plate having upper and lower sections (111,112), wherein: a) said upper section is positioned above a mean line of said body; b) said lower section is positioned below said mean line of said body; and c) a ratio of the area of said upper section to the area of said lower section is less than 1.

Abstract translation: 本发明涉及一种无人驾驶飞行器（105），其包括具有前部（121）和后部（122）部分的主体，所述主体部分具有连接到所述主体的至少一对端板（110），其中，所述内部 至少一对端板连接到所述主体的左侧，并且在所述至少一对端板内的另一个端板连接到所述主体的右侧，每个端板具有上部和下部（111,112）， 其中：a）所述上部分位于所述主体的平均线之上; b）所述下部部分位于所述主体的平均线下方; 和c）所述上部区域与所述下部区域的面积之比小于1。

公开(公告)号：US20110057074A1

公开(公告)日：2011-03-10

申请号：US12556225

申请日：2009-09-09

Applicant: Adam Woodworth ,  Brandon Suarez

Inventor： Adam Woodworth ,  Brandon Suarez

IPC: G05D1/00 ,  B64C13/00

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。