公开(公告)号：US08967527B2

公开(公告)日：2015-03-03

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: B64C3/56 ,  B64C1/30 ,  B64D27/26 ,  B64D9/00 ,  B64C19/00 ,  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.

公开(公告)号：US20150021430A1

公开(公告)日：2015-01-22

申请号：US14507228

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

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

IPC: B64C3/42 ,  B64C25/10 ,  B64C9/00 ,  B64D27/02 ,  B64C5/02 ,  B64C29/00 ,  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.

公开(公告)号：US20140353432A1

公开(公告)日：2014-12-04

申请号：US14288203

申请日：2014-05-27

Applicant: AeroVironment, Inc.

Inventor： Martyn Cowley ,  Matthew Todd Keennon

IPC: B64C11/00 ,  B64C11/04

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：US08721383B2

公开(公告)日：2014-05-13

申请号：US12556225

申请日：2009-09-09

Applicant: Adam Woodworth ,  Brandon Suarez

Inventor： Adam Woodworth ,  Brandon Suarez

IPC: 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。

公开(公告)号：US20140061390A1

公开(公告)日：2014-03-06

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: B64C15/00

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：US08500067B2

公开(公告)日：2013-08-06

申请号：US13567015

申请日：2012-08-04

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

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

IPC: B64C1/32

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：US20120187243A1

公开(公告)日：2012-07-26

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: B64F1/02

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。

公开(公告)号：US20120104163A1

公开(公告)日：2012-05-03

申请号：US13200466

申请日：2011-09-23

Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Kyle D. Swanson ,  Robert F. Curtin

Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Kyle D. Swanson ,  Robert F. Curtin

IPC: B64D27/00

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere.

公开(公告)号：US20120075461A1

公开(公告)日：2012-03-29

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: H04N7/18

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

Abstract: The present invention provides a ground-based camera surveying and guiding method for aircraft landing and unmanned aerial vechicle recovery based on the camera surveying technology, which is a ground-based camera surveying and guiding system mainly including several video cameras arranged near the landing areas of an aircraft or an unmanned aerial vechicle. During the approaching process of the aircraft or the unmanned aerial vechicle, the system performs imaging of the aircraft in real time and detects movement parameters such as the track, velocity, acceleration, attitude and the offset relative to the glide slope of the aircraft or the unmanned aerial vechicle in real time by analyzing images and applying camera surveying method and technology, so as to provide guidance for aircraft landing or unmanned aerial vechicle recovery. The method is an autonomic guiding survey without interferences from others, which has high accuracy and reliability. The hardware devices are mature, simple and have low cost. The devices are moveable and versatile, and can be used in aircraft landing aid, unmanned aerial vechicle recovery and the like.

Abstract translation: 本发明提供了一种基于相机测量技术的飞机着陆和无人驾驶飞行器采集技术的地面摄像机测量和指导方法，该摄像机测量技术是一种基于地面的摄像机测量和指导系统，主要包括安装在着陆区附近的几台摄像机 飞机或无人驾驶飞机。 在飞行器或无人驾驶飞行器的接近过程中，系统实时执行飞行器的成像，并检测运动参数，例如轨道，速度，加速度，姿态和相对于飞行器的滑翔坡度的偏移量 通过分析图像和应用摄像机测量方法和技术实时实现无人驾驶飞行器，为飞机着陆或无人驾驶飞行器械恢复提供指导。 该方法是无干扰的自主指导调查，准确性和可靠性高。 硬件设备成熟，简单，成本低。 这些装置是可移动的和通用的，并且可以用于飞机着陆援助，无人驾驶空中飞行器恢复等。

公开(公告)号：US08028951B2

公开(公告)日：2011-10-04

申请号：US11973091

申请日：2007-10-05

Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Kyle D. Swanson ,  Robert F. Curtin

Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Kyle D. Swanson ,  Robert F. Curtin

IPC: B64D27/00

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.