公开(公告)号：US09567071B1

公开(公告)日：2017-02-14

申请号：US15152416

申请日：2016-05-11

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: B64C29/00 ,  B64C29/02 ,  G05D1/08 ,  G05D1/10 ,  B64C11/00

CPC classification number: B64C29/02 ,  B64C11/001 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162 ,  G05D1/0858 ,  G05D1/102

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract translation: 飞机包括机身，机翼，风扇和控制器。 机翼和管道风扇耦合到机身。 控制器可操作以以垂直飞行模式，水平飞行更多地控制飞行器，并且将飞行器从垂直飞行模式转换到水平飞行模式。

公开(公告)号：US09555885B2

公开(公告)日：2017-01-31

申请号：US15231579

申请日：2016-08-08

Applicant: Ford Global Technologies, LLC

Inventor： Joseph F. Stanek ,  John A. Lockwood

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

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：US09505493B2

公开(公告)日：2016-11-29

申请号：US14222158

申请日：2014-03-21

Applicant: Brandon Borko

Inventor： Brandon Borko

IPC: B64F1/06 ,  B64C39/02 ,  B64F1/02 ,  B64F1/12 ,  G05D1/10 ,  B64F1/22

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/20 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06 ,  B64F1/12 ,  B64F1/222 ,  G05D1/101

Abstract: A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and/or payload capacity.

Abstract translation: 一种用于促进自主着陆和起飞的自动着陆和起飞的系统，其具有在固定或移动着陆地点的协作车身，以及与着陆和起飞机构结合使用的自动存储系统，其存储和服务多个UAV 被描述。 该系统的主要特征在于，着陆机构可设置为具有卷轴，俯仰，偏航以及x，y和z的6个轴线，并与飞行中的空中车辆对准并截取，并相对于车辆的惯性极限使车辆减速。 飞行器和捕获机构设置有发射器和接收器，以协调车辆优先级，着陆机构和机动车辆之间的距离和角度。 着陆和起飞系统具有实时跟踪无人机的位置和方向的方法。 着陆机构将基本上与机动车辆的底座对准。 对于小型无人机，起重能力有限。 通过使着陆板执行着陆操作的精确调整来减少感测和计算要求，可以增加飞行时间和/或有效载荷。

公开(公告)号：US20160311529A1

公开(公告)日：2016-10-27

申请号：US15104614

申请日：2014-12-17

Applicant: Neva Aerospace, Ltd.

Inventor： David Brotherton-Ratcliffe ,  Laurent Martin

IPC: B64C29/00 ,  B64C27/20 ,  B64C37/02 ,  B64C39/02 ,  B64D35/06 ,  G05D1/00 ,  G08G5/00 ,  B64D27/10 ,  B64D35/04 ,  B64D27/24 ,  B64C27/30 ,  G01C21/16

CPC classification number: B64C29/0033 ,  B64C27/20 ,  B64C27/30 ,  B64C37/02 ,  B64C39/024 ,  B64C2027/8227 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2211/00 ,  B64D27/10 ,  B64D27/24 ,  B64D35/04 ,  B64D35/06 ,  B64D2041/002 ,  G01C21/16 ,  G05D1/0088 ,  G08G5/0034

Abstract: A VTOL aircraft is disclosed comprising a plurality of autonomous lifting modules wherein each autonomous lifting module is composed of a physical structure in which are mounted one or more electric ducted fans, an electrical energy storage system to drive the electric ducted fans, a charging and energy storage monitoring system to charge and monitor the electrical energy storage system, an inertial navigation system, electronic speed controllers to control the electric ducted fans and one or more microcomputers assuring (a) module flight stability by control of the electric ducted fans given the input of the inertial navigation system, (b) flight planning and (c) inter-module communication.

Abstract translation: 公开了一种VTOL飞机，其包括多个自主提升模块，其中每个自动提升模块由物理结构组成，其中安装有一个或多个电风扇，用于驱动电风扇的电能存储系统，充电和能量 存储监控系统，用于对电能存储系统进行充电和监测，惯性导航系统，电子速度控制器，用于控制电风扇和一个或多个微型计算机，确保（a）通过控制电风扇的模块飞行稳定性， 惯性导航系统，（b）飞行计划和（c）模块间通信。

公开(公告)号：US09470477B2

公开(公告)日：2016-10-18

申请号：US14281680

申请日：2014-05-19

Applicant: AeroVironment, Inc.

Inventor： Guan H Su ,  Marcos Henry Rodriguez

IPC: F41F3/00 ,  B64C39/02 ,  B64F1/06 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。

公开(公告)号：US20160272315A1

公开(公告)日：2016-09-22

申请号：US14625806

申请日：2015-02-19

Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Michael J. Logan ,  Mark A. Motter ,  Richard Deloach ,  Thomas L. Vranas ,  Joseph M. Prendergast ,  Brittney N. Lipp

IPC: B64C39/00 ,  B64C29/00 ,  B64C39/02 ,  B64C39/08 ,  B64C27/82 ,  B64C5/06

CPC classification number: B64C39/005 ,  B64C15/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/165

Abstract: Systems, methods, and devices are provided that enable robust operations of a small unmanned aircraft system (sUAS) using a compound wing. The various embodiments may provide a sUAS with vertical takeoff and landing capability, long endurance, and the capability to operate in adverse environmental conditions. In the various embodiments a sUAS may include a fuselage and a compound wing comprising a fixed portion coupled to the fuselage, a wing lifting portion outboard of the fixed portion comprising a rigid cross member and a controllable articulating portion configured to rotate controllable through a range of motion from a horizontal position to a vertical position, and a freely rotating wing portion outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion.

Abstract translation: 提供了系统，方法和设备，其使得能够使用复合翼的小型无人飞行器系统（sUAS）的鲁棒操作。 各种实施例可以提供具有垂直起飞和着陆能力，长期耐久性和在不利环境条件下操作的能力的sUAS。 在各种实施例中，一个sUAS可以包括一个机身和一个复合机翼，它包括一个与机身相连的固定部分，固定部分外侧的机翼提升部分包括一个刚性横梁和一个可控制的铰接部分， 从水平位置到垂直位置的运动，以及在所述机翼提升部分的外侧自由旋转的翼部，并且被构造成基于入射到所述自由旋转的翼部上的风力而自由旋转。

公开(公告)号：US09409642B1

公开(公告)日：2016-08-09

申请号：US14749299

申请日：2015-06-24

Applicant: Amazon Technologies, Inc.

Inventor： Liam Stewart Cavanaugh Pingree

IPC: B64C15/02 ,  B64C11/28 ,  B64C39/02

CPC classification number: B64C11/28 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141

Abstract: Aerial vehicles may be equipped with collapsible lift propellers and thrust propellers. The collapsible lift propellers may include retractable tips that may pivot or rotate from a first orientation substantially co-aligned with a main body of the collapsible lift propellers during ordinary operations and a second orientation substantially transverse to the main body of the collapsible lift propellers when rotation of the collapsible lift propellers is stopped. The collapsible lift propellers may further include biasing elements, e.g., springs for biasing the retractable tips into the second orientation, and mechanical stops for inhibiting the pivoting or rotation of the retractable tips beyond the first orientation.

Abstract translation: 空中车辆可能配备有可折叠提升螺旋桨和推力螺旋桨。 可折叠提升螺旋桨可以包括可伸缩的尖端，其可以在正常操作期间从与可折叠提升螺旋桨的主体基本上共同对准的第一定向枢转或旋转，并且当旋转时基本上横向于可折叠提升螺旋桨的主体的第二取向 的可拆卸提升螺旋桨停止。 可折叠提升螺旋桨还可以包括偏置元件，例如用于将可缩回尖端偏压到第二方向的弹簧，以及用于阻止可伸缩尖端的枢转或旋转超过第一定位的机械止动件。

公开(公告)号：US20160214712A1

公开(公告)日：2016-07-28

申请号：US14706905

申请日：2015-05-07

Applicant: AEROVIRONMENT, INC.

Inventor： CHRISTOPHER EUGENE FISHER ,  JASON SIDHARTHADEV MUKHERJEE ,  WILLIAM ARDEN LOTT ,  PAVEL BELIK ,  BART DEAN HIBBS

IPC: B64C29/00 ,  B64C27/54 ,  B64C27/26 ,  B64D27/24 ,  B64C11/32 ,  B64C27/605

CPC classification number: B64C29/0025 ,  B64C11/32 ,  B64C27/26 ,  B64C27/54 ,  B64C27/605 ,  B64C29/00 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  G05D1/0858

Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.

公开(公告)号：US20160159468A1

公开(公告)日：2016-06-09

申请号：US14562934

申请日：2014-12-08

Applicant: The Boeing Company

Inventor： John H. Harris, III ,  Daniel I. Newman

IPC: B64C25/14 ,  B64C25/52 ,  B64C25/66 ,  B64C25/36

CPC classification number: B64C25/14 ,  B64C25/36 ,  B64C25/52 ,  B64C25/66 ,  B64C29/0025 ,  B64C2201/088

Abstract: A multi-position landing gear for an aircraft may include a first landing skid disposed on a bottom side of the aircraft, and a second landing skid disposed on one of a top side or the bottom side of the aircraft, wherein the first landing skid and the second landing skid are rotatable relative to the aircraft.

Abstract translation: 用于飞行器的多位置起落架可以包括设置在飞行器的底侧上的第一登陆滑行装置和设置在飞行器的顶侧或底侧中的一个上的第二着陆滑架，其中第一着陆滑行和 第二个着陆防滑装置相对于飞行器是可旋转的。

公开(公告)号：US20160096613A1

公开(公告)日：2016-04-07

申请号：US14849814

申请日：2015-09-10

Applicant: Jonathon Thomas Johnson ,  Elizabeth V.M. Johnson

Inventor： Jonathon Thomas Johnson ,  Elizabeth V.M. Johnson

IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64C25/34 ,  B64C25/10

CPC classification number: B64C39/024 ,  B64C25/32 ,  B64C29/04 ,  B64C2025/325 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/16 ,  B64C2201/18

Abstract: Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.

Abstract translation: 目前的飞机技术包括固定翼，多转子和矢量引擎设计。 固定翼技术和矢量引擎技术的综合已经实施，但仅限于传统的固定翼设计飞机。 所提出的飞机设计具有机身预期的创新，改进的矢量引擎设计系统和起落架系统。