公开(公告)号：US09708059B2

公开(公告)日：2017-07-18

申请号：US14625806

申请日：2015-02-19

Applicant: The United States of America 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 ,  B64C39/02 ,  B64C15/00

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.

公开(公告)号：US09688397B2

公开(公告)日：2017-06-27

申请号：US15204547

申请日：2016-07-07

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64D35/04 ,  B64D27/02 ,  B64C27/22 ,  B64C29/00 ,  B64C1/14 ,  B64C27/52 ,  B64C39/02 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/80 ,  B64D31/00 ,  B64C27/26 ,  B64C27/28 ,  B64C27/82 ,  B64D17/64

CPC classification number: B64C29/0033 ,  B64C1/1415 ,  B64C1/1476 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C27/82 ,  B64C29/00 ,  B64C29/0016 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64D31/00 ,  B64D35/04

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

公开(公告)号：US20170139421A1

公开(公告)日：2017-05-18

申请号：US15419814

申请日：2017-01-30

Applicant: Ford Global Technologies, LLC

Inventor： John A. Lockwood ,  Joseph F. Stanek

IPC: G05D1/02 ,  G08G1/01 ,  G05D1/00 ,  B64C39/02

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.

公开(公告)号：US20170113796A1

公开(公告)日：2017-04-27

申请号：US15397415

申请日：2017-01-03

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64C29/02 ,  B64D47/00 ,  H01Q1/42 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/18 ,  B64D47/00 ,  B64D47/08 ,  H01Q1/42

Abstract: An aircraft is provided and includes a single sensor and wings extending outwardly in opposite directions from a fuselage. Each wing includes a main section, an engine section supported on the main section and tail surfaces extending transversely relative to the main section. The single sensor is mountable to one of the tail surfaces with a field of view (FOV) representable as a spherical wedge having a dihedral angle exceeding 180°.

公开(公告)号：US20170057633A1

公开(公告)日：2017-03-02

申请号：US15152416

申请日：2016-05-11

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: 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.

公开(公告)号：US20170057632A1

公开(公告)日：2017-03-02

申请号：US15152413

申请日：2016-05-11

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: B64C29/02 ,  G05D1/08 ,  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：US20170057631A1

公开(公告)日：2017-03-02

申请号：US15332391

申请日：2016-10-24

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

Inventor： William J. FREDERICKS ,  Mark D. MOORE ,  Ronald C. BUSAN ,  Paul M. ROTHHAAR ,  David D. NORTH ,  William M. LANGFORD ,  Christopher T. LAWS ,  William T HODGES ,  Zachary R. JOHNS ,  Sandy R. WEBB

IPC: B64C29/00 ,  B64D27/24 ,  B64D27/26 ,  B64C5/02 ,  B64C11/28 ,  B64C25/52 ,  B64C39/02 ,  B64C3/38 ,  B64C11/50 ,  B64C9/14

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

Abstract translation: 提供了系统，方法和装置，其将先进的车辆配置（例如先进的飞行器配置）与电力推进的输注结合在一起，从而能够在保持完全垂直起飞和着陆的同时保持四倍的范围和耐力增加（“VTOL “）和车辆的悬停能力。 实施例可以提供具有垂直起落架和巡航高效能力的车辆，而不使用地面基础设施。 一种实施方式的车辆可以包括被配置为倾斜运动范围的翼，连接到翼的第一系列电动马达，并且每个被配置成驱动相关翼翼推进器，构造成在所述运动范围内倾斜的尾部，第二系列 耦合到尾部并且每个被配置成驱动相关联的尾部螺旋桨的电动马达以及连接到第一系列电动机和第二系列电动机的电动推进系统。

公开(公告)号：US09573674B1

公开(公告)日：2017-02-21

申请号：US15197763

申请日：2016-06-30

Applicant: Amazon Technologies, Inc.

Inventor： Liam Stewart Cavanaugh Pingree

IPC: B64C15/02 ,  B64C11/28 ,  B64C39/02 ,  B64C29/00

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：US09567075B2

公开(公告)日：2017-02-14

申请号：US14176960

申请日：2014-02-10

Applicant: Northrop Grumman Systems Corporation

Inventor： Thomas S. Tighe

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: A multi-engine aircraft is disclosed which is convertible from horizontal flight mode to a vertical flight mode. The aircraft comprises an aircraft fuselage defining a fuselage longitudinal axis, and the first and second wing attached to the fuselage. Each wing defines first and second wing segments. The first segments are translatable about the fuselage longitudinal axis, from a horizontal mode position adjacent the second wing segments to vertical fight mode wherein the first wing segment are substantially offset from the second wing segments. An aircraft propulsion unit is attached to each of the first and second wing segments. The propulsion units attached to a common wing being disposed in substantial axial alignment when the aircraft operates in a horizontal flight mode, and being substantially offset when the aircraft operates in a vertical flight mode. A sensor unit is connected to a forward portion of the fuselage.

Abstract translation: 公开了一种可从水平飞行模式转换为垂直飞行模式的多引擎飞机。 该飞机包括一个定义机身纵向轴线的飞机机身，以及连接到机身的第一和第二翼。 每个翼限定第一和第二翼段。 第一段可绕机身纵向轴线平移，从邻近第二翼段的水平模式位置到垂直起搏模式，其中第一翼段基本上偏离第二翼段。 飞机推进单元附接到第一和第二翼段中的每一个。 当飞机以水平飞行模式操作时，连接到共同翼的推进单元被布置成基本上轴向对准，并且当飞机以垂直飞行模式操作时基本上偏移。 传感器单元连接到机身的前部。

公开(公告)号：US20170029135A1

公开(公告)日：2017-02-02

申请号：US15292908

申请日：2016-10-13

Applicant: AeroVironment, Inc.

Inventor： Guan H. Su ,  Marcos Henry Rodriguez

IPC: B64F1/04 ,  B64C39/02 ,  F41B11/80

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。