公开(公告)号：US20170177006A1

公开(公告)日：2017-06-22

申请号：US15040985

申请日：2016-02-10

Applicant: AeroVironment, Inc.

Inventor： CHRISTOPHER EUGENE FISHER ,  Jason Sidharthadev Mukherjee ,  William Arden Lott ,  Eric James Aagaard

IPC: G05D1/10 ,  B64C29/02 ,  B64D47/08 ,  G05D1/00 ,  B60L11/18 ,  B64D1/02 ,  G08G5/00 ,  B64C39/02 ,  B64F1/22

CPC classification number: G05D1/102 ,  B60L11/1824 ,  B60L2200/10 ,  B60L2230/22 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/201 ,  B64D1/02 ,  B64D47/08 ,  B64F1/222 ,  G05D1/0088 ,  G06Q10/08 ,  G06T11/60 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0069 ,  G08G5/0091

Abstract: A method of migrating unmanned aerial vehicle (UAV) operations between geographic survey areas, including: uploading a first plurality of flight missions into a first UAV pod; deploying the UAV pod; autonomously launching the UAV from the UAV pod a plurality of times to perform the first plurality of flight missions; providing first survey data from the UAV to the UAV pod; autonomously migrating the UAV from the first UAV pod to a second UAV pod; receiving a second plurality of flight missions in a second UAV pod; providing the UAV with one of the second plurality of flight missions from the second UAV pod; autonomously launching the UAV from the second UAV pod a plurality of times to perform the second plurality of flight missions; and providing a second survey data from the UAV to the second UAV pod; where the autonomous migrating of the UAV to accomplish the first and second survey data happens autonomously and without active human intervention.

公开(公告)号：US20170066543A1

公开(公告)日：2017-03-09

申请号：US14845615

申请日：2015-09-04

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Russell M. SYLVIA

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/04 ,  B63G8/28 ,  B63G2008/008 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/088 ,  B64C2201/20 ,  B64C2201/201 ,  B64C2201/205

Abstract: A payload launch system that uses an inflatable air bag ram to launch a payload, such as an unmanned aerial vehicle, from a launch chamber of a launch tube. The air bag ram seals with the interior surface of the launch tube to isolate a dump valve that controls the flow of compressed gas from a gas storage chamber into the air bag ram. The air bag ram sealing with the interior surface of the launch tube isolates the dump valve, both pre-launch and post-launch, from any water or debris carried in with water in which the payload launch system is disposed

Abstract translation: 一种有效载荷发射系统，其使用可充气气囊冲压器从发射管的发射室发射有效载荷，例如无人驾驶飞行器。 气囊柱塞与发射管的内表面密封，以隔离一个排气阀，其将压缩气体从气体储存室流入气囊冲头。 与发射管内表面密封的气囊柱塞将排放阀（预发射和发射后）与运载有有效载荷发射系统的水携带的任何水或碎屑隔离

公开(公告)号：US20170057635A1

公开(公告)日：2017-03-02

申请号：US14843329

申请日：2015-09-02

Applicant: THE BOEING COMPANY

Inventor： James David Strayer

IPC: B64C39/02 ,  B64C5/06 ,  B64D1/02

CPC classification number: B64C39/024 ,  B63G3/04 ,  B63G2008/004 ,  B63G2008/008 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205

Abstract: A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.

Abstract translation: 无人机发射系统包括限定内部空腔的罐和位于收纳状态的内部空腔内的无人机。 无人机被配置为从罐排出并从收起状态转换到罐外部的展开状态。 一种用于发射无人机的方法，该方法包括将无人机处于收起状态，将其从罐中排出，将喷射器从罐排出，并且在喷射操作之后将无人机转换成展开状态。

公开(公告)号：US09567105B2

公开(公告)日：2017-02-14

申请号：US14722921

申请日：2015-05-27

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber

IPC: B64D47/08 ,  B64C29/02

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°.

Abstract translation: 设有飞机并且包括单个传感器和从机身向相反方向向外延伸的翼。 每个翼包括主部分，支撑在主部分上的发动机部分和相对于主部分横向延伸的尾部表面。 单个传感器可安装到一个尾部表面，其视场（FOV）可表示为具有超过180°的二面角的球形楔形物。

公开(公告)号：US09567088B2

公开(公告)日：2017-02-14

申请号：US14460013

申请日：2014-08-14

Applicant: SWIFT ENGINEERING, INC.

Inventor： Robert Godlasky ,  Nate Ogawa ,  Andrew Streett

IPC: B64D27/02 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

Abstract translation: 垂直起落飞行器包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持固定的方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到达基本水平的飞行路径的路径。

公开(公告)号：US20170008625A1

公开(公告)日：2017-01-12

申请号：US15164718

申请日：2016-05-25

Applicant: Orville Olm ,  Zenon Dragan

Inventor： Orville Olm ,  Zenon Dragan

IPC: B64C29/02 ,  B64C3/56 ,  B64C3/32 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/20 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.

Abstract translation: 垂直起飞和着陆（VTOL）无人驾驶飞机系统（UAS）可以通过折翼设计独特地实现垂直起降，同时还可以在机翼延伸时配置为动力飞行。 在具有扩展翼的动力飞行机构中，VTOL UAS可以保持受控的动力飞行作为双推杆的设计。 无人驾驶飞机系统可以以垂直起降飞行系统以零空速（或近零空速）起飞的姿态折叠起来，使用主发动机推力以及作为垂直起降飞机的向心推力来维持受控飞行。 从空中飞行任务飞行状态到动力飞行的空降过渡，反之亦然，可能使VTOL UAS在每个制度中持续控制飞行。

公开(公告)号：US20170001723A1

公开(公告)日：2017-01-05

申请号：US14860072

申请日：2015-09-21

Applicant: Kabushiki Kaisha TOPCON

Inventor： Atsushi Tanahashi

IPC: B64C29/00 ,  B64D47/08 ,  G06K9/00 ,  G05D1/10 ,  E02F9/26 ,  B64C39/02 ,  G05D1/00

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/145 ,  B64D47/08 ,  E02F9/205 ,  E02F9/2054 ,  E02F9/262 ,  G05D1/0011 ,  G05D1/0027 ,  G05D1/0094 ,  G05D1/102 ,  G05D2201/0202 ,  G06K9/00637

Abstract: A site management system includes an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight, a working vehicle working in a civil construction site, a shape detection sensor provided in the unmanned airplane to detect a shape of the civil construction site, and an external control apparatus that controls flight of the unmanned airplane, driving of the working vehicle, and driving of the shape detection sensor. The external control apparatus moves the unmanned airplane to an observation area by performing the high speed flight. Further, the external control apparatus detects a shape of the observation area by driving the shape detection sensor while performing the high speed flight or by driving the shape detection sensor while performing low speed flight by switching from the airplane mode to the VTOL mode.

Abstract translation: 现场管理系统包括可在飞行高速飞行模式和低速飞行的垂直起降模式之间切换的无人驾驶飞机，在民用建筑工地工作的作业车辆，设置在无人驾驶飞机中以检测形状的形状检测传感器 以及控制无人驾驶飞行的驾驶，工作车辆的驾驶和形状检测传感器的驱动的外部控制装置。 外部控制装置通过执行高速飞行将无人驾驶飞机移动到观察区域。 此外，外部控制装置通过在执行高速飞行的同时驱动形状检测传感器或者通过从飞机模式切换到垂直起动模式来执行低速飞行来驱动形状检测传感器来检测观察区域的形状。

公开(公告)号：US20160311553A1

公开(公告)日：2016-10-27

申请号：US15070599

申请日：2016-03-15

Applicant: Sikorsky Aircraft Corporation

Inventor： Mark R. Alber ,  Charles Gayagoy ,  Jeffrey Parkhurst ,  Glenn D. Tiongson

IPC: B64D39/04 ,  B64C39/02 ,  B64C11/28 ,  B64D41/00 ,  B64C25/36 ,  B64C25/04 ,  B64D37/04 ,  B64C29/02 ,  B64C23/06

CPC classification number: B64D39/04 ,  B64C3/56 ,  B64C11/28 ,  B64C23/072 ,  B64C25/04 ,  B64C27/50 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/063 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64D7/00 ,  B64D37/04 ,  B64D37/16 ,  B64D39/00 ,  B64D41/00 ,  B64D2041/002 ,  Y02T50/164 ,  Y02T50/44

Abstract: An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations.

Abstract translation: 提供飞机并且包括机身，从机身的相对侧向外延伸的第一和第二翼，可操作地设置在第一和第二翼中的每一个上的推进器，以驱动垂直起飞和着陆飞机操作和水平飞行飞行器操作，以及 加油系统，包括设置在机身，第一翼或第二翼中的至少一个或多个中的至少一个燃料箱和加油装置。 加油装置联接到至少一个燃料箱，使得燃料在飞机地面和空中操作期间相对于至少一个燃料箱可移动。

公开(公告)号：US20160244159A1

公开(公告)日：2016-08-25

申请号：US14862134

申请日：2015-09-22

Applicant: Transition Robotics, Inc.

Inventor： JoeBen Bevirt

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C15/00 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in least two dimensions relative to the horizontal during takeoff. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the wings of the vehicle for takeoff and landing.

Abstract translation: 一种适用于垂直起飞和着陆的载人/无人机，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其通过交替发动机的推力来控制起飞和着陆期间车辆的姿态，发动机的推力在起飞期间相对于水平线至少二维分开。 一种飞行器，其使用彼此固定关系并且相对于车辆的翼部旋转以便起飞和着陆的发动机的旋转平台。

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。