公开(公告)号：US20170327218A1

公开(公告)日：2017-11-16

申请号：US15535309

申请日：2015-12-11

Applicant: Universite Pierre et Marie Curie (UPMC) ,  Centre National de la Recherche Scientifique

Inventor： Pascal Morin ,  Olivier Gaste ,  Duckien Phung

IPC: B64C29/00 ,  B64C3/38 ,  B64C39/02 ,  B64C13/28 ,  B64C27/26

CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  Y02T50/14

Abstract: A light unmanned vertical take-off aircraft includes at least two fixed coplanar propulsion devices and at least one wing providing the lift for the drone. The coplanar propulsion devices and the wing are each laid out on the frame of the drone so that the plane of the profile chord line of the wing is substantially parallel to the plane defined by the two coplanar propulsion devices. The wing is pivotingly mobile relative to the frame along an axis parallel to the pitch axis of the drone. Also a method is provided for controlling orientation of a wing of a light unmanned vertical take-off aircraft as described here above. The method includes controlling an orientation of a wing as a function of at least one flight parameter of the aircraft.

公开(公告)号：US09771162B1

公开(公告)日：2017-09-26

申请号：US15163977

申请日：2016-05-25

Applicant: Amazon Technologies, Inc.

Inventor： Nicholas Kristofer Gentry

IPC: B64D35/08 ,  B64C39/02 ,  B64D27/24 ,  G05D1/04 ,  G08G5/00 ,  B64D27/02

CPC classification number: B64D35/08 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/145 ,  B64D27/24 ,  B64D2027/026 ,  G05D1/042 ,  G08G5/006 ,  Y10S903/93

Abstract: An unmanned aerial vehicle (“UAV”) is configured with a redundant power generation system on-board the UAV. A redundant power system on-board the UAV can selectively utilize an auxiliary power source during operation and/or flight of the UAV. The power system on-board the UAV may include a battery and at least one auxiliary power source comprising a combustion engine. The combustion engine on-board the UAV may be selectively operated to charge the battery when a charge level of the battery is below a full charge level, and/or to power one or more propeller motors of the UAV.

公开(公告)号：US20170267376A1

公开(公告)日：2017-09-21

申请号：US15165616

申请日：2016-05-26

Applicant: X Development LLC

Inventor： Joseph Charles Benedetto ,  Olivia Hatalsky ,  John Frederick Udall ,  Liang-Shian Chen ,  Chase R. Haegele ,  Daniel Patrick Bowen ,  C.O. Lee Boyce, JR. ,  Shane Washburn ,  Keegan Gartner

IPC: B64F1/04 ,  B64F1/36 ,  B64B1/58

CPC classification number: B64F1/04 ,  B64B1/005 ,  B64B1/40 ,  B64B1/58 ,  B64C2201/022 ,  B64C2201/088 ,  B64C2201/122 ,  B64F1/14 ,  B64F1/36

Abstract: A portable launch rig (PLR) may include a support structure including two side supports defining an interior space for lifting and filling a balloon envelope of a balloon. Wheels on each of the side supports enable the PLR to be moved in various directions in order to prepare the PLR for launching the balloon. The side supports are connected by a lateral support beam having a pair of cranes arranged thereon. Each crane has an arm arranged over the interior space that is connected to a spreader beam. The spreader beam includes a lift assembly configured to lift and inflate the balloon envelope within the interior space. The PLR includes a platform and perch for supporting and moving the balloon envelope. A door assembly of the PLR includes a plurality of hangar doors configured to block wind from a respective direction of each hangar door entering the interior space.

公开(公告)号：US20170197731A1

公开(公告)日：2017-07-13

申请号：US15090597

申请日：2016-04-04

Applicant: ZEROTECH (Shenzhen) Intelligence Robot Co., Ltd.

Inventor： Jianjun Yang ,  Hongtao Sun

IPC: B64F1/04 ,  G05D1/00 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0016 ,  G05D1/0669

Abstract: A method for hand launching an unmanned aerial vehicle (UAV) includes detecting a first motion state of the UAV via a sensor, and controlling the UAV to enter into a launch mode according to the detected first motion state; and detecting a second motion state of the UAV via the sensor after the UAV enters into the launch mode, and controlling whether or not to activate a flight system of the UAV according to the detected second motion state.

公开(公告)号：US09694906B1

公开(公告)日：2017-07-04

申请号：US15132107

申请日：2016-04-18

Applicant: KING SAUD UNIVERSITY

Inventor： Shereef Aly Sadek

IPC: B64C29/00 ,  B64C39/08 ,  B64C39/02 ,  B64C25/10 ,  B64C5/06

CPC classification number: B64C29/00 ,  B64C5/06 ,  B64C25/10 ,  B64C29/0075 ,  B64C39/024 ,  B64C39/08 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/187

Abstract: The vertical takeoff and landing unmanned aerial vehicle includes a pair of selectively rotatable ducted fans and a selectively rotatable thrust vectoring nozzle providing vertical takeoff and landing for an unmanned aerial vehicle or a similar type of aircraft. A pair of fixed forward-swept wings are mounted on a rear portion of a fuselage, and a pair of canards are mounted on a top end of a forward portion of the fuselage. The pair of ducted fans are respectively mounted on free ends of the pair of canards, and are selectively rotatable about an axis parallel to a pitch axis of the fuselage. An engine is mounted in the rear portion of the fuselage, and a thrust vectoring nozzle is mounted on the rear portion of the fuselage for directing thrust exhaust from the engine. The thrust vectoring nozzle is selectively rotatable about an axis parallel to the pitch axis.

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。