公开(公告)号：US09776715B2

公开(公告)日：2017-10-03

申请号：US15350458

申请日：2016-11-14

Applicant: Andrew H B Zhou ,  Dylan T X Zhou ,  Tiger T G Zhou

Inventor： Andrew H B Zhou ,  Dylan T X Zhou ,  Tiger T G Zhou

IPC: B64C35/00 ,  B60F5/02 ,  B64C29/00 ,  B64C39/02 ,  G05D1/04 ,  B64C37/00 ,  G05D1/08 ,  G08G5/04 ,  B60R11/04 ,  B60K16/00

CPC classification number: B64C35/008 ,  B60F5/02 ,  B60K16/00 ,  B60K2016/003 ,  B60R11/04 ,  B64C29/0033 ,  B64C29/0066 ,  B64C29/0075 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/141 ,  B64C2201/162 ,  G05D1/0816 ,  G05D1/0858 ,  G08G5/04

Abstract: An amphibious vertical takeoff and landing (VTOL) unmanned device is provided. The amphibious VTOL unmanned device includes a modular and expandable waterproof body, an outer body shell, a gimbaled swivel propulsion system comprising a plurality of VTOL jet engines and VTOL ducted fans, a processor, electronic speed controllers, a two-way telemetry device, a video transmitter, a radio control receiver, a power distribution board, an electrical machine, an onboard electricity generator comprising a plurality of solar cells, a light detection and ranging device, an ultrasonic radar sensor, a plurality of sensors, a tail configured to stabilize the amphibious VTOL unmanned device, a head VTOL ducted fan adapted for VTOL, a plurality of wheels, a plurality of foldable wings configured to create a pressure difference and creating a lift, a plurality of parachutes configured to safely land the amphibious VTOL unmanned device in an emergency.

公开(公告)号：US20170260973A1

公开(公告)日：2017-09-14

申请号：US15065185

申请日：2016-03-09

Applicant: Northrop Grumman Systems Corporation

Inventor： Gregory L. Larson ,  Peter A. Barnett

IPC: F03G7/06 ,  B64C3/56

CPC classification number: F03G7/065 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/102 ,  B64D5/00 ,  B64D7/00

Abstract: An exemplary rotational assembly includes a base having a circular collar and first and second arms that rotate about the circular collar in opposite angular directions. In a stored state the arms have substantially the same angle relative to the circular collar; in a deployed state the arms have rotated into opposing positions. Each end of a Nitinol wire is coupled to the first and second arms and contracts when heated by the flow of electrical current. This contraction causes the simultaneously application of a rotational force to the first and second arms causing the first and second arms to rotate about the circular collar in opposite angular directions. The simultaneous counter rotating angular forces during rotation of the arms causes no substantial change in angular inertia at the base.

公开(公告)号：US20170240276A1

公开(公告)日：2017-08-24

申请号：US15503470

申请日：2015-08-11

Applicant: ALMOG RESCUE SYSTEMS LTD.

Inventor： Ariel Zilberstein

IPC: B64C31/02 ,  A62C3/02 ,  B64D5/00 ,  B64D1/10 ,  B64C39/02 ,  B64D1/16

CPC classification number: B64C31/02 ,  A62C3/0242 ,  A62C3/025 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/201 ,  B64C2201/206 ,  B64D1/10 ,  B64D1/16 ,  B64D5/00

Abstract: A disposable unmanned aerial glider (UAG) with pre-determined UAG flight capabilities. The UAG comprises a flight module comprising at least one aerodynamic arrangement; and a fuselage module comprising a container configured for storing therein a payload and having structural integrity. The container is pressurized so as to maintain structural integrity thereof at least during flight, so that the UAG flight capabilities are provided only when the container is pressurized.

公开(公告)号：US09682774B2

公开(公告)日：2017-06-20

申请号：US14507313

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler ,  Adam Woodworth

IPC: B64C13/16 ,  B64C27/52 ,  B64C29/04 ,  B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C25/10 ,  B64D27/02 ,  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：US20170057630A1

公开(公告)日：2017-03-02

申请号：US15119812

申请日：2015-02-17

Applicant: IAT 21 INNOVATIVE AERONAUTICS TECHNOLOGIES GMBH

Inventor： Meinhard Schwaiger

IPC: B64C29/00 ,  B64C3/56 ,  B64C27/02 ,  B64C39/02 ,  B64D27/04 ,  B64D27/24 ,  B64C3/38 ,  B64C27/20

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/56 ,  B64C27/026 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026 ,  B64D2211/00

Abstract: The invention relates to an aircraft comprising a fuselage (1), a plurality of propeller units (3) that can pivot in relation to the fuselage (1), and wings (5) that can pivot at least partially in relation to the fuselage (1) and independently of the propeller units (3).

Abstract translation: 本发明涉及一种飞机，其包括机身（1），可相对于机身（1）枢转的多个螺旋桨单元（3）和能够相对于机身至少部分地枢转的翼（5） 1）并且独立于螺旋桨单元（3）。

公开(公告)号：US09561843B2

公开(公告)日：2017-02-07

申请号：US14942174

申请日：2015-11-16

Applicant: TUFTS UNIVERSITY

Inventor： Alfram V. Bright ,  Richard Wlezien

IPC: B64C3/30 ,  B64C3/56 ,  B64C39/02 ,  D06M10/00 ,  D06M10/10 ,  D06M15/327 ,  E04H12/00 ,  H05G2/00

CPC classification number: B64C3/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/127 ,  D06M10/001 ,  D06M10/10 ,  D06M15/327 ,  E04H12/00 ,  F03D13/20 ,  H05G2/00 ,  Y02E10/728

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements rapidly inflated and rigidized using an acrylic adhesive and UV light generated by combustion, which find use, for example, in rapidly deploying and supporting the wing of an aerial vehicle and wind turbine towers.

Abstract translation: 本发明提供了新颖的可膨胀和可固化的支撑元件，及其制造和使用方法。 特别地，本发明提供了使用丙烯酸粘合剂和由燃烧产生的UV光快速膨胀和刚性化的可膨胀和可固化的支撑元件，其可用于例如快速部署和支撑飞行器和风力涡轮机塔架的机翼。

公开(公告)号：US09541924B2

公开(公告)日：2017-01-10

申请号：US14737814

申请日：2015-06-12

Applicant: SUNLIGHT PHOTONICS INC.

Inventor： Sergey V. Frolov ,  John Peter Moussouris ,  Michael Cyrus

IPC: G05D1/10 ,  G05D1/00 ,  G05D1/02 ,  G05D1/06 ,  B64C37/02 ,  B64C3/56 ,  G08G5/00 ,  G08G7/02 ,  B64C29/00

CPC classification number: G05D1/104 ,  B64C3/56 ,  B64C29/0016 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/143 ,  B64C2201/145 ,  B64D1/02 ,  G05D1/0022 ,  G05D1/0027 ,  G05D1/005 ,  G05D1/0212 ,  G05D1/0669 ,  G05D1/102 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0017 ,  G08G5/0021 ,  G08G5/003 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025 ,  G08G5/045 ,  G08G7/02 ,  Y02T50/14

Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

Abstract translation: 本发明的实施例提供了一种替代的分布式机载运输系统。 在一些实施例中，一种用于分布式机载运输的方法包括：向机载车辆提供机翼和机翼跨度，具有携带乘客或货物中的一个或多个的能力; 机载车辆靠近一个或多个乘客或货物并装载至少一个乘客或货物; 起飞和确定机载飞行方向; 至少定位一个具有大致相同的飞行方向的其他机载车辆; 并将至少一个其他机载车辆接入飞行形成并形成一个舰队，其中机载车辆以相同的速度和方向飞行，并且相邻的机载车辆以小于100个翼跨的距离分开。

公开(公告)号：US09540103B2

公开(公告)日：2017-01-10

申请号：US14313680

申请日：2014-06-24

Applicant: Kitty Hawk Corporation

Inventor： Geoffrey A. Long

IPC: B64C27/00 ,  B64C39/02 ,  B64C27/32 ,  B64C27/24

CPC classification number: B64C39/024 ,  B64C27/24 ,  B64C27/32 ,  B64C2201/102 ,  B64C2201/108

Abstract: A vertical takeoff and landing aircraft includes rotors that provide vertical and horizontal thrust. During forward motion, the vertical lift system is inactive. A lift fan mechanism positions the fan blades of the aircraft in a collapsed configuration when the vertical lift system is inactive and positions the fan blades of the aircraft in a deployed configuration when the vertical lift system is active.

Abstract translation: 垂直起降飞机包括提供垂直和水平推力的转子。 在向前运动期间，垂直升降系统不起作用。 当垂直升降系统处于非活动状态时，升降风扇机构将飞行器的风扇叶片定位在折叠构型中，并且当垂直升降系统处于活动状态时将飞行器的风扇叶片定位在展开配置中。

公开(公告)号：US20160167781A1

公开(公告)日：2016-06-16

申请号：US14944482

申请日：2015-11-18

Applicant: AURORA FLIGHT SCIENCES CORPORATION

Inventor： ROBERT PARKS ,  ADAM WOODWORTH ,  TOM VANECK ,  JUSTIN MCCLELLAN

IPC: B64C37/00 ,  B64C39/02 ,  B63G8/00 ,  B63G8/08 ,  B60F5/02

CPC classification number: B64C37/00 ,  B60F5/02 ,  B63G8/001 ,  B63G8/08 ,  B63G2008/005 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  F42B15/20

Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

公开(公告)号：US20160122016A1

公开(公告)日：2016-05-05

申请号：US14528024

申请日：2014-10-30

Applicant: Ecole Polytechnique Federale De Lausanne (EPFL)

Inventor： Stefano Mintchev ,  Ludovic Daler ,  Dario Floreano

IPC: B64C39/02

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127

Abstract: An aerial vehicle including self-autonomous deployable arms and methods of deploying the vehicle are disclosed. The arms may include patterns located thereon that allow the arms to transition between wrapped, flat, and deployed configurations autonomously without the need for direct intervention by a user.

Abstract translation: 公开了一种包括自主部署臂的飞行器和部署车辆的方法。 臂可以包括位于其上的图案，其允许臂在包裹的，平坦的和部署的配置之间自主地转换，而不需要用户的直接干预。