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：US20170201738A1

公开(公告)日：2017-07-13

申请号：US15176229

申请日：2016-06-08

Applicant: Alberto Daniel Lacaze ,  Karl Nicholas Murphy ,  Raymond Paul Wilhelm, III

Inventor： Alberto Daniel Lacaze ,  Karl Nicholas Murphy ,  Raymond Paul Wilhelm, III

IPC: H04N13/02 ,  G01S17/93 ,  G01S7/481 ,  B64D47/08 ,  H04N5/232 ,  B64C39/02 ,  B64C27/08 ,  G01S17/89 ,  G01S17/02

CPC classification number: H04N13/243 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/14 ,  B64C2201/162 ,  G01B11/245 ,  G01B11/2518 ,  G01B11/2545 ,  G01S7/4813 ,  G01S7/4815 ,  G01S7/4816 ,  G01S17/08 ,  G01S17/42 ,  G01S17/48 ,  G01S17/89 ,  G01S17/933 ,  H04N13/128 ,  H04N13/254 ,  H04N13/271 ,  H04N2013/0081

Abstract: Structured light approaches utilize a laser to project features, which are then captured with a camera. By knowing the disparity between the laser emitter and the camera, the system can triangulate to find the range. Four, 185 degree field-of-view cameras provide overlapping views over nearly the whole unit sphere. The cameras are separated from each other to provide parallax. A near-infrared laser projection unit sends light out into the environment, which is reflected and viewed by the cameras. The laser projection system will create vertical lines, while the cameras will be displaced from each other horizontally. This relative shift of the lines, as viewed by different cameras, enables the lines to be triangulated in 3D space. At each point in time, a vertical stripe of the world will be triangulated. Over time, the laser line will be rotated over all yaw angles to provide full a 360 degree range.

公开(公告)号：US09688400B2

公开(公告)日：2017-06-27

申请号：US14526790

申请日：2014-10-29

Applicant: QUALCOMM Incorporated

Inventor： Donald Bolden Hutson

IPC: B64C37/00 ,  B64C39/02 ,  B60F5/02 ,  F41H11/12 ,  F41H11/28

CPC classification number: B64C39/024 ,  B60F5/02 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  F41H11/12 ,  F41H11/28

Abstract: Unmanned aerial vehicles and methods for providing the same are disclosed. The unmanned aerial vehicles may have various configurations related to a support frame. The unmanned aerial vehicles may have various configurations with a continuous track for ground propulsion. The unmanned aerial vehicles may have various configurations related to payload clamps.

公开(公告)号：US09688398B2

公开(公告)日：2017-06-27

申请号：US14643857

申请日：2015-03-10

Applicant: DZYNE Technologies, Inc.

Inventor： Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

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：US09630710B2

公开(公告)日：2017-04-25

申请号：US14527674

申请日：2014-10-29

Applicant: QUALCOMM Incorporated

Inventor： Donald Bolden Hutson

IPC: B64C37/00 ,  B64D1/22 ,  B64C25/38 ,  B60F5/02 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64C37/00 ,  B60F5/02 ,  B64C25/38 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/22

Abstract: Unmanned aerial vehicles and methods for providing the same are disclosed. The unmanned aerial vehicles may have various configurations related to a support frame. The unmanned aerial vehicles may have various configurations with a continuous track for ground propulsion. The unmanned aerial vehicles may have various configurations related to payload clamps.

公开(公告)号：US20170101180A1

公开(公告)日：2017-04-13

申请号：US15391517

申请日：2016-12-27

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64C39/02 ,  B64C1/26 ,  B64D17/80

CPC classification number: B64C39/024 ,  B64C1/26 ,  B64C3/56 ,  B64C2201/104 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203 ,  B64D17/00 ,  B64D17/80

Abstract: A remotely controlled or autonomously controlled UAV is disclosed. The UAV has both wings and a deployable parachute to enable both fixed wing flight and paraglider flight. The UAV can fly at a higher speed to a mission area as a fixed wing craft, and loiter over the area as a powered paraglider. In some embodiments, the wings are jettisoned over the mission area and the UAV configured as a powered paraglider completes its mission. In other embodiments the UAV flies to the mission area as a fixed wing craft, deploys the parachute to loiter as a powered paraglider and then jettisons the parachute to fly under a fixed wing back to a base. The former embodiment cannot fly back to a base, they may be used to carry and deploy bombs or grenades, while the latter may be used for surveillance, deliver supplies or the like.

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：US20160325834A1

公开(公告)日：2016-11-10

申请号：US15149972

申请日：2016-05-09

Applicant: Curtis Asa Foster

Inventor： Curtis Asa Foster

IPC: B64C39/02 ,  B64D27/24 ,  B64C27/14

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/066 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24

Abstract: An in-flight battery recharging system for Unmanned Aerial Vehicle (UAV). This invention converts byproducts of a multi-rotor unmanned aerial vehicle's conventional propulsion system operation and airframe movements to generate electricity that, in turn, is used to power the propulsion system's electric motors, power onboard electronic components, and recharge the battery that initially powers the propulsion system's electric motors. Having this ability of recharging the battery in-flight gives an unmanned aerial vehicle a much improved flight time and range, thereby greatly increasing its utility.

Abstract translation: 无人机（UAV）的飞行中电池充电系统。 本发明转化了多转子无人驾驶飞行器的常规推进系统操作和机身运动的副产物，以产生电力，其又被用于为推进系统的电动机提供动力，并且对电子组件进行动力，以及对最初为 推进系统的电动机。 在飞行中为电池充电的能力给无人驾驶飞行器提供了大大改进的飞行时间和范围，从而大大提高了其效用。

公开(公告)号：US20160311528A1

公开(公告)日：2016-10-27

申请号：US15089576

申请日：2016-04-03

Applicant: Skylift Global

Inventor： Reza Nemovi ,  Robert Bartlett

IPC: B64C27/82 ,  B64C27/80 ,  B64C29/00 ,  B64C39/02 ,  B64C27/625 ,  B64C27/52 ,  B64C27/08

CPC classification number: B64C27/82 ,  B64C27/08 ,  B64C27/14 ,  B64C27/28 ,  B64C27/52 ,  B64C27/68 ,  B64C27/80 ,  B64C29/0033 ,  B64C39/024 ,  B64C2027/8209 ,  B64C2027/8254 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165

Abstract: An improved vehicle with superior performance and reliability. The vehicle, such as an unmanned aerial vehicle, is capable of vertical takeoff and landing, uses three swashless, variable-pitch vertical lift main rotors with a yaw tail rotor system. Two rear main rotors are optionally tiltrotors, which pivot to increase forward speed without the increased coefficient of drag inherent in tilting the entire vehicle. The three main rotors are positioned in an equilateral triangular configuration, improving balance, increasing load-bearing strength, and making it more compact in size. Movements are controlled through changes in pitch of the rotors, allowing the motors to maintain constant governed rotations per minute, maximizing drivetrain efficiency. Vehicle configurations disclosed herein allow for smaller vehicle size with greater performance than prior art vehicles.

Abstract translation: 具有优异性能和可靠性的改进型车。 诸如无人驾驶飞行器的车辆能够垂直起飞和着陆，使用具有偏航尾部转子系统的三个无斜杠，可变俯仰垂直升降主转子。 两个后部主转子是可选的倾斜旋转器，其枢转以增加前进速度，而不会在整个车辆倾斜时固有的增加的阻力系数。 三个主转子位于等边三角形结构中，改善了平衡，增加了承载力，并使其尺寸更加紧凑。 通过转子间距的变化来控制运动，允许电机每分钟保持恒定的转动旋转，从而最大限度地提高传动系效率。 本文公开的车辆配置允许具有比现有技术车辆更大的性能的较小车辆尺寸。