公开(公告)号：US20160368590A1

公开(公告)日：2016-12-22

申请号：US15052699

申请日：2016-02-24

Applicant: Karem Aircraft, Inc.

Inventor： Abe Karem ,  Benjamin Tigner

IPC: B64C3/42 ,  B64C39/02 ,  B64D27/24 ,  B64F5/00 ,  G05D1/00

CPC classification number: B64C3/42 ,  B64C3/16 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/165 ,  B64D27/24 ,  B64D2211/00 ,  B64F5/10 ,  G05D1/0011 ,  G05D1/0088 ,  H02S10/40 ,  H02S20/30 ,  H02S40/38 ,  Y02T50/12 ,  Y02T50/44 ,  Y02T50/62

Abstract: Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network.

Abstract translation: 描述了制造和操作具有分段翼的太阳能飞行器的方法，其可在飞行期间重新配置以优化太阳能收集。 飞机具有刚性结构，耐恶劣天气，并配置为依靠高空和常规条件下的自由飞行控制，从而提供超过2个月的飞行时间。 该飞机特别适合用作电信网络的一部分。

公开(公告)号：US09505484B1

公开(公告)日：2016-11-29

申请号：US15096216

申请日：2016-04-11

Applicant: Nasser M. Al-Sabah

Inventor： Nasser M. Al-Sabah

IPC: B64C3/38 ,  B64C13/00 ,  B64C9/00 ,  B64C13/20 ,  B64C9/32 ,  B64D27/02 ,  B64C3/34 ,  B64D47/08 ,  B64D15/00 ,  B64C39/02 ,  B64D37/00 ,  B64D27/14 ,  B64D27/20

CPC classification number: B64C3/38 ,  B64C1/26 ,  B64C3/34 ,  B64C5/06 ,  B64C9/00 ,  B64C9/326 ,  B64C13/00 ,  B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/063 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/16 ,  B64C2201/165 ,  B64C2211/00 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D37/00 ,  B64D39/00 ,  B64D47/08 ,  Y02T50/32

Abstract: The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle.

Abstract translation: 模块化飞机系统包括具有永久安装的尾翼和多组翼模块和发动机模块的单个机身，每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身和每个模块配置为快速拆卸和安装模块，以最大限度地减少飞机的停机时间。 在具有较高耐久性和/或重量承载能力的情况下，为相对高速飞行提供具有相对较低纵横比的短翼。 为长距离和耐力航班提供高长宽比的长翼，速度并不是绝对重要的。 还提供了中跨翼模块。 提供涡轮螺旋桨发动机，单涡轮喷气发动机和双涡轮喷气发动机模块用于安装，具体取决于任何给定航班的任务要求。 该飞机主要适用于自主操作或远程操作的无人驾驶飞行器。

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。

公开(公告)号：US20160257401A1

公开(公告)日：2016-09-08

申请号：US14635743

申请日：2015-03-02

Applicant: Amazon Technologies, Inc.

Inventor： Daniel Buchmueller ,  Scott A. Green ,  Atishkumar Kalyan ,  Gur Kimchi

IPC: B64C39/02 ,  G08G5/00

CPC classification number: B64C39/024 ,  B64C2201/128 ,  B64C2201/14 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/20 ,  B64C2201/208 ,  G01C21/3423 ,  G01C21/343 ,  G06Q10/047 ,  G06Q10/083 ,  G06Q50/28 ,  G06Q50/30 ,  G08G5/0013 ,  G08G5/0039 ,  G08G5/0056 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025

Abstract: Unmanned aerial vehicles (“UAVs”) which fly to destinations (e.g., for delivering items) may land on transportation vehicles (e.g., delivery trucks, etc.) for temporary transport. An agreement with the owner of the transportation vehicles (e.g., a shipping carrier) may be made for obtaining consent and determining compensation for landings, and the associated transportation vehicles that are available for landings may be identified by markers on the roof or other identification techniques. The routes of the transportation vehicles may be known and utilized to determine locations where UAVs will land on and take off from the transportation vehicles, and in cases of emergencies (e.g., due to low batteries, mechanical issues, etc.) the UAVs may land on the transportation vehicles for later retrieval.

Abstract translation: 飞往目的地（例如交付物品）的无人机（“UAV”）可以登陆运输车辆（例如运送卡车等）进行临时运输。 可以与运输工具的所有者（例如航运承运人）达成协议，以获得同意并确定着陆的赔偿，可用于着陆的相关运输车辆可以通过屋顶上的标记或其他识别技术来识别 。 运输车辆的路线可能是已知的，用于确定无人机将从运输车辆着陆和起飞的地点，并且在紧急情况下（例如，由于电池电量低，机械问题等），UAV可能会着陆 在运输车辆上进行后续检索。

公开(公告)号：US20160244158A1

公开(公告)日：2016-08-25

申请号：US14121001

申请日：2014-08-13

Applicant: USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINSTRATION

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 ,  B64C3/40 ,  B64C9/14 ,  B64C39/02 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64D27/24 ,  B64D27/26

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为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推进系统。

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：US20160129998A1

公开(公告)日：2016-05-12

申请号：US14538570

申请日：2014-11-11

Applicant: Amazon Technologies, Inc.

Inventor： Ricky Dean Welsh ,  Daniel Buchmueller ,  Fabian Hensel ,  Gur Kimchi ,  Louis LeRoi LeGrand, III ,  Brandon William Porter ,  Walker Chamberlain Robb ,  Joshua White Traube

IPC: B64C27/08 ,  B64C27/26

CPC classification number: B64C39/024 ,  B64C27/22 ,  B64C27/24 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pushing motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor may be engaged and the pushing propeller will aid in the horizontal propulsion of the UAV.

Abstract translation: 本公开描述了将有助于延长飞行持续时间的无人驾驶飞行器（UAV）的配置。 无人机可能有任何数量的起重马达。 例如，无人机可以包括四台起重电动机（也称为四号机），八台起重马达（八重直升机）等。同样，为了提高水平飞行的效率，无人机还包括一个推动马达和螺旋桨 组件，其定向在一个或多个起重马达上大约九十度。 当无人机水平移动时，推动马达可以接合，推进螺旋桨将有助于无人机的水平推进。

公开(公告)号：US09296270B2

公开(公告)日：2016-03-29

申请号：US13765144

申请日：2013-02-12

Applicant: Aurora Flight Sciences Corporation

Inventor： Robert Parks ,  Adam Woodworth ,  Tom Vaneck ,  Justin McClellan

IPC: B60F5/02 ,  B64C39/02 ,  F42B15/20

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.

Abstract translation: 组合潜艇和无人驾驶飞行器优选地包括主体结构，至少一个翼结构，至少一个垂直稳定器结构和至少一个水平稳定器结构。 推进系统联接到车身结构并且被构造成在空中飞行和水下操作中推进飞行潜艇。 优选地，推进系统包括电动机，耦合到电动机并被配置为接收由电动机产生的电力并提供可变输出功率的变速箱;耦合到齿轮箱并被配置为传递由变速箱提供的可变输出功率的驱动轴， 以及联接到所述驱动轴并被配置为接受从所述驱动轴传递到其的动力的螺旋桨。 螺旋桨进一步构造成在空中环境和水下环境中旋转和推进飞行潜艇。

公开(公告)号：US08991751B2

公开(公告)日：2015-03-31

申请号：US13429156

申请日：2012-03-23

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

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.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。

公开(公告)号：US08951086B2

公开(公告)日：2015-02-10

申请号：US13954218

申请日：2013-07-30

Applicant: Aurora Flight Sciences Corporation

Inventor： Adam John Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Scott Hollman

IPC: A63H17/02 ,  B64C1/30 ,  B64D27/26 ,  B64D9/00 ,  B64C19/00 ,  B64C15/00 ,  B64C39/02 ,  A63H27/00

CPC classification number: B64C1/30 ,  A63H27/001 ,  A63H27/02 ,  B64C15/00 ,  B64C19/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64D1/14 ,  B64D9/00 ,  B64D27/26

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.