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1. 发明授权

US09972212B1 Unmanned aerial vehicle camera calibration as part of departure or arrival at a materials handling facility 有权
公开(公告)号：US09972212B1
公开(公告)日：2018-05-15
申请号：US15188904
申请日：2016-06-21
申请人： Amazon Technologies, Inc.
发明人： Samuel Sperindeo , Benji Barash , Yves Albers Schoenberg , Daniel Buchmueller
IPC分类号： G05D3/00 , G08G5/00 , B64C39/02 , B64D47/08 , H04N7/18 , G06K9/62 , H04N17/00 , G06T7/60 , G06T7/40 , G06K9/52
CPC分类号： G08G5/0069 , B64C39/022 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/048 , B64C2201/108 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2201/128 , B64C2201/145 , B64D47/08 , G06K9/52 , G06K9/6215 , G06T7/408 , G06T7/60 , G06T2207/30204 , H04N7/185 , H04N17/002
摘要： This disclosure describes systems, methods, and apparatus for automating the verification of aerial vehicle sensors as part of a pre-flight, flight departure, in-transit flight, and/or delivery destination calibration verification process. At different stages, aerial vehicle sensors may obtain sensor measurements about objects within an environment, the obtained measurements may be processed to determine information about the object, as presented in the measurements, and the processed information may be compared with the actual information about the object to determine a variation or difference between the information. If the variation is within a tolerance range, the sensor may be auto adjusted and operation of the aerial vehicle may continue. If the variation exceeds a correction range, flight of the aerial vehicle may be aborted and the aerial vehicle routed for a full sensor calibration.

2. 发明授权

US09920706B1 Methods of laser powering unmanned aerial vehicles with heat engines 有权
公开(公告)号：US09920706B1
公开(公告)日：2018-03-20
申请号：US15009080
申请日：2016-01-28
申请人： Dmitriy Yavid , Stephen Jon Blank
发明人： Dmitriy Yavid , Stephen Jon Blank
IPC分类号： F02G1/02 , B64G1/40 , F01B17/02 , F03G7/00 , B64C39/02 , H05B7/18 , F01B29/10
CPC分类号： F02G1/02 , B64C39/024 , B64C2201/04 , B64C2201/046 , B64C2201/048 , B64C2201/06 , B64G1/40 , B64G1/409 , F01B17/02 , F01B17/022 , F01B17/025 , F01B29/10 , F03G7/00 , H05B7/18
摘要： Methods of laser powering unmanned aerial vehicles (UAV) with heat engines are disclosed. The laser powered heat engines are used in conjunction with devices for absorbing laser optical radiation, turning the laser optical radiation into heat, supplying the heat to a working fluid of the heat engine and harvesting mechanical work from expanding working fluid in the heat engine.

3. 发明授权

US09694894B2 Aerial vehicle and method of flight 有权
公开(公告)号：US09694894B2
公开(公告)日：2017-07-04
申请号：US14324306
申请日：2014-07-07
申请人： Athene Works Limited
发明人： Nicholas James Deakin
IPC分类号： B64B1/20 , B64B1/02 , B64B1/08 , B64B1/10 , B64B1/12 , B64B1/14 , B64B1/38 , H01Q1/36 , H01Q9/27 , B64B1/64
CPC分类号： B64B1/02 , B64B1/08 , B64B1/10 , B64B1/12 , B64B1/14 , B64B1/20 , B64B1/38 , B64B1/64 , B64B2201/00 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/101 , B64C2201/122 , B64C2201/127 , B64C2201/165 , B64C2201/167 , H01Q1/36 , H01Q9/27
摘要： An aerial vehicle comprises an elongate envelope within which are at least one first compartment for holding a lighter than air gas and at least one second compartment for holding atmospheric air and said at least one second compartment having an inlet and an outlet and at least one pair of wings extending laterally from the envelope; said wings being planar units with a leading and trailing edge, the width of the wings from their leading edges to their trailing edges being substantially less than the length of the envelope with airfoil portions fitted between the leading and trailing edges of the wing: the top and bottom of the wings are mirror images of one another; in which forward motion of the vehicle is obtainable without trust through alternate diving and climbing motion.

4. 发明授权

US09677466B2 Method of managing a power demand for the operation of a pilotless aircraft equipped with an internal combustion engine 有权
公开(公告)号：US09677466B2
公开(公告)日：2017-06-13
申请号：US14966180
申请日：2015-12-11
申请人： AIRBUS GROUP SAS
发明人： Hichem Smaoui , Bruno Rechain , Fabien Retho
IPC分类号： F02B65/00 , B64C39/02 , F02B37/00 , F02B33/40 , F01D15/10 , F02C6/12 , F02C6/14 , F02C6/20 , B60K6/24 , B60K6/38 , B60K6/40 , B60K6/44 , B60K6/387 , B60K6/442 , B64D27/02
CPC分类号： F02B65/00 , B60K6/24 , B60K6/387 , B60K6/40 , B60K6/442 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/048 , B64D2027/026 , F01D15/10 , F02B33/40 , F02B37/00 , F02C6/12 , F02C6/14 , F02C6/206 , F05D2220/329 , F05D2220/40 , F05D2220/62 , F05D2220/76 , F05D2220/90 , F05D2260/42 , Y02T10/144 , Y02T10/6234 , Y02T10/6295 , Y02T50/64 , Y02T50/671
摘要： A method of managing a power demand to assure the operation of a pilotless aircraft. The aircraft includes an internal combustion engine supplying a maximum principal power which can vary. The management method is particularly suitable for a rotary wing pilotless aircraft. It guarantees the storage of an amount of electrical energy at least equal to a recovery energy of the aircraft in the event of failure of the internal combustion engine. This recovery energy enables the control of autorotation and landing of the aircraft.

5. 发明申请

US20160096613A1 VTOL SYMMETRIC AIRFOIL FUSELAGE OF FIXED WING DESIGN 审中-公开
标题翻译：固定式设计的垂直变形对称气垫
公开(公告)号：US20160096613A1
公开(公告)日：2016-04-07
申请号：US14849814
申请日：2015-09-10
申请人： Jonathon Thomas Johnson , Elizabeth V.M. Johnson
发明人： Jonathon Thomas Johnson , Elizabeth V.M. Johnson
IPC分类号： B64C1/00 , B64C29/00 , B64C39/02 , B64C25/34 , B64C25/10
CPC分类号： B64C39/024 , B64C25/32 , B64C29/04 , B64C2025/325 , B64C2201/021 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/16 , B64C2201/18
摘要： Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system.
摘要翻译：目前的飞机技术包括固定翼，多转子和矢量引擎设计。固定翼技术和矢量引擎技术的综合已经实施，但仅限于传统的固定翼设计飞机。所提出的飞机设计具有机身预期的创新，改进的矢量引擎设计系统和起落架系统。

6. 发明申请

US20100012790A1 GYRO-STABILIZED AIR VEHICLE 审中-公开
标题翻译： GYRO稳定的空气车
公开(公告)号：US20100012790A1
公开(公告)日：2010-01-21
申请号：US12426162
申请日：2009-04-17
申请人： Nicolae Bostan
发明人： Nicolae Bostan
IPC分类号： B64C29/04
CPC分类号： B64C3/385 , B64C17/06 , B64C27/20 , B64C29/0033 , B64C29/02 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/127 , B64C2201/146 , B64C2201/162 , B64C2201/165 , Y02T50/14
摘要： A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.
摘要翻译：一架垂直起降（VTOL）的空中客车。机动车可以载人或无人驾驶。在一个实施例中，空中交通工具包括安装在机身中的两个被覆盖的螺旋桨，机身和陀螺仪稳定盘。陀螺稳定盘可以被配置成通过足够的质量和/或足够的角速度来提供足够的角动量，使得在飞行的各个阶段期间航空器的陀螺仪稳定。在一个实施例中，机身固定地附接到被覆盖的螺旋桨。在另一个实施例中，被覆盖的螺旋桨可枢转地安装在机身上。

7. 发明授权

US07542828B2 Unmanned air vehicle, integrated weapon platform, avionics system and control method 失效
标题翻译：无人机，综合武器平台，航空电子系统及控制方法
公开(公告)号：US07542828B2
公开(公告)日：2009-06-02
申请号：US11160645
申请日：2005-07-01
申请人： Daniel W. Steele , Joseph R. Chovan
发明人： Daniel W. Steele , Joseph R. Chovan
IPC分类号： G01C23/00 , B64C13/20
CPC分类号： B64D7/00 , B64C39/024 , B64C2201/021 , B64C2201/044 , B64C2201/048 , B64C2201/104 , B64C2201/121 , B64C2201/127 , B64C2201/141 , B64C2201/165
摘要： A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV.
摘要翻译：一种小型，可重复使用的拦截无人机（UAV），无人机的航空电子控制系统，无人机的设计方法和无人机的控制方法，阻止小规模空中，水和地面威胁。无人机包括具有集成武器和航空电子平台的高性能机身。无人机的设计首先涉及选择合适的武器，然后设计拦截机体，以通过机身操纵实现武器瞄准。无人机使用以车辆为中心的航空电子控制系统，因此提供了对UAV的高度自主控制。情境感知处理器可以访问一套不同的传感器，可以智能地（自主地）执行各种任务场景。与情境感知处理器可操作地集成的飞行控制处理器包括飞行员控制器和用于飞行和操纵无人机的自动驾驶仪控制器。

8. 发明申请

US20090026314A1 CARGO AIRCRAFT 有权
标题翻译：货运飞机
公开(公告)号：US20090026314A1
公开(公告)日：2009-01-29
申请号：US11782850
申请日：2007-07-25
申请人： ELIE HELOU, JR.
发明人： ELIE HELOU, JR.
IPC分类号： B64C1/20 , B64C1/00
CPC分类号： B64C1/10 , B64C1/00 , B64C1/061 , B64C1/065 , B64C39/02 , B64C39/024 , B64C2001/0072 , B64C2201/021 , B64C2201/048 , B64C2201/086 , B64C2201/104 , B64C2201/128 , B64C2201/162 , B64C2201/167 , B64C2211/00 , Y02T50/43
摘要： An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.
摘要翻译：用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。飞机被认为是无人机。

9. 发明授权

US07481396B2 Small-size high-speed transmission system for use in microturbine-powered aircraft 有权
标题翻译：用于微型涡轮动力飞机的小型高速传动系统
公开(公告)号：US07481396B2
公开(公告)日：2009-01-27
申请号：US11398375
申请日：2006-06-14
申请人： Jules G. Kish
发明人： Jules G. Kish
IPC分类号： B64C35/00
CPC分类号： B64C27/14 , B64C39/028 , B64C2201/048 , B64C2201/104 , B64C2201/121 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D35/02
摘要： A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. The two stages of the transmission system may comprise any one (or parts of) of a number of configurations, including an in-line lay shaft configuration, an in-line star-star configuration, an offset star-spur configuration, an offset compound idler configuration, an inline traction-internal gear configuration, and an inline traction-planetary gear configuration. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.
摘要翻译：与微型涡轮发动机结合使用的用于推进飞机机体（例如基于螺旋桨的固定翼飞行器或基于转子的垂直升降飞机）或用于各种其它应用的传动系统。微型涡轮发动机的输出轴优选地在72,000RPM和150,000RPM之间的转速下工作，输出功率在150HP和5HP之间（最优选地在50,000RPM和200,000RPM之间的扩展范围内工作，并且输出功率在200 HP和5 HP之间）。两个还原阶段提供优选具有至少19的值，最优选大于24的减小率。传动系统的尺寸最小，最好具有小于12英寸的最大直径。传动系统的两个阶段可以包括许多构造的任何一个（或部分）构造，包括在线卧轴构造，直列星星构造，偏移星形支路构造，偏移化合物惰轮构造，在线牵引内齿轮配置和在线牵引行星齿轮配置。优选地，传动系统的输入级是自平衡的，使得第一轴可以被支撑而没有轴承，并且通过外径引导的花键联接机构可操作地联接到微型涡轮发动机的输出轴。对于垂直升降应用，可以使用单个牵引台以及锥齿轮组件或其他轴传动机构来提供必要的RPM减小。

10. 发明授权

US07331546B2 Bendable wing for micro air vehicle 有权
标题翻译：微型飞机的弯曲翼
公开(公告)号：US07331546B2
公开(公告)日：2008-02-19
申请号：US11510013
申请日：2006-08-25
申请人： Peter Ifju , Kyu-Ho Lee , Roberto Albertani , Shawn J. Mitryk , Frank J. Boria , Mujahid Abdulrahim
发明人： Peter Ifju , Kyu-Ho Lee , Roberto Albertani , Shawn J. Mitryk , Frank J. Boria , Mujahid Abdulrahim
IPC分类号： B64C3/56
CPC分类号： B64C39/028 , A63H27/007 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/082 , B64C2201/102 , B64C2201/123 , B64C2201/127 , B64C2201/165 , B64C2201/201
摘要： A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.
摘要翻译：具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。

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