公开(公告)号：US09969486B1

公开(公告)日：2018-05-15

申请号：US15188922

申请日：2016-06-21

Applicant: Amazon Technologies, Inc.

Inventor： Barry James O'Brien ,  Scott Michael Wilcox ,  Joshua John Watson

IPC: B64C13/20 ,  G01J5/52 ,  G05D1/06 ,  B64C39/02 ,  B64D47/08 ,  G01C25/00 ,  G01K15/00 ,  G01K13/00 ,  G06K9/62

CPC classification number: B64C13/20 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/145 ,  B64D47/08 ,  G01C25/00 ,  G01J5/522 ,  G01K13/00 ,  G01K15/00 ,  G05D1/0653 ,  G06K9/6202 ,  G06T2207/10024 ,  G06T2207/10032

Abstract: 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.

公开(公告)号：US20170240275A1

公开(公告)日：2017-08-24

申请号：US15456450

申请日：2017-03-10

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

IPC: B64C29/04 ,  B64C39/02 ,  B64C11/00 ,  B64C9/00 ,  B64C39/12 ,  B64D27/20

CPC classification number: B64C29/04 ,  B64C9/38 ,  B64C11/001 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/162 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0273 ,  Y02T50/166 ,  Y02T50/44

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

公开(公告)号：US20140318132A1

公开(公告)日：2014-10-30

申请号：US13859424

申请日：2013-04-09

Applicant: DAVID J. PODROG

Inventor： DAVID J. PODROG

IPC: F02C1/05

CPC classification number: F02C1/05 ,  B64C2201/048 ,  F02G2254/90 ,  F05D2220/76 ,  Y02E30/00 ,  Y02T50/678 ,  Y02T70/5227

Abstract: A device powered by a method of heating a gas by directing X-rays at a mass of hafnium 178 to induce gamma rays. The gamma rays are directed at a heat exchanging apparatus, resulting in a stream of heated gas. This process powers a Hafnium gas turbine engine capable of providing shaft power or thrust to mechanical devices.

Abstract translation: 一种由通过以大量铪178引导X射线来加热气体以引起γ射线的方法的装置。 伽马射线被引导到热交换装置，导致加热气体流。 该方法为能够向机械装置提供轴功率或推力的铪燃气轮机提供动力。

公开(公告)号：US20140110527A1

公开(公告)日：2014-04-24

申请号：US14126846

申请日：2011-06-17

Applicant: Robert L. Sing

Inventor： Robert L. Sing

IPC: B64D9/00

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

Abstract: The self-sustaining drone aircraft freight and observation system (5) comprises a fleet of jet-powered drone aircraft (10) designed to carry freight (12) only. The drones (10) operate from a separate airfield in outlying areas to decrease land costs and to avoid disturbing residential and business areas. Navigation is automated using guidance from GPS satellites (16), and the aircraft (10) can be assisted by a hydraulic catapult (13) during takeoff to reduce the fuel payload. The observation component (18) includes sensors that can observe weather conditions and emergency signals from boats, ships and other sources. The system (5) may include a large-scale energy production center and multi-acre vegetable, herb and flower production center (26). The energy production center includes solar panels (30), fuel cells (38), and batteries (44). Thus, the system (5) does not need to be connected to the public utility electrical grid.

Abstract translation: 自维持无人机飞机货运观察系统（5）包括一个仅用于运输（12）的喷气式无人机（10架）舰队。 无人机（10）从外围地区的独立机场运营，以降低土地成本，避免住宅和商业区域的不安。 导航使用GPS卫星（16）的指导进行自动化，飞机（10）可在起飞期间由液压弹射器（13）辅助以减少燃料有效载荷。 观察部件（18）包括能够观察船舶，船舶和其他来源的天气状况和紧急信号的传感器。 系统（5）可以包括一个大型能源生产中心和多英亩蔬菜，草药花卉生产中心（26）。 能源生产中心包括太阳能电池板（30），燃料电池（38）和电池（44）。 因此，系统（5）不需要连接到公共事业电网。

公开(公告)号：US20130062457A1

公开(公告)日：2013-03-14

申请号：US13636583

申请日：2011-03-22

Applicant: Nicholas James Deakin

Inventor： Nicholas James Deakin

IPC: B64B1/62 ,  H01L31/0232 ,  H01Q1/28 ,  B64B1/20

CPC classification number: 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

Abstract: An aerial vehicle is described which comprises: a first compartment for holding a lighter than air gas; a second compartment for holding atmospheric air and having an inlet and an outlet; a solar panel for converting sunlight into electricity; a compressor for pumping atmospheric air through the inlet into the second compartment; control means for controlling the pitch and yaw of the vehicle; and a controller for controlling the buoyancy of the vehicle via the compressor and the outlet such that the vehicle is either lighter than the surrounding air and rising or heavier than the surrounding air and falling, and for controlling the control means such that the rising and falling motion includes a horizontal component. In another embodiment the solar panel is replaced by an engine and a fuel tank for storing fuel for the engine is also provided.The aerial vehicle can remain airborne for extended periods by using buoyancy propulsion.In the embodiments including a solar panel, a system including a light transmission station may be provided to supply energy to the solar panel from the light transmission station rather than relying on the incident sunlight alone.A method of flight using buoyancy propulsion is also described.

Abstract translation: 描述了一种飞行器，其包括：用于保持比空气气体轻的第一隔室; 用于容纳大气并具有入口和出口的第二隔室; 用于将阳光转化为电的太阳能电池板; 用于将大气通过所述入口泵送到所述第二隔室中的压缩机; 用于控制车辆的俯仰和偏航的控制装置; 以及用于经由压缩机和出口控制车辆的浮力的控制器，使得车辆比周围空气要轻，并且比周围空气上升或者重，并且下降，并且用于控制控制装置使得上升和下降 运动包括水平分量。 在另一个实施例中，太阳能电池板被发动机代替，并且还提供了用于储存用于发动机的燃料的燃料箱。 航空器可以通过使用浮力推进长时间保持空中。 在包括太阳能电池板的实施例中，可以提供包括光传输站的系统，以从光传输站向太阳能电池板提供能量，而不是仅依赖于入射的太阳光。 还描述了使用浮力推进的飞行方法。

公开(公告)号：US20100019098A1

公开(公告)日：2010-01-28

申请号：US12179690

申请日：2008-07-25

Applicant: Daniel Ross Collette

Inventor： Daniel Ross Collette

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风扇风扇芯包括框架，附接到发动机，变速箱组件，风扇和多个控制叶片。 框架上的第一表面包括多个连接或电迹线。 多个连接用于可拆卸地附接携带各种有效载荷的各种吊舱。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。

公开(公告)号：US07575192B1

公开(公告)日：2009-08-18

申请号：US11305711

申请日：2005-12-16

Applicant: Jules G. Kish

Inventor： Jules G. Kish

IPC: B64D35/00

CPC classification number: B64D35/00 ,  B64C27/12 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/165 ,  F02C6/206 ,  F02C7/36 ,  F05D2250/82 ,  F16H1/22 ,  Y02T50/671

Abstract: A transmission system for use with a microturbine engine that includes an input shaft operably coupled to the output shaft of the microturbine engine. The output shaft of the microturbine engine and the input shaft of the transmission system operate at a rotational speed in a range between 50,000 and 250,000 RPM with an output power between 200 and 5 HP. The transmission system includes a gear train having a first gear that interfaces to a second gear, the first and second gears employing teeth with opposite handed helix-angled surfaces that apply axial forces to the input shaft during both normal operation and start-up operations, which pushes the input shaft toward the output shaft of the microturbine engine. Preferably, the helix-angled surfaces on respective normal drive sides of the teeth produce an axial force during normal operation that will not be overcome with the axial force produced by the mass time acceleration of the first gear. The gear train interfaces to a starter-generator preferably through the second gear. The gear train preferably provides a reduction ratio having a value greater than 24.

Abstract translation: 一种与微型涡轮发动机一起使用的传动系统，其包括可操作地联接到微型涡轮发动机的输出轴的输入轴。 微型涡轮发动机的输出轴和变速器系统的输入轴在50,000和250,000 RPM之间的转速下运行，输出功率在200和5 HP之间。 传动系统包括齿轮系，该齿轮系具有与第二齿轮相接合的第一齿轮，第一和第二齿轮采用具有相反的双螺旋角倾斜表面的齿，在正常操作和启动操作过程中将轴向力施加到输入轴， 其将输入轴推向微型涡轮发动机的输出轴。 优选地，齿的相应正常驱动侧上的螺旋角度表面在正常操作期间产生轴向力，这将不会被第一档的质量时间加速度产生的轴向力所克服。 齿轮系优选地通过第二齿轮与起动器发电机接口。 齿轮系优选地提供具有大于24的值的减速比。

公开(公告)号：US07270296B2

公开(公告)日：2007-09-18

申请号：US10756024

申请日：2004-01-12

Applicant: J. William Box ,  Jules G. Kish

Inventor： J. William Box ,  Jules G. Kish

IPC: B64D35/00

CPC classification number: B64C27/14 ,  B64C39/028 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D35/02

Abstract: 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.

Abstract translation: 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（或多个部分），包括一个在线的卧式结构，一个星形星形配置，一个偏移星形齿轮配置，一个偏移复合惰轮 配置，内联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。

公开(公告)号：US07261257B2

公开(公告)日：2007-08-28

申请号：US10996799

申请日：2004-11-23

Applicant: Elie Helou, Jr.

Inventor： Elie Helou, Jr.

IPC: B64C1/22

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20070023582A1

公开(公告)日：2007-02-01

申请号：US11160645

申请日：2005-07-01

Applicant: Daniel Steele ,  Joseph Chovan

Inventor： Daniel Steele ,  Joseph Chovan

IPC: B64C13/20

CPC classification number: B64D7/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165

Abstract: 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.

Abstract translation: 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。