公开(公告)号：US20160376005A1

公开(公告)日：2016-12-29

申请号：US15262177

申请日：2016-09-12

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

IPC: B64C39/02 ,  B64C27/00 ,  B64C27/08 ,  G05D1/10 ,  B64F3/02 ,  B64D1/08 ,  B64D1/22 ,  B64D27/24 ,  B64D33/08

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

公开(公告)号：US09475579B2

公开(公告)日：2016-10-25

申请号：US14121001

申请日：2014-08-13

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

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: B64D27/24 ,  B64D27/26 ,  B64C29/00 ,  B64C3/40 ,  B64C9/14 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64C39/02 ,  B64D27/02

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：US20160304199A1

公开(公告)日：2016-10-20

申请号：US14560765

申请日：2014-12-04

Applicant: Elwha LLC

Inventor： ALISTAIR K. CHAN ,  JESSE R. CHEATHAM, III ,  HON WAH CHIN ,  WILLIAM DAVID DUNCAN ,  RODERICK A. HYDE ,  MURIEL Y. ISHIKAWA ,  JORDIN T. KARE ,  TONY S. PAN ,  ROBERT C. PETROSKI ,  CLARENCE T. TEGREENE ,  DAVID B. TUCKERMAN ,  THOMAS ALLAN WEAVER ,  LOWELL L. WOOD, JR.

IPC: B64C39/02 ,  B64D47/08 ,  B64D27/26 ,  B64C27/08 ,  B64C27/52

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/52 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/128 ,  B64D27/26 ,  B64D47/08

Abstract: A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission.

Abstract translation: 公开了一种可重新配置的无人机系统。 还公开了一种用于配置可重新配置的无人驾驶飞行器的系统和方法，以及用于在空域中操作和管理可重新配置的无人飞行器的系统和方法。 该飞机是有选择地可重构的，以修改飞行特性。 飞机包括一组转子。 相对于基座的至少一个转子的位置可以通过转子相对于起重臂的平移，悬臂相对于基座的枢转以及起重臂相对于基座的平移的至少一个来改变。 使得可以通过至少一个转子相对于基座的位置的配置来修改飞行特性。 一种在任务上配置具有一组转子的承载有效载荷的飞行器的方法包括以下步骤：确定所述载荷的属性至少包括质量属性，确定所述有效载荷将与飞行器耦合的方式，确定 转子组中的每个转子至少部分地考虑有效载荷的属性，并将该组转子定位在飞行器的构型中以执行任务。

公开(公告)号：US20150285165A1

公开(公告)日：2015-10-08

申请号：US14439502

申请日：2013-10-22

Applicant: EADS DEUTSCHLAND GMBH

Inventor： Juergen Steinwandel ,  Florian Stagliano ,  Jan Van Toor

IPC: F02D29/02 ,  B64D27/02 ,  B64C39/02 ,  B64D31/00 ,  B64D41/00

CPC classification number: F02D29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/16 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.

Abstract translation: 无人机包括具有柴油或煤油内燃机的推进系统和用于发动机充气的充电装置。 推进系统可以是混合推进系统或并联混合推进系统。

公开(公告)号：US20130283816A1

公开(公告)日：2013-10-31

申请号：US13979120

申请日：2012-01-06

Applicant: Stephen John Richard Smith ,  Kieran James Watt ,  Andrew Charles White

Inventor： Stephen John Richard Smith ,  Kieran James Watt ,  Andrew Charles White

IPC: F02C7/24

CPC classification number: F02C7/24 ,  B64C39/024 ,  B64C2201/044 ,  B64D13/08 ,  B64D15/02 ,  B64D15/04 ,  B64D27/10 ,  B64D33/08 ,  B64D2013/0607 ,  B64D2013/0614 ,  B64D2013/0648 ,  B64D2013/0674 ,  F28D2020/0013 ,  F28D2020/0017 ,  F28F13/003 ,  Y02T50/56

Abstract: A turboprop-powered medium altitude long endurance aircraft, having a gas turbine engine; a heat scavenging device to scavenge heat from the gas turbine engine; and a heating device to use the scavenged heat to provide heating to the aircraft. The heat scavenging device may be placed on an engine casing and/or on or in an engine exhaust duct. The heating device may include a circulation path routed directly to a location in the aircraft where heating is to be performed, for example a leading edge of an engine support pylon or a leading edge of an engine-carrying wing. The heating device can include a heat exchanger.

Abstract translation: 具有燃气涡轮发动机的涡轮螺旋桨发动机中型高空耐久型飞机; 用于清除来自燃气涡轮发动机的热的除热装置; 以及使用清扫热量来向飞机提供加热的加热装置。 除热装置可以放置在发动机壳体上和/或在发动机排气管道上或发动机排气管道中。 加热装置可以包括直接路由到飞行器中要进行加热的位置的循环路径，例如发动机支撑塔的前缘或发动机承载翼的前缘。 加热装置可以包括热交换器。

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：US08256704B2

公开(公告)日：2012-09-04

申请号：US11838731

申请日：2007-08-14

Applicant: Gert Lundgren

Inventor： Gert Lundgren

IPC: B64C27/22

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/165

Abstract: A vertical/short take-off and landing aircraft with a single proprotor assembly that has a pair of inline counter-rotating rotors. Two inline counter-rotating engines are directly connected to the rotors. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the proprotor assembly permits thrust to be directed forward to back and left to right to control pitch and roll when hovering. Varying the relative engine speeds controls yaw. The aircraft is adaptable as an unmanned vehicle.

Abstract translation: 具有单个推进器组件的垂直/短距起飞和着陆飞机，其具有一对在线的反向旋转的转子。 两个直列反向旋转发动机直接连接到转子上。 一个引擎在水平飞行中关闭以提高效率。 安装推进器组件的万向节允许推动力向前指向前向左并向左转，以便在悬停时控制俯仰和滚动。 改变相对发动机转速来控制偏航。 该飞机适用于无人驾驶的车辆。

公开(公告)号：US20110193959A1

公开(公告)日：2011-08-11

申请号：US12658543

申请日：2010-02-11

Applicant: Steven Roger Brandon

Inventor： Steven Roger Brandon

IPC: H04N7/18 ,  B64C27/82 ,  B64D7/00

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2211/00

Abstract: This device, a modular minihelicopter, is a radio-controlled, gas-powered aircraft designed to perform varying missions based upon the functions of interchangeable modular-systems mounted on the minihelicopter's chassis.

Abstract translation: 该装置是一种模块化小型飞行器，是一种无线电控制的气动飞机，旨在根据安装在小型飞机底盘上的可互换模块化系统的功能执行不同的任务。

公开(公告)号：US20100256839A1

公开(公告)日：2010-10-07

申请号：US12417380

申请日：2009-04-02

Applicant: David Fitzpatrick

Inventor： David Fitzpatrick

IPC: G05D1/08 ,  G05D1/00 ,  B64C13/20

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  G01R33/0206 ,  G05D1/0858

Abstract: Methods and systems are provided for using a measurement of only one axis of a three-axis magnetometer to perform at least one corrective action on an unmanned aerial vehicle (“UAV”). An exemplary embodiment comprises (i) receiving from a three-axis magnetometer a measurement representative of an attitude of a UAV, wherein the measurement is of only one axis of the magnetometer, (ii) comparing the measurement to an allowable range of attitudes, (iii) determining that the measurement is not within the allowable range of attitudes, and (iv) performing at least one corrective action on the UAV.

Abstract translation: 提供了用于仅使用三轴磁力计的一个轴的测量来对无人驾驶飞行器（“UAV”）执行至少一个校正动作的方法和系统。 示例性实施例包括（i）从三轴磁力计接收表示UAV姿态的测量值，其中测量仅为磁力计的一个轴，（ii）将测量值与允许的姿态范围进行比较， iii）确定测量不在允许的态度范围内，以及（iv）对UAV执行至少一个纠正措施。

公开(公告)号：US20100147993A1

公开(公告)日：2010-06-17

申请号：US12334098

申请日：2008-12-12

Applicant: Richard E. Annati ,  Patrick L. O'Brien

Inventor： Richard E. Annati ,  Patrick L. O'Brien

IPC: B64C29/02 ,  H02P7/00

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64D27/24 ,  Y02T50/64

Abstract: A propulsion system for a vertical take-off and landing ducted fan aerial vehicle is provided, the propulsion system comprising an internal combustion engine, an electric motor that comprises a motor generator, a motor drive and a battery. The motor drive and battery are integrated into the aerial vehicle and provide power to the ducted fan aerial vehicle. The electric motor may comprise a ring motor generator. In operation, this dual propulsion system serves as a weight-efficient option to allow for two sources of power on a ducted fan unmanned aerial vehicle.

Abstract translation: 提供了一种用于垂直起飞和降落的风扇飞行器的推进系统，该推进系统包括内燃机，包括电动发电机，电机驱动器和电池的电动机。 电动机驱动器和电池被集成到飞行器中，并向管道风扇飞行器提供电力。 电动机可以包括环形电动发电机。 在操作中，这种双推进系统作为一种重量选择，允许在风扇无人驾驶飞行器上的两个电源。