公开(公告)号：US09920706B1

公开(公告)日：2018-03-20

申请号：US15009080

申请日：2016-01-28

Applicant: Dmitriy Yavid ,  Stephen Jon Blank

Inventor： Dmitriy Yavid ,  Stephen Jon Blank

IPC: F02G1/02 ,  B64G1/40 ,  F01B17/02 ,  F03G7/00 ,  B64C39/02 ,  H05B7/18 ,  F01B29/10

CPC classification number: 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

Abstract: 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.

公开(公告)号：US20170247107A1

公开(公告)日：2017-08-31

申请号：US15056408

申请日：2016-02-29

Applicant: GeoScout, Inc.

Inventor： Istvan Hauer ,  Cyril Blank ,  Allan Vaitses

IPC: B64C39/02 ,  B64C27/12 ,  B64D35/06 ,  B64C27/08

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/12 ,  B64C2201/027 ,  B64C2201/04 ,  B64C2201/108 ,  B64C2201/14 ,  B64D35/06

Abstract: An apparatus comprising a body defining a first vertical axis, two or more frame members each having a longitudinal axis and having an inner-end and an outer-end connected to the body at the inner-end and where a first horizontal geometrical plane is generally coincident with the longitudinal axis of each of the two or more frame members and where the first horizontal geometrical plane is generally orthogonal to the first vertical axis, two or more rotary-wings each comprising one or more blades whose rotation defines a first rotational axis which is configurable to be nearly parallel with the first vertical axis and comprising a second rotational axis which is configurable to be approximately parallel first horizontal geometrical plane where a first of the two or more rotary-wings having a blade-inner-end and a first blade-outer-end rotatably connected by its blade-inner-end to a first transmission is disposed substantially on the outer-end of a first of the two or more frame members, a second of the two or more rotary-wings having a blade-inner-end and a blade-outer-end rotatably connected by its blade-inner-end to a second transmission is disposed substantially on the outer-end of a second of the two or more frame members, where each of the first rotational axes is disposed on the opposite side of plane which is coincident with the first vertical axis, where the direction of rotation of a first of the two or more rotary-wings about its first rotational axis is opposite of that of the second of the two or more rotary-wings about its first rotational axis, and, where the rotational disk defined by the rotation of the blade-outer-end of the first of the two or more rotary-wings is at least partially coincident with rotational disk defined by the rotation of the blade-outer-end of the second of the two or more rotary-wings.

公开(公告)号：US20120234968A1

公开(公告)日：2012-09-20

申请号：US13442544

申请日：2012-04-09

Applicant: FRICK A. SMITH

Inventor： FRICK A. SMITH

IPC: B64C29/00 ,  B64C5/04 ,  B64D35/04

CPC classification number: B64C29/0033 ,  B64C1/1415 ,  B64C1/1476 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C27/82 ,  B64C29/00 ,  B64C29/0016 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64D31/00 ,  B64D35/04

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

Abstract translation: 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。

公开(公告)号：US20080184906A1

公开(公告)日：2008-08-07

申请号：US11703362

申请日：2007-02-07

Applicant: Joseph B. Kejha

Inventor： Joseph B. Kejha

IPC: B64C11/00 ,  F42B15/00

CPC classification number: B64D27/24 ,  B64C39/024 ,  B64C2201/04 ,  B64D27/02 ,  B64D2027/026 ,  Y02T50/64 ,  Y02T90/44

Abstract: An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

Abstract translation: 一种先进的内燃电动混合动力飞机，其飞行范围和飞行时间至少比传统等效飞机的两倍，同时使用相同数量的任何所需的燃料。 这是通过使用2-3x小型超轻型发动机进行巡航，并且在起飞和爬升期间由锂电池供电的超轻型电动机实现。 电动马达在巡航和下降期间成为发电机，对所述电池进行充电。 飞机还具有暂时的静电隐身能力，并通过电动备用电源增加安全性。 由于其高效率，操作成本大大降低。 附加功能包括高度先进的，最小的阻力和重量的机身。

公开(公告)号：US20170334581A1

公开(公告)日：2017-11-23

申请号：US15160071

申请日：2016-05-20

Applicant: Michael White ,  Miles Austin

Inventor： Michael White ,  Miles Austin

IPC: B64F1/36 ,  B60L11/18 ,  H01M2/10 ,  B64F1/04 ,  B64F1/28 ,  B64C39/02

CPC classification number: B64F1/36 ,  B60L53/80 ,  B60L2200/10 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/04 ,  B64C2201/042 ,  B64D37/30 ,  B64D47/00 ,  B64D2221/00 ,  B64F1/007 ,  B64F1/04 ,  B64F1/22 ,  B64F1/28 ,  H01M2/1083 ,  H01M2220/20 ,  H01M2250/20 ,  Y02T10/7005 ,  Y02T10/7072 ,  Y02T90/124 ,  Y02T90/14 ,  Y02T90/32

Abstract: A system for autonomously replacing batteries or fuel cells on small aerial vehicles such as Unmanned Aerial Vehicles (UAVs) or radio-controlled aircraft (RC) is described. At the core of this system is a “universal battery receptacle” that can be added to a variety of unmanned aircraft platforms and provides a uniform interface for battery or fuel cell replacement in the form of a commensurately designed “universal fuel cell”.Additionally, a system is described through which an aerial vehicle can be accepted, manipulated, the batteries replaced, and the vehicle re-launched, all without direct user intervention. Such systems can be deployed across a geographic area to increase the range of aerial vehicles without extensive ground support personnel.

公开(公告)号：US20170088277A1

公开(公告)日：2017-03-30

申请号：US15163499

申请日：2016-05-24

Applicant: Reebeez, Inc.

Inventor： Ankita Ghoshal

IPC: B64D27/24 ,  H01L35/04 ,  H02P31/00 ,  H01L35/22 ,  H01L35/34 ,  B64C39/02 ,  H01L35/32

CPC classification number: B64D27/24 ,  B60L8/003 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/042 ,  B64D2027/026 ,  H01L35/00 ,  H01L35/04 ,  H01L35/12 ,  H01L35/22 ,  H01L35/28 ,  H01L35/30 ,  H01L35/32 ,  H01L35/34 ,  H02P31/00 ,  H02P2201/07 ,  H02S10/30 ,  Y02T10/7083 ,  Y02T50/64

Abstract: This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles which includes a thermoelectric generator. The thermoelectric generator includes a first heat exchanger disposed within an exhaust duct of an unmanned aerial vehicle. The thermoelectric generator further includes a first ceramic layer disposed on the first heat exchanger and a first and second metal tab bonded to the first ceramic layer. The thermoelectric generator further includes a second metal tab bonded to a second ceramic layer. At least one N-type thermoelectric leg is disposed between the first metal tab bonded to the first ceramic layer and the metal tab bonded to the second ceramic layer. Further, at least one P-type thermoelectric leg is disposed between the second metal tab bonded to the first ceramic layer and the metal tab bonded to the second ceramic layer.

公开(公告)号：US20160311530A1

公开(公告)日：2016-10-27

申请号：US15204547

申请日：2016-07-07

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64C29/00 ,  B64C27/28 ,  B64D31/00 ,  B64C39/02 ,  B64C27/82 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64C1/14 ,  B64C27/52 ,  B64C27/26 ,  B64D17/24

CPC classification number: B64C29/0033 ,  B64C1/1415 ,  B64C1/1476 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C27/82 ,  B64C29/00 ,  B64C29/0016 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64D31/00 ,  B64D35/04

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

Abstract translation: 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。

公开(公告)号：US20160185447A1

公开(公告)日：2016-06-30

申请号：US14947871

申请日：2015-11-20

Applicant: AeroVironment, Inc.

Inventor： Carlos Thomas Miralles

IPC: B64C13/16 ,  G05D1/12 ,  B64C39/02 ,  F41G7/22

CPC classification number: B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

Abstract translation: 一种包括具有翼元件和尾部元件的无人飞行器（UAV）的系统，其被配置成滚动以通过滚动来成角度地定向UAV，以便在其后期终点阶段将UAV的纵向平面与目标对准。 一种UAV身体重定向的方法，包括：（a）由处理器确定基于身体固定框架的目标点和视轴之间的距离的视轴角度误差校正值; 和（b）实现UAV机动，其包括将目标点平移到身体固定框架中的重定向目标点的角度角色率分量，以经由偏移角度校正值来保持偏移角度。

公开(公告)号：US09376214B2

公开(公告)日：2016-06-28

申请号：US14867152

申请日：2015-09-28

Applicant: Reebeez, Inc.

Inventor： Ankita Ghoshal

IPC: H01L35/00 ,  H01L35/12 ,  H01L35/28 ,  H01L35/30 ,  H01L35/32 ,  H02S10/30 ,  B64D27/24 ,  B64C39/02 ,  H02P31/00

CPC classification number: B64D27/24 ,  B60L8/003 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/042 ,  B64D2027/026 ,  H01L35/00 ,  H01L35/04 ,  H01L35/12 ,  H01L35/22 ,  H01L35/28 ,  H01L35/30 ,  H01L35/32 ,  H01L35/34 ,  H02P31/00 ,  H02P2201/07 ,  H02S10/30 ,  Y02T10/7083 ,  Y02T50/64

Abstract: This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles. The hybrid propulsion system includes a combustor, a thermophotovoltaic generator, and a thermoelectric generator. The combustor burns a chemical based fuel to produce radiation and heat that are converted into electricity used to power the aerial vehicle. The thermophotovoltaic generator is positioned to receive radiation and remnant heat generated by flames in the combustor while the thermoelectric generator receives heat from exhausted flue gases from the combustor.

Abstract translation: 本公开一般涉及用于空中飞行器的混合固态推进系统。 混合推进系统包括燃烧器，热光伏发电机和热电发电机。 燃烧器燃烧基于化学物质的燃料以产生被转换成用于为飞行器运行的电力的辐射和热量。 热光电发生器被定位成接收由燃烧器中的火焰产生的辐射和残余热，同时热电发电机从来自燃烧器的排出的废气中接收热量。

公开(公告)号：US09211947B2

公开(公告)日：2015-12-15

申请号：US14016602

申请日：2013-09-03

Applicant: AEROVIRONMENT, INC.

Inventor： Carlos Miralles

IPC: G01C23/00 ,  G05D1/00 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00 ,  B64C13/16 ,  G05D1/12 ,  F41G7/22

CPC classification number: B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

Abstract translation: 一种包括具有翼元件和尾部元件的无人飞行器（UAV）的系统，其被配置成滚动以通过滚动来成角度地定向UAV，以便在其后期终点阶段将UAV的纵向平面与目标对准。 一种UAV身体重定向的方法，包括：（a）由处理器确定基于身体固定框架的目标点和视轴之间的距离的视轴角度误差校正值; 和（b）实现UAV机动，其包括将目标点平移到身体固定框架中的重定向目标点的角度角色率分量，以经由偏移角度校正值来保持偏移角度。