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。

公开(公告)号：US07299130B2

公开(公告)日：2007-11-20

申请号：US11011001

申请日：2004-12-13

Applicant: Anthony C. Mulligan ,  Christopher D. Troudt ,  Jason Michael K. Douglas

Inventor： Anthony C. Mulligan ,  Christopher D. Troudt ,  Jason Michael K. Douglas

IPC: G01C21/26

CPC classification number: G05D1/0094 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/205 ,  B64C2201/208

Abstract: Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

Abstract translation: 方法和设备对车队进行监视。 至少一架无人驾驶飞行器（UAV）获取围绕车队位置的图像，以提供关于潜在敌对行为的信息，而无人机按照车队车辆指示的方式沿着车队周围的大致曲线路径。 路径规划器算法软件由控制车队车辆执行，其中处理关于无人机和车队的位置和速度信息以确定控制变量的值。 所确定的值通过无线通信信道发送到无人驾驶飞行器。 监视车辆的路径可能会改变，以便提供回避措施，以避免对手对监控车辆的攻击。

公开(公告)号：US20070252034A1

公开(公告)日：2007-11-01

申请号：US11603815

申请日：2006-11-21

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

公开(公告)号：US20070228214A1

公开(公告)日：2007-10-04

申请号：US11235057

申请日：2005-09-26

Applicant: Dan Horak

Inventor： Dan Horak

IPC: B64F1/04

CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

Abstract: Autonomous micro air vehicles surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad. The MAV has an engine that is adapted to power the MAV. The launch pad has a starter that is adapted to start the engine in the MAV when the MAV is resting on a launching surface of the launch pad. The launch pad further has a battery to power the starter.

Abstract translation: 提供自动微型飞行器车辆监视系统。 一个实施例的MAV系统包括MAV和发射台。 MAV具有适用于为MAV供电的发动机。 发射台具有一个启动器，当MAV在发射台的发射表面上时，该启动器适于在MAV中启动发动机。 发射台还有一个电池为起动器供电。

公开(公告)号：US07182290B2

公开(公告)日：2007-02-27

申请号：US10976566

申请日：2004-10-29

Applicant: Steven M. Sliwa ,  Andreas H. von Flotow ,  Brian D. Dennis

Inventor： Steven M. Sliwa ,  Andreas H. von Flotow ,  Brian D. Dennis

IPC: B64D31/02

CPC classification number: B64C11/003 ,  A63H27/02 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/206 ,  B64D41/007 ,  F02K5/023 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/672

Abstract: Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.

Abstract translation: 公开了用于启动螺旋桨驱动的飞机和其他装置的方法和系统。 根据本发明的一个实施例的系统包括可拆卸的固定装置，其连接到螺旋桨并且具有暴露于流动流中的至少一个部分以在发动机起动期间旋转螺旋桨。 发动机开始翻转（例如在发动机起动和/或旋转高于阈值速率之后），该固定装置构造成与螺旋桨分离。 因此，系统可以包括夹具和螺旋桨之间的可释放的连接。