公开(公告)号：US09156552B2

公开(公告)日：2015-10-13

申请号：US14129195

申请日：2012-06-20

Applicant: Isobel Louise Freeman ,  Keith Antony Rigby

Inventor： Isobel Louise Freeman ,  Keith Antony Rigby

IPC: G05D1/00 ,  B64C39/02 ,  F41H7/00 ,  F41H13/00 ,  F42B12/36

CPC classification number: B64C39/024 ,  B64C2201/00 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  F41H7/005 ,  F41H13/00 ,  F42B12/365

Abstract: An apparatus, and a method performed by the apparatus, are disclosed wherein the apparatus can be mounted on an unmanned vehicle and arranged to act upon a payload. The payload can be mounted on the unmanned vehicle and, under an action of the apparatus, is able to be activated. The method can include receiving an activation instruction from an entity remote from the unmanned vehicle; determining whether or not the received activation instruction is valid by performing a validation process; and in response to determining that the received activation instruction is valid, activating the payload. In response to determining that the received activation instruction is not valid, activation of the payload may be prevented or opposed.

Abstract translation: 公开了一种装置和由该装置执行的方法，其中该装置可以安装在无人驾驶车辆上并被布置为作用在有效载荷上。 有效载荷可以安装在无人驾驶车辆上，并且在装置的作用下能够被激活。 该方法可以包括从远程无人驾驶车辆的实体接收激活指令; 通过执行验证过程来确定所接收到的激活指令是否有效; 并且响应于确定所接收到的激活指令是有效的，激活有效载荷。 响应于确定接收到的激活指令无效，可以防止或反对有效载荷的激活。

公开(公告)号：US09121669B1

公开(公告)日：2015-09-01

申请号：US08300378

申请日：1994-09-02

Applicant: Gregory L. Hyslop ,  John W. Kraemer ,  Kurt A. Mizgate

Inventor： Gregory L. Hyslop ,  John W. Kraemer ,  Kurt A. Mizgate

IPC: F41G7/22 ,  G05D1/00

CPC classification number: F41G7/2206 ,  B64C2201/121 ,  B64C2201/146 ,  F41G7/2253 ,  F41G7/2293 ,  G05D1/0033

Abstract: A system and method of guiding a remote aerial vehicle toward a designated target includes an imaging sensor which generates sequential video images of the target area from the remote aerial vehicle and transmits the images to a control center via the video portion of a communications data link. The control center receives and displays the plurality of video images on a video display. An image selection signal is generated at the control center and transmitted to the remote aerial vehicle for commanding the imaging sensor to continuously transmit one of the sequential video images. A target designation signal, corresponding to the azimuth and elevation of the desired target on the continuously displayed video image, is generated and transmitted via a command portion of the data link to the remote aerial vehicle. The target designation signal is processed and an updated target position is computed to compensate for time delays. A tracker tracks the updated target position to thereby guide the remote aerial vehicle toward the designated target. The video images and the target designation signal may be transmitted at low bandwidth frequencies to a satellite and relayed to the control center and the remote aerial vehicle respectively.

Abstract translation: 将远程航空器引导到指定目标的系统和方法包括：成像传感器，其从远程航空器生成目标区域的顺序视频图像，并且经由通信数据链路的视频部分将图像发送到控制中心。 控制中心在视频显示器上接收并显示多个视频图像。 在控制中心产生图像选择信号并发送到远程飞行器，以指示成像传感器连续发送顺序视频图像之一。 通过数据链路的命令部分生成并发送对应于连续显示的视频图像上的期望目标的方位角和仰角的目标指定信号到远程飞行器。 处理目标指定信号，并且计算更新的目标位置以补偿时间延迟。 跟踪器跟踪更新的目标位置，从而将远程飞行器引导到指定的目标。 视频图像和目标指定信号可以以低带宽频率传输到卫星并分别传送到控制中心和远程飞行器。

公开(公告)号：US20120211589A1

公开(公告)日：2012-08-23

申请号：US11455709

申请日：2006-06-20

Applicant: Burak Uzman

Inventor： Burak Uzman

IPC: F41G7/24 ,  F42B15/01 ,  F41G7/00

CPC classification number: F42B12/365 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/122 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F41G7/30 ,  F42B15/01 ,  F42B15/10 ,  G05D1/0038

Abstract: A lightweight, man-portable weapon delivery system includes a fuselage, and first and second wings mounted to opposing sides of the fuselage. The system includes an electric motor for driving a propeller for providing thrust to propel the system. The electric motor is mounted to the fuselage, and configured to be remotely started by a user. The system includes an imaging device mounted to the system and configured to capture images of a theater of operations of the system. The system includes a communication circuit in communication with the imaging device and configured to transmit the images from the imaging device to the user for viewing the theater of operations of the system for remotely steering the system. The communication circuit is configured to receive commands from the user for steering the system into the target. The system includes a payload configured to store the ordnance.

公开(公告)号：US20120061508A1

公开(公告)日：2012-03-15

申请号：US12639735

申请日：2009-12-16

Applicant: Gregoire de Viry ,  Guillaume Dupont

Inventor： Gregoire de Viry ,  Guillaume Dupont

IPC: F41G7/26 ,  F41G5/18

CPC classification number: B64C39/024 ,  B64C2201/121 ,  B64D1/04 ,  B64D7/08 ,  F41G3/145 ,  F41G3/22 ,  F41G7/226 ,  F41G7/2293

Abstract: The present invention relates to the field of unmanned air vehicles, more commonly designated drone. More specifically, the invention applies to an armed drone system (10), notably equipped with a firing device and a steerable optronics ball (B) comprising means of illuminating targets (C).The invention proposes that the firing device be oriented towards the rear, so as to reduce the problems of masking of the optronics ball (B) by elements located in its line of sight, such as a front wheel (FW) for example. Moreover, because of operational use involving a phase (10S) for firing weapons and illuminating the target (C) from the back, the armed drone (10) moving away from the target, the vulnerability of the drone (10) is lessened.

Abstract translation: 本发明涉及无人驾驶飞行器领域，更常见的是无人驾驶飞机。 更具体地，本发明适用于特别装备有点火装置和可转向光电子球（B）的武装无人机系统（10），其包括照明目标（C）的装置。 本发明提出了射击装置朝向后方，从而通过例如前轮（FW）等位于其视线内的元件来减少光电球（B）的掩蔽问题。 此外，由于涉及使用武器的阶段（10S）和从后面照射目标（C）的操作使用，武装无人机（10）远离目标，所以无人机（10）的脆弱性被减轻了。

公开(公告)号：US20090206193A1

公开(公告)日：2009-08-20

申请号：US11450720

申请日：2006-06-09

Applicant: David J. File

Inventor： David J. File

IPC: B64C3/54 ,  B64C1/00

CPC classification number: B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  Y02T50/14

Abstract: An apparatus for increasing an aerodynamic surface area of an aircraft, e.g., a wing thereof, includes coaxially disposed first and second elongated airfoils and an inflatable device arranged to move the first airfoil coaxially relative to the second airfoil. The second airfoil has a root end fixed to the vehicle and an opposite outboard end, and the first airfoil is arranged to move axially between a retracted position generally inboard of the outboard end of the second airfoil and a deployed position generally outboard thereof. When the movable airfoil is deployed, a latching mechanism locks it in position. The inflatable device can include a collapsible duct that is sealed at one end and coupled at a second end to an inflating source, such as a reservoir of a compressed gas or a pyrotechnic gas generator.

Abstract translation: 用于增加飞行器（例如其翼）的空气动力学表面积的装置包括同轴布置的第一和第二细长翼型件以及布置成使第一翼型件相对于第二翼型件同轴地移动的可充气装置。 第二翼型件具有固定到车辆的根部端部和相对的外侧端部，并且第一翼型件布置成在第二翼型件的外侧端部的大致内侧的缩回位置和大致在其外侧的展开位置之间轴向移动。 当可移动翼片展开时，闩锁机构将其锁定就位。 可膨胀装置可以包括可折叠的管道，其在一端被密封并且在第二端处连接到充气源，例如压缩气体或烟火气体发生器的储存器。

公开(公告)号：US07542828B2

公开(公告)日：2009-06-02

申请号：US11160645

申请日：2005-07-01

Applicant: Daniel W. Steele ,  Joseph R. Chovan

Inventor： Daniel W. Steele ,  Joseph R. Chovan

IPC: G01C23/00 ,  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。

公开(公告)号：US07481396B2

公开(公告)日：2009-01-27

申请号：US11398375

申请日：2006-06-14

Applicant: Jules G. Kish

Inventor： Jules G. Kish

IPC: B64C35/00

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。

公开(公告)号：US20050230535A1

公开(公告)日：2005-10-20

申请号：US10823434

申请日：2004-04-13

Applicant: Robert Ruszkowski

Inventor： Robert Ruszkowski

IPC: B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C1/00 ,  B64C1/06 ,  B64C35/00 ,  B64C37/00 ,  B64C39/00 ,  B64C39/02 ,  F41F3/07 ,  F42B15/20

CPC classification number: B64C1/062 ,  B63G8/28 ,  B63G8/30 ,  B63G13/00 ,  B64C35/00 ,  B64C37/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/205 ,  F41F3/07 ,  F42B15/20

Abstract: A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.

Abstract translation: 披露了一架海上发射和回收的无人机。 飞机是喷气式动力的，并具有保持水密完整性的特征和系统，使得其可以从潜水艇释放或由船或飞机落入水体。 这架飞机是浮力的，并且在其火箭点火之前保持在水面或附近。 火箭将空中车辆推出大海，并将其加速到飞行速度，此时喷气发动机起动，火箭被放弃。 机动车辆独立地或与其他机动车辆一起执行任务。 然后，空中飞行器通过例如发动机关闭“鞭炮”操纵返回到海上指定的飞溅点。 潜艇或船只可以检索空中飞行器并准备进行另一个飞行任务。

公开(公告)号：US20050178892A1

公开(公告)日：2005-08-18

申请号：US10756024

申请日：2004-01-12

Applicant: J. Box ,  Jules Kish

Inventor： J. Box ,  Jules Kish

IPC: B64C27/14 ,  B64C39/02 ,  B64D35/02 ,  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 1 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。1传输系统的尺寸最小，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：US20050082421A1

公开(公告)日：2005-04-21

申请号：US10901132

申请日：2004-07-29

Applicant: Pietro Perlo ,  Denis Bollea ,  Bartolo Pairetti ,  Stefano Alacqua ,  Roberto Finizio ,  Cosimo Carvignese ,  Piermario Repetto ,  Gianfranco Innocenti

Inventor： Pietro Perlo ,  Denis Bollea ,  Bartolo Pairetti ,  Stefano Alacqua ,  Roberto Finizio ,  Cosimo Carvignese ,  Piermario Repetto ,  Gianfranco Innocenti

IPC: B64C29/00 ,  A63H27/127 ,  A63H29/22 ,  B64C27/20 ,  B64C39/02 ,  B64C15/00

CPC classification number: B64C39/024 ,  A63H27/12 ,  A63H29/22 ,  B64C27/20 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146

Abstract: The flying machine includes a supporting structure including a central rotational support having a vertical axis connected to an essentially horizontal, preferably annular, peripheral support part, coaxial with the central support, at least one upper rotor including a central hub rotatable about the axis of the central support of the supporting structure, an outer channel-section ring supported by the peripheral part of the supporting structure by contactless suspension means, preferably magnetic suspension means, and a plurality of blades which extend from the hub to the channel-section ring and which are inclined with respect to the horizontal plane; and motor devices carried at least partially by the peripheral part of the supporting structure and operable to cause rotation of the rotor with respect to this structure in a predetermined direction.

Abstract translation: 飞行器包括支撑结构，其包括中心旋转支撑件，该中心旋转支撑件具有连接到基本上水平的，优选环形的外围支撑部分的垂直轴线，该中心旋转支撑件与中心支撑件同轴，至少一个上转子包括可围绕 支撑结构的中心支撑，通过非接触式悬挂装置，优选磁悬浮装置由支撑结构的周边部分支撑的外部通道截面环，以及从轮毂延伸到通道截面环的多个叶片， 相对于水平面倾斜; 以及至少部分地由支撑结构的周边部分承载的马达装置，并且可操作以使转子相对于该结构在预定方向上旋转。