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1. 发明授权

US09920706B1 Methods of laser powering unmanned aerial vehicles with heat engines 有权
公开(公告)号：US09920706B1
公开(公告)日：2018-03-20
申请号：US15009080
申请日：2016-01-28
申请人： Dmitriy Yavid , Stephen Jon Blank
发明人： Dmitriy Yavid , Stephen Jon Blank
IPC分类号： F02G1/02 , B64G1/40 , F01B17/02 , F03G7/00 , B64C39/02 , H05B7/18 , F01B29/10
CPC分类号： 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
摘要： 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.

2. 发明申请

US20160046372A1 Rocket Morphing Aerial Vehicle 审中-公开
标题翻译：火箭变形飞行器
公开(公告)号：US20160046372A1
公开(公告)日：2016-02-18
申请号：US14722104
申请日：2015-05-26
申请人： L'Garde, Inc.
发明人： Nathaniel C. Barnes , Amir Shahram Gohardani
IPC分类号： B64C39/02 , B64D17/80 , B64F1/10
CPC分类号： B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/046 , B64C2201/082 , B64C2201/185
摘要： A rocket morphing aerial vehicle has a first rocket configuration and a second aerial vehicle configuration. The rocket morphing aerial vehicle may be used to deploy an aerial vehicle at further distances faster. The rocket configuration may be used to get the aerial vehicle to its desired location, while the aerial vehicle is used for the desired task. The rocket morphing aerial vehicle may include a deceleration mechanism such that the speed of the rocket does not interfere with the deployment of the aerial vehicle.
摘要翻译：火箭变形飞行器具有第一火箭构型和第二空中飞行器构造。火箭变形飞行器可以用于更快地部署更远的飞行器。可以使用火箭配置来将空中飞行器用于所需的位置，而空中飞行器则用于所需的任务。火箭变形飞行器可以包括减速机构，使得火箭的速度不会干扰飞行器的展开。

3. 发明申请

US20110204188A1 ROTOCRAFT 有权
公开(公告)号：US20110204188A1
公开(公告)日：2011-08-25
申请号：US12712094
申请日：2010-02-24
申请人： Robert Marcus
发明人： Robert Marcus
IPC分类号： B64C29/00
CPC分类号： B64C19/00 , B64C29/0058 , B64C39/024 , B64C2201/027 , B64C2201/046 , B64C2201/088 , B64D45/00
摘要： An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.
摘要翻译：飞行器包括独立控制的水平推进器和垂直升降器，以提供设计和操作简单性，同时允许六度自由度的精确飞行和使用诸如工具，传感器和仪器的安装设备。每个水平推进器和垂直升降器可以安装为恒定间距的固定轴转子，同时仍然允许精确控制偏航，俯仰，滚动，水平运动和垂直高程。陀螺仪和倾斜仪可用于进一步提高飞行精度。控制器管理施加水平推进器和垂直升降器的推力，以补偿由使用安装在飞行器上的工具和其他装置产生的力和扭矩。

4. 发明申请

US20030127559A1 Circular vertical take off & landing aircraft 失效
标题翻译：圆形垂直起降飞机
公开(公告)号：US20030127559A1
公开(公告)日：2003-07-10
申请号：US10084749
申请日：2002-02-26
发明人： Eric Ronald Walmsley
IPC分类号： B64C029/00
CPC分类号： B64C27/20 , B64C29/0066 , B64C39/001 , B64C39/024 , B64C39/06 , B64C39/062 , B64C2201/027 , B64C2201/046 , B64C2201/048 , B64C2201/108 , B64C2201/121 , B64C2201/127
摘要： A circular VTOL aircraft with a central vertically mounted jet or rocket engine 7, (or engines) having below vertical thrust vents 14 at cardinal points, together with a jet rocket engine 20 (or engines) horizontally mounted on turntable pod 16 which is steerable through 360 degrees and centrally situated below the vertical engine (s). Alternatively the horizontal engine can be replaced by central thrust vent 36 delivering thrust from the vertical engine to vectored thrust nozzle 37 attached to the turntable. Thrust from the four vertical thrust vents is controlled by valves 21 giving VTOL thrust control as well as pitch and bank control. The horizontal engine provides acceleration and retro-thrust for horizontal flight and directional control through 360 degrees. The passenger cabin is situated in the main body of the aircraft. Fuel tanks are installed around the central engines. The flight-deck is situated at the top-centre of the craft above the engines, which are detachable for maintenance.
摘要翻译：一个圆形垂直起降飞机，其中心垂直安装的喷气式或火箭发动机7（或发动机）在主要点处具有低于垂直推力通风口14，以及水平安装在转盘舱16上的喷气式火箭发动机20（或发动机），该喷射式火箭发动机20可引导通过 360度并位于垂直发动机的下方。或者，水平发动机可以由中心推力孔36代替，其将来自垂直发动机的推力传递到附接到转盘的向量推力喷嘴37。来自四个垂直推力通风口的推力由阀门21控制，提供垂直起动器推力控制以及俯仰和组合控制。水平发动机提供加速度和逆向推力，用于水平飞行和360度方向控制。客舱位于飞机的主体。燃油箱安装在中央发动机周围。飞行甲板位于发动机上方的工艺的顶部中心，可拆卸以进行维护。

5. 发明授权

US5340057A Thrust vectoring free wing aircraft 失效
标题翻译：推力矢量自由翼飞机
公开(公告)号：US5340057A
公开(公告)日：1994-08-23
申请号：US850913
申请日：1992-03-13
申请人： Hugh Schmittle
发明人： Hugh Schmittle
IPC分类号： B64C3/38 , B64C29/00 , B64C29/02 , B64C39/02 , B64C39/04
CPC分类号： B64C39/024 , B64C29/0033 , B64C29/02 , B64C3/385 , B64C39/04 , B64C2201/044 , B64C2201/046 , B64C2201/084 , B64C2201/088 , B64C2201/104 , B64C2201/146 , B64C2201/165 , B64C2201/182 , B64D2201/00
摘要： The VTOL aircraft includes a free wing having wings on opposite sides of the fuselage connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators, rudder and the differential pitch settings of the wings, respectively. At launch, the elevator pitches the fuselage nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing freely rotates relative to the fuselage into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and tile aircraft may be gently recovered in or on a resilient surface such as a net.
摘要翻译：垂直起落架飞机包括一个自由翼，在机身的相对两侧具有彼此连接的翼，用于联合自由旋转，并在飞行员，计算机或遥控器下进行差距俯仰设置。在垂直发射时，俯仰，偏航和侧倾控制分别由电梯，方向舵和翼的差距俯仰设置来实现。在发射时，升降机将机身鼻部向下倾斜以改变推力矢量并向飞行器提供水平速度，由此自由翼相对于机身自由旋转成大致水平的方向以在水平飞行期间提供升力。从水平飞行到垂直飞行的过渡是通过相反的过程实现的，瓦片飞机可以在诸如网络的弹性表面中或其上轻轻地回收。

6. 发明授权

US4730793A Ordnance delivery system and method including remotely piloted or programmable aircraft with yaw-to-turn guidance system 失效
标题翻译：兵器交付系统和方法包括遥控或可编程飞机与偏航转弯导向系统
公开(公告)号：US4730793A
公开(公告)日：1988-03-15
申请号：US566163
申请日：1984-01-26
申请人： Charles H. Thurber, Jr. , Frederick A. Behrens , John H. Hunton
发明人： Charles H. Thurber, Jr. , Frederick A. Behrens , John H. Hunton
IPC分类号： B64C39/02 , B64F1/10 , F41G7/00 , F41G7/22 , F42B15/053
CPC分类号： B64C39/024 , B64F1/10 , F41G7/007 , F41G7/22 , B64C2201/044 , B64C2201/046 , B64C2201/084 , B64C2201/102 , B64C2201/128 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64C2201/201 , B64C2201/208
摘要： A method and system for delivery ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.
摘要翻译：公开了一种用于通过远程驾驶或可编程的飞行器对目标进行运送的方法和系统，包括偏航转向引导系统，用于飞机的部署和发射系统以及包装。

7. 发明申请

US20180251218A1 Space Combat Drone 审中-公开
公开(公告)号：US20180251218A1
公开(公告)日：2018-09-06
申请号：US15760259
申请日：2016-09-16
申请人： Christopher Wilkinson
发明人： Christopher Wilkinson
IPC分类号： B64C39/02 , B64D1/04
CPC分类号： B64C39/024 , B64C2201/02 , B64C2201/046 , B64C2201/082 , B64C2201/121 , B64C2201/123 , B64C2201/206 , B64C2201/22 , B64D1/04
摘要： An unmanned aerial combat vehicle system is disclosed. The system provides for an unmanned aerial combat vehicle that is capable of performing reconnaissance, disrupting enemy communications, or delivering a weaponized payload. The unmanned aerial combat vehicle may also be equipped with a cloaking mechanism, where it can mask it's heat signature, or simulate an image on its outer surface.

8. 发明申请

US20140027579A1 HAND LAUNCHABLE UNMANNED AERIAL VEHICLE 有权
标题翻译：手动无人驾驶的空中客车
公开(公告)号：US20140027579A1
公开(公告)日：2014-01-30
申请号：US13790655
申请日：2013-03-08
申请人： Gerald Miller , James Stewart
发明人： Gerald Miller , James Stewart
IPC分类号： B64C19/00
CPC分类号： B64C19/00 , B64C39/028 , B64C2201/046 , B64C2201/084 , B64C2201/104 , B64C2201/127 , B64C2201/141 , B64C2201/201 , B64C2201/203 , F41F3/042 , F41G7/008 , F41G7/2206 , F41G7/2253 , F41G7/2293 , F42B12/20 , F42B12/365 , F42B15/01 , F42B15/10 , G05D1/12
摘要： An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.
摘要翻译：一种无人驾驶飞行器，其包括在搜索操作模式下操作的控制器，其中采集传感器的接收器搜索目标并使飞行控制表面以向下的螺旋路径引导车辆，其中采集传感器检测到的操作的终端操作目标并使飞行控制表面引导车辆朝向目标;以及激活操作模式，其中触发传感器检测到与车辆预定距离内的目标，并且控制器激活响应者。

9. 发明申请

US20120043411A1 UNMANNED AERIAL VEHICLE SYSTEM 审中-公开
标题翻译：无人驾驶航空系统
公开(公告)号：US20120043411A1
公开(公告)日：2012-02-23
申请号：US13149576
申请日：2011-05-31
申请人： Peter Joseph Beck , Nikhil Raghu
发明人： Peter Joseph Beck , Nikhil Raghu
IPC分类号： F42B15/08 , F42B10/14 , H04N7/18 , B64D17/80
CPC分类号： B64C39/024 , B64C2201/046 , B64C2201/127 , B64C2201/141 , B64C2201/185 , B64C2201/201 , F41F3/042 , F41F3/045 , F42B15/08 , F42B15/10 , H04N7/183
摘要： A UAV includes: a rocket body, having a rocket motor and a payload section; a parachute coupled with the payload section; an image capture device; a magnetometer to provide a compass reference for images taken from the image capture device; and a transmitter to communicate image and compass data to a remote receiver. Compass bearings are overlaid on image data from the image capture device. A handheld launch unit includes an ignition system, having an activation mechanism and an igniter to activate the rocket motor. A safety pin prevents electrical current from flowing to the igniter until the pin is removed. An accelerometer and/or magnetometer determines an angular orientation of the UAV. Software verifies that the angle is within a user-defined safety limit before activating the igniter.
摘要翻译：无人机包括：具有火箭发动机和有效载荷部分的火箭主体; 与有效载荷部分相连的降落伞; 图像捕获装置; 磁力计，用于为从图像捕获装置拍摄的图像提供罗盘参考; 以及用于将图像和罗盘数据传送到远程接收器的发射器。指南针轴承覆盖在图像捕获装置的图像数据上。手持式发射单元包括具有启动机构和点火器来激活火箭发动机的点火系统。一个安全销防止电流流到点火器，直到引脚被移除。加速度计和/或磁力计确定无人机的角度取向。激活点火器之前，软件将验证角度在用户定义的安全极限内。

10. 发明授权

US06926235B2 Runway-independent omni-role modularity enhancement (ROME) vehicle 有权
标题翻译：跑道独立的全能模块化增强（ROME）车辆
公开(公告)号：US06926235B2
公开(公告)日：2005-08-09
申请号：US10600400
申请日：2003-06-20
申请人： Richard P. Ouellette , Aaron J. Kutzmann
发明人： Richard P. Ouellette , Aaron J. Kutzmann
IPC分类号： B64C1/00 , B64C29/00 , B64C39/02 , B64D7/00
CPC分类号： B64C1/00 , B64C29/0058 , B64C39/024 , B64C2201/046 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/121 , B64C2201/165 , B64C2201/167 , B64C2201/187 , B64D7/00
摘要： A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.
摘要翻译：模块化组件组可配置成形成多个具有飞行能力的平台。多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。多个任务专用面板各自可拆卸地连接到相对的壁之一。至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

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