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：US20120091284A1

公开(公告)日：2012-04-19

申请号：US12906096

申请日：2010-10-17

Applicant: Hosein Goodarzi

Inventor： Hosein Goodarzi

IPC: B64C29/00 ,  G01C21/00 ,  G05D1/00

CPC classification number: B64C39/024 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146

Abstract: The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servomotors and each of the plurality of the servomotors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a Vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servomotors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft.

Abstract translation: 本发明的各种实施例提供一种无人驾驶飞行器，其包括半球体，无刷电，螺旋桨，多个翼尖装置，多个伺服马达，多个伺服马达中的每一个连接到多个 的翼尖装置，多个碳棒和壳体。 无刷式电动机为垂直起降（VTOL）提供提升力，多个翼尖装置分为三种翼尖装置，三种翼尖装置由各自的伺服电机控制 以控制偏航，俯仰和侧倾运动，从而稳定和控制飞行器的运动。

公开(公告)号：US08104707B1

公开(公告)日：2012-01-31

申请号：US12190516

申请日：2008-08-12

Applicant: Osgar John Ohanian, III

Inventor： Osgar John Ohanian, III

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162

Abstract: Disclosed herein is a propulsion system, which may be implemented in an air-vehicle, such as a ducted-fan organic air-vehicle. The propulsion system comprises (a) a power source, (b) a fan located within a duct and powered by the power source, (c) a plurality of vanes arranged in an x-clocked configuration and configured to produce control moments from the flow generated by the fan. The maximum control moments, which can be created by the vanes in the x-clocked configuration, are substantially oriented along the flight axes of the air-vehicle or the principle axis of the maximum moment of inertia.

Abstract translation: 本文公开了一种推进系统，其可以在诸如管道式风扇有机机动车辆的空中车辆中实现。 推进系统包括（a）电源，（b）位于管道内并由电源供电的风扇，（c）以x时钟配置布置的多个叶片，并配置成从流动产生控制力矩 由风扇产生。 可以由x时钟配置中的叶片产生的最大控制力矩基本上沿着空中车辆的飞行轴线或最大惯性矩的主轴线定向。

公开(公告)号：US20110278391A1

公开(公告)日：2011-11-17

申请号：US12781039

申请日：2010-05-17

Applicant: Andrey KOTLER

Inventor： Andrey KOTLER

IPC: B64C33/00

CPC classification number: B64C39/028 ,  B64C33/02 ,  B64C2201/025 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/127

Abstract: A micro aerial vehicle apparatus capable of flying in different flight modes is disclosed. The apparatus includes a fuselage; at least one pair of blade-wings; and an actuator for actuating the blade-wings by flapping the blade-wings in dissonance or resonance frequencies.

Abstract translation: 公开了能够以不同飞行模式飞行的微型飞行器具。 该装置包括机身; 至少一对叶片翼; 以及致动器，用于通过以不相干或共振频率拍打叶片翼来致动叶片翼。

公开(公告)号：US20110204188A1

公开(公告)日：2011-08-25

申请号：US12712094

申请日：2010-02-24

Applicant: Robert Marcus

Inventor： Robert Marcus

IPC: B64C29/00

CPC classification number: B64C19/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/088 ,  B64D45/00

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110155860A1

公开(公告)日：2011-06-30

申请号：US12990964

申请日：2009-05-07

Applicant: Greg Chapman ,  Jakub Kawka ,  Christopher Kim Schlunke

Inventor： Greg Chapman ,  Jakub Kawka ,  Christopher Kim Schlunke

IPC: B64C27/20 ,  B64C15/02 ,  B64C29/00 ,  B64C7/00 ,  B64C39/02

CPC classification number: B64C27/20 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108

Abstract: A fluid dynamic device (100) for directing fluid flow to generate thrust comprising a thrust control shroud (130) disposed about a central axis (210) of said fluid dynamic device (100) for directing a fluid flow between an upstream fluid intake region (220) and a downstream fluid exit region (222), forming a fluid exit area, of said shroud (130) to generate thrust wherein a displacement of said fluid exit region (222) of said shroud (130) with respect to said central axis (210) results in a translation of said fluid exit area (222) such that the level of shear stress induced in that part of the shroud (130) disposed laterally to the direction of translation of the shroud (130) is minimised.

Abstract translation: 一种用于引导流体流动以产生推力的流体动力装置（100），包括围绕所述流体动力装置（100）的中心轴线（210）设置的推力控制罩（130），用于引导流体流在上游流体进入区域 220）和形成所述护罩（130）的流体出口区域的下游流体出口区域（222）以产生推力，其中所述护罩（130）的所述流体出口区域（222）相对于所述中心轴线 （210）的平移导致所述流体出口区域（222）的平移，使得在围绕护罩（130）的平移方向侧向设置的护罩（130）的那部分中引起的剪切应力水平最小化。

公开(公告)号：US20110101156A1

公开(公告)日：2011-05-05

申请号：US13001993

申请日：2009-07-01

Applicant: Key Nam Choi

Inventor： Key Nam Choi

IPC: B64C27/06 ,  B64C29/00

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127

Abstract: Conventional bottom blade type flight vehicles have a complex structure and complex flying control operations in that several pairs of fixing plates, and forward/backward and left and right rotation adjustment blades are separately mounted and adjusted to remove the anti-torque of the flight vehicle caused by the rotation of the propellers and to fly the flight vehicle, so that the flight vehicles has difficulties in scouting and surveillance of an indoor area due to the heavy weight and the great volume. The flight vehicle of the disclosure continuously rotates in a state in which the anti-torque is not removed by one adjustment blade. The flight vehicle stops, ascends, descends, advances forward, backward, leftward, or rightward, or left or right rotates, performs flight in a narrow space, scouting and surveillance in an indoor area with a simple structure, simple control, light weight, and small size, and increases power efficiency.

Abstract translation: 传统的底叶型飞行器具有复杂的结构和复杂的飞行控制操作，其中分别安装和调整了几对固定板，前/后和左右旋转调节叶片，以消除飞行车辆的抗扭矩 通过螺旋桨的旋转并飞行飞行器，使得由于重量大，体积大，飞行器车辆难以对室内进行侦察和监视。 本公开的飞行器在防转矩没有被一个调整叶片去除的状态下连续旋转。 飞行器停止，上升，下降，向前，向后，向左或向右前进，左右旋转，在狭窄的空间内进行飞行，在室内进行侦察和监视，结构简单，控制简单，重量轻， 体积小，效率高。

公开(公告)号：US07681832B2

公开(公告)日：2010-03-23

申请号：US11947585

申请日：2007-11-29

Applicant: John C. Colclough

Inventor： John C. Colclough

IPC: B64C15/00

CPC classification number: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

Abstract translation: 公开了一种管道风扇空气动力车辆和操作方法，用于在前进飞行操作中获得空气动力学提升和效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼包括在管道式风扇飞行器上，并且在向前飞行期间部署以提供空气动力学提升。 当车辆悬停时，翼或翼缩回，以减少翼对风中的稳定性的影响。 每个翼可以在缩回时符合车辆的曲率或轮廓，并且可以构造在一个或多个翼部中。 机翼或机翼可以自动部署和撤回，或者在操作员的指令下进行。 每个翼和相关部件可以集成到车辆中或者可以是可拆卸的。

公开(公告)号：US07658347B2

公开(公告)日：2010-02-09

申请号：US11492490

申请日：2006-07-25

Applicant: Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

Inventor： Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

IPC: B64F1/04

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/201

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Abstract translation: 微型飞行器（MAV）启动系统，提供组合功能：敏感车辆部件的包装保护，机械起动组件和发射台。 优选实施例包括容器和容器盖，其中MAV夹在盖上。 还设置在容器盖上的是起动组件。 将附加的MAV作为发射台的盖子从容器中取出，放在地面上，MAV以起动机构启动并启动。 这种布置可最大限度地减少操作人员的身体风险，最大限度地减少总体MAV系统的重量，消耗操作员运输系统的最小空间，并消除对电池更换或充电的电源线的依赖。

公开(公告)号：US20100025543A1

公开(公告)日：2010-02-04

申请号：US12262747

申请日：2008-10-31

Applicant: LLOYD E. KINSEY ,  Patrick Kranking

Inventor： LLOYD E. KINSEY ,  Patrick Kranking

IPC: B64C27/24

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。