公开(公告)号：WO2017037698A1

公开(公告)日：2017-03-09

申请号：PCT/IL2016/050935

申请日：2016-08-25

Applicant: UVISION AIR LTD

Inventor： KAHLON, Moshe ,  MORAG, Amit

IPC: F42B10/14 ,  B64C3/56

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/203 ,  F42B10/14

Abstract: An unmanned air vehicle (UAV) having a fuselage, a foldable propulsion means to generate thrust leading to the UAV movement, a driving means to drive the propulsion means and a plurality of flight control surfaces actuators are further included. The UAV further includes at least one pair of foldable wings where the rear portion of the wings is pivotally attached to the fuselage. The wings having at least one roll control surface hinged to at least one of the foldable wings. At least a pair of tail stabilizers having ruddervators flight control surfaces hinged to the tail stabilizers. In a fully extended position or in ready to fly state position, each of the foldable wings are deployed perpendicular to one another and perpendicular to the fuselage to form an offset-x shaped wings, and in a stowed position, each of the wings are positioned parallel to one another and positioned parallel to the fuselage.

Abstract translation: 具有机身的无人驾驶飞行器（UAV），产生通向无人机移动的推力的可折叠推进装置，还包括驱动推进装置的驱动装置和多个飞行控制面致动器。 无人机还包括至少一对可折叠的翼，其中翼的后部可枢转地附接到机身。 所述翼具有铰接到所述可折叠翼中的至少一个的至少一个滚动控制表面。 至少一对具有舵机飞行控制面的尾部稳定器铰接到尾部稳定器上。 在完全延伸的位置或准备飞行状态的位置，每个可折叠翼彼此垂直并垂直于机身展开以形成偏移x形的翼，并且在收起位置中，每个翼定位 彼此平行并且平行于机身定位。

公开(公告)号：WO2015000088A1

公开(公告)日：2015-01-08

申请号：PCT/CH2014/000089

申请日：2014-06-27

Applicant: TAUSEL, Marco

Inventor： TAUSEL, Marco

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64B2201/00 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/105 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/203 ,  B64C2201/22

Abstract: To improve overall performance and reduce the weight of an unmanned aerial vehicle (UAV) an inflatable structure was invented to directly support systems for propulsion and control system of the UAV. Independent claims have been implemented to obtain a relatively small radar footprint, methods to obtain a reduced visibility, methods to realize a hybrid power supply, methods for transporting the different components of the inflatable UAV.

Abstract translation: 为了提高无人机（UAV）的整体性能和减轻重量，发明了一种充气结构，直接支持无人机的推进和控制系统。 已实施独立权利要求，以获得相对较小的雷达足迹，获得可见度降低的方法，实现混合动力供应的方法，运送可充气无人机的不同部件的方法。

公开(公告)号：WO2012130790A2

公开(公告)日：2012-10-04

申请号：PCT/EP2012/055298

申请日：2012-03-26

Applicant: PROX DYNAMICS AS ,  MUREN, Petter

Inventor： MUREN, Petter

IPC: B64C39/02

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C39/028 ,  B64C2201/024 ,  B64C2201/127 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2203/00 ,  B64D47/08

Abstract: The embodiments herein disclose a personal UAV kit for storing, preparing and remote control of micro UAVs. The UAV kit includes a base unit, a control unit and at least one UAV. The UAVs can typically be a winged aircraft with foldable wings or a helicopter with a two-bladed or foldable rotor. The base unit comprises UAV compartments for housing at least one UAV, a bay for storing the control unit, batteries and electronic components for charging, communication, control and processing and storing of data. In addition, the system includes an eye near display device for viewing system information and sensor data, typically live video, transmitted from the UAV.

Abstract translation: 本文的实施例公开了用于存储，准备和远程控制微型无人机的个人UAV套件。 UAV套件包括基本单元，控制单元和至少一个UAV。 无人机通常可以是具有可折叠翼的有翼飞机或具有双叶片或可折叠转子的直升机。 基座单元包括用于容纳至少一个UAV的UAV隔间，用于存储控制单元的舱，用于对数据进行充电，通信，控制和处理和存储的电池和电子组件。 此外，该系统包括用于观看系统信息的眼睛附近，以及从UAV发送的通常是实时视频的传感器数据。

公开(公告)号：WO2009048666A2

公开(公告)日：2009-04-16

申请号：PCT/US2008/070598

申请日：2008-07-21

Applicant: KEAVENEY, Kevin

Inventor： KEAVENEY, Kevin

IPC: B64C39/00

CPC classification number: B64C39/024 ,  B64C2201/102 ,  B64C2201/203 ,  B64C2201/206

Abstract: The invention is a method for launching and recovering a child aircraft, manned or unmanned, as well as providing a method for continuous flight to and from a parent aircraft, manned or unmanned, from a pylon that is mounted externally or internally on the parent aircraft. The pylon mechanics are contained within the pylon, and controlled from the parent aircraft, through hard wiring or electronic signals via a data link, facilitated by antennas on both the parent aircraft and the pylon.

Abstract translation: 本发明是一种用于发射和恢复载人或无人驾驶的儿童飞机的方法，以及提供一种方法，用于连续飞行从载客人员或无人驾驶的母机飞行员从外部或内部安装在母飞机上的塔架 。 塔架机械装置包含在塔架内，并由母机通过硬接线或电子信号通过数据链路进行控制，由母机和塔架上的天线辅助。

公开(公告)号：WO2007084186A3

公开(公告)日：2007-10-11

申请号：PCT/US2006032105

申请日：2006-08-17

Applicant: CHANG INDUSTRY INC ,  DE LA TORRE SAMUEL

Inventor： DE LA TORRE SAMUEL

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203

Abstract: An aerial surveillance device (100) is provided, comprising an image capturing device (150.) capable of being supported by an airframe structure (200) above the ground. The airframe structure includes a body portion (300) defining a longitudinal axis and configured to support the image - capturing device. A tail portion (400) having control surfaces (425,450) is operably engaged with the body portion along the axis. Transversely- extending wing portions (800, 850) are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars (800A, 800B, 850A, 850B) extending from a spaced-apart disposition at the body portion to a common connection (800C, 850C) distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member (900, 950) extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

Abstract translation: 提供了一种空中监视装置（100），包括能够由地面上方的机身结构（200）支撑的图像捕获装置（150）。 机身结构包括限定纵向轴线并构造成支撑图像捕获装置的主体部分（300）。 具有控制表面（425,450）的尾部（400）与主体部分沿轴线可操作地接合。 横向延伸的翼部（800,850）直接与主体部分接合。 每个翼部分由纵向相对的翼梁（800A，800B，850A，850B）限定，该翼梁从主体部分处的间隔布置延伸到远离主体部分的公共连接（800C，850C）。 翼梁具有在其间延伸的织物以提供机翼表面。 支撑构件（900,950）沿着每个翼部的横向于主体部分的空气动力学中心延伸，以张紧和刚化翼部，以便为翼部提供正弧形并形成翼型。

公开(公告)号：WO2006073750A3

公开(公告)日：2006-12-28

申请号：PCT/US2005045715

申请日：2005-12-16

Applicant: ALMAN JAMES

Inventor： ALMAN JAMES

IPC: B64C3/38

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203

Abstract: An unmanned aerial vehicle (UAV) having a design for optimum stowability and low cost. The UAV having a collapsible wing section which can be easily removed from the fuselage, allowing for quick assembly and disassembly and ease of portability. The unmanned aerial vehicle includes a primary wing assembly, a fuselage, a means for propelling the unmanned aerial vehicle , and means for remotely controlling the unmanned aerial vehicle. The primary wing assembly includes a wing having a center spar and two outwardly diverging side spars. The wing also has a pliable flexible material supported by the center spar and the at least two outwardly diverging side spars. The pylon is connected to the wing and supports the wing. The fuselage is connected to the pylon such that the pylon extends away from the fuselage and spaces the wing a distance from the fuselage. The fuselage includes a tail having a rudder located along a trailing edge and elevators located along the trailing edge.

Abstract translation: 无人飞行器（UAV）具有最佳的可收藏性和低成本的设计。 无人机具有可折叠的机翼部分，可以方便地从机身中移除，从而实现快速组装和拆卸，便于携带。 无人飞行器包括主翼组件，机身，用于推动无人驾驶飞行器的装置，以及用于远程控制无人驾驶飞行器的装置。 主翼组件包括具有中心翼梁和两个向外发散的侧翼的翼。 机翼还具有由中心翼梁和至少两个向外发散的侧翼支撑的柔韧的柔性材料。 塔架连接到机翼并支撑机翼。 机身连接到挂架，使得吊架远离机身延伸，并将机翼与机身隔开一段距离。 机身包括尾部，尾部沿着后缘设有方向舵，沿着后缘设有电梯。

公开(公告)号：WO2005023642A2

公开(公告)日：2005-03-17

申请号：PCT/US2004/004720

申请日：2004-02-19

Applicant: AAI CORPORATION ,  MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

Inventor： MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

IPC: B64B

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract translation: 提供了一种便携式无人驾驶飞行器和发射系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于发射气体的发射气藏; 操作地连接到发射气体储存器并具有位于空中载体的压力管中的自由端的发射管; 位于发射管内的自由活塞; 和自由活塞止挡件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中，并且将自由活塞从初始位置推动到自由活塞由自由活塞停止的终止位置。

公开(公告)号：WO03059735A2

公开(公告)日：2003-07-24

申请号：PCT/US0241280

申请日：2002-12-19

Applicant: ARLTON PAUL E ,  ARLTON DAVID J

Inventor： ARLTON PAUL E ,  ARLTON DAVID J

IPC: B64C27/10 ,  B64C39/02 ,  B64C

CPC classification number: G08B13/19621 ,  B64C27/10 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/208 ,  G08B13/19619 ,  G08B13/1963

Abstract: A flying micro-rotorcraft unit is provided for remote tactical and operational missions. The unit includes an elongated body having an upper and a lowe end. The body defines a vertical axis. The unit further includes a navigation module including means for determining a global position of the elongated body during flight of the unit. Rotor means of the unit is coupled to the upper end of the elongated body for generating a thrust force that acts in a direction parallel to the verical axis to lift the elongated body into the air. The rotor means is located between the elongated body and the navigation module.

Abstract translation: 提供了一个飞行的微型旋翼航空器，用于远程战术和作战任务。 该单元包括具有上端和下端的细长体。 身体定义垂直轴。 该单元还包括导航模块，其包括用于在单元飞行期间确定细长主体的全局位置的装置。 该单元的转子装置联接到细长主体的上端，用于产生一个推力，该推力作用在平行于虚拟轴线的方向上，以将细长主体提升到空气中。 转子装置位于细长主体和导航模块之间。

公开(公告)号：CN205989812U

公开(公告)日：2017-03-01

申请号：CN201620537213.2

申请日：2016-06-03

Applicant: 瑞德利斯技术公司

Inventor： 史蒂芬·魏森伯格

IPC: B64C27/08 ,  B64C1/30

CPC classification number: B64C39/024 ,  B64C27/006 ,  B64C2201/027 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/203

Abstract: 根据本实用新型的一个方面，提供了一种多旋翼无人机，其中臂从中央本体延伸出并支撑主要提供向上的推力的电机和螺旋桨。每个臂能够在连接至中央结构的连接点处通过铰链沿多旋翼无人机的竖直轴线折叠，臂在飞行期间可通过由第二结构施加的夹持力锁定在适当位置，其中第二结构可以是可拆除的或者相对于中央结构可旋转的。在任意两个相邻臂之间具有挠性连接件，当臂固定在飞行位置时挠性连接件拉紧，而当臂折叠至合拢位置时挠性连接件变得松弛，并且挠性连接件可用于通过使用绳扣或其它摩擦类设备以及手系的结中的任意一个将臂固定在合拢位置。