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公开(公告)号：US20060226280A1
公开(公告)日：2006-10-12
申请号：US11305524
申请日：2005-12-16
Applicant: James Alman
Inventor： James Alman
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。
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公开(公告)号：US06793172B2
公开(公告)日：2004-09-21
申请号：US10296137
申请日：2003-06-30
Applicant: Lance A. Liotta
Inventor： Lance A. Liotta
IPC: B64C300
CPC classification number: B64C39/066 , A63H27/00 , B64C39/028 , B64C2201/105 , B64C2201/107
Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.
Abstract translation: 一种专为遥控慢速飞行，室内或室外小型场地设计的飞机。 升降体由一系列以径向对称构造布置的轻型平面或薄型翼型表面（A1，A2，A3，A4）限定。 悬挂在由薄翼面（A1，A2，A3，A4）形成的空腔（O）内的是推力发生螺旋桨系统（C），其向上倾斜并且可以远程调节，以便改变推力角 在腔（O）内的向量用于转向。 飞行中的运动方向的提升，稳定性，转向和一般控制是在没有任何正式的机翼，方向舵，尾翼或控制面的情况下完成的。
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公开(公告)号：US20020193914A1
公开(公告)日：2002-12-19
申请号：US10045777
申请日：2002-01-11
Inventor： Tony L. Talbert , John Mark Kulo
IPC: B64C013/00
CPC classification number: B64C13/50 , B64C31/036 , B64C39/024 , B64C2201/044 , B64C2201/105 , B64C2201/107 , B64C2201/123 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D47/08
Abstract: A remote-control powered parafoil aircraft has an aircraft body (1) that is engine powered and hung with lines (2) from an air-expandable wing (3, 30). The lines include control lines (15) with which air flow and aerodynamic shape of the air-expandable wing are variable selectively from a foil controller (18, 19, 20) on the aircraft body for flight-mode control. Sight from a television camera (8) on the aircraft body is televised to a control unit (9) from which control data is transmitted selectively from proximate the control unit to the foil controller (14) with a multi-axis joystick or similar control, to an engine (6) on the parafoil body from an engine controller (24) and to an item servo (29) for control of optional items (45) on the aircraft body.
Abstract translation: 遥控动力的parafoil飞机具有发动机动力并悬挂有来自可膨胀翼（3,30）的线（2）的飞机主体（1）。 这些管线包括控制线（15），空气膨胀翼的空气流动和空气动力学形状可选择性地从飞行器体上的箔控制器（18,19,20）可变地进行飞行模式控制。 来自飞机机体上的电视摄像机（8）的视线被电视传送到控制单元（9），控制数据通过多轴操纵杆或类似的控制从控制单元的附近被选择性地发送到箔片控制器（14） 从发动机控制器（24）到达副翼车体上的发动机（6）和用于控制飞机主体上的可选项（45）的物品伺服（29）。
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公开(公告)号：US4311290A
公开(公告)日：1982-01-19
申请号：US90205
申请日：1979-11-01
Applicant: Kenneth T. Koper
Inventor： Kenneth T. Koper
IPC: B64F1/02
CPC classification number: B64F1/02 , B64C2201/105 , B64C2201/107 , B64C2201/182 , B64C2201/185
Abstract: Apparatus and method for recovering and arresting an aircraft or other vele. A boom is swivelly connected to a support structure via braking mechanism. The boom is pivotally connected to the brake mechanism such that it can also pivot in a second, different plane intersecting the plane of rotation of the brake mechanism. A shear pin prevents pivoting of the boom in the second plane until the boom has experienced a predetermined load in that plane. The distal end of the boom distant from the brake mechanism is provided with structure for engaging the aircraft. When the aircraft is flown at and captured by the boom, the weight and motion of the aircraft breaks the shear pin, causing the boom to move in the second plane until engaged by a stop. This rapid change in position of the engaging end of the boom in the second plane prevents the aircraft from pendulating about the boom. Forward motion of the aircraft also causes movement within the brake mechanism in the first plane which absorbs the kinetic energy of the aircraft as the boom swivels against the brake mechanism, so that the aircraft is slowed and arrested.
Abstract translation: 用于恢复和阻止飞机或其他车辆的装置和方法。 动臂通过制动机构旋转地连接到支撑结构。 吊杆枢转地连接到制动机构，使得其也可以在与制动机构的旋转平面相交的第二不同平面中枢转。 剪切销防止悬臂在第二平面中的枢转，直到悬臂在该平面中经历了预定的载荷。 离开制动机构的悬臂的远端设置有用于接合飞行器的结构。 当飞机飞行并被悬臂捕获时，飞行器的重量和运动会破坏剪切销，导致吊臂在第二平面中移动，直到停止。 在第二平面中，起重臂的接合端的这种快速变化防止飞机在吊杆周围摆动。 飞行器的前进运动也引起在第一平面内的制动机构内的运动，当悬臂靠在制动机构上转动时吸收飞行器的动能，从而使飞行器减慢和停止。
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公开(公告)号：KR101903002B1
公开(公告)日：2018-10-01
申请号：KR1020170038457
申请日：2017-03-27
Applicant: 주식회사 올브릿지 , 부산대학교 산학협력단
CPC classification number: G01W1/08 , B64C39/02 , B64C2201/02 , B64C2201/101 , B64C2201/107 , B64C2201/12 , G01D21/02 , G01W2201/00
Abstract: 본발명은헬륨충진탐사체에대한것으로서, 중심이편심된우산형태의연과, 연내부에다수개의부력챔버가구비되어강한바람이불더라도수직을유지할수 있는헬륨충진탐사체에관한것이다. 본발명은중심이편심된우산형태의연과그 내부를채우는다수개의부력챔버를이용하여강한바람이불더라도수직을유지할수 있는헬륨충진탐사체를제공할수 있다. 또한, 본발명은연에장착된지지대에수평대를장착하여헬륨충진탐사체를더욱수직으로유지시킬수 있다.
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Patent Agency Ranking
公开(公告)号：WO2016012695A1
公开(公告)日：2016-01-28
申请号：PCT/FR2015/051936
申请日：2015-07-15
Applicant: INSTITUT POLYTECHNIQUE DE GRENOBLE
Inventor： LOZANO, Rogelio
CPC classification number: F03D9/32 , A63H27/08 , B63H9/0685 , B64C31/06 , B64C39/022 , B64C39/024 , B64C2201/04 , B64C2201/107 , F03D5/00 , F03D9/00 , F03D9/25 , F03D13/20 , Y02E10/70 , Y02E10/728
Abstract: L'invention concerne un dispositif aéroporté (10) comprenant au moins trois ailes portantes (12) et un dispositif de liaison (18), les ailes étant reliées entre elles par des premiers câbles flexibles (16), chaque aile étant, en outre, reliée au dispositif de liaison (18) par un deuxième câble flexible (20), le dispositif de liaison étant relié à un troisième câble flexible (22) destiné à être relié à une base (46, 48), les premiers, deuxièmes et troisième câbles étant tendus lorsque le dispositif aéroporté est mis au vent.
Abstract translation: 本发明涉及一种包括至少三个支撑翼（12）和连接装置（18）的机载装置（10），所述翼通过第一柔性缆线（16）彼此连接，每个翼进一步连接到所述连接装置 （18）通过第二柔性电缆（20）连接，所述连接装置连接到旨在连接到基座（46,48）的第三柔性电缆（22），所述第一，第二和第三电缆在空中 设备被携带在风中。
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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。
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公开(公告)号：WO2007086055A1
公开(公告)日：2007-08-02
申请号：PCT/IL2007/000090
申请日：2007-01-25
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. , SOMECH, Haim
Inventor： SOMECH, Haim
CPC classification number: B64C39/024 , B63B35/52 , B64C2201/021 , B64C2201/084 , B64C2201/088 , B64C2201/104 , B64C2201/105 , B64C2201/107 , B64C2201/127 , B64C2201/145 , B64C2201/165 , B64C2201/182 , B64C2201/185 , B64C2201/205 , B64F1/02
Abstract: The invention provides a system, method and landing device for landing an aircraft (50) with respect to a predetermined landing location (P). The aircraft is configured for powered flight at least when the parafoil (60) is deployed, and includes an automatic landing system for controllably executing a landing approach maneuver for the aircraft while in free powered flight with the parafoil deployed to enable the aircraft to be brought into overlying proximity with the landing location. A landing device in the form of an energy absorbing landing net arrangement (20) is provided at the landing location for enabling the aircraft to be landed thereon at least partially vertically when in overlying proximity, and for dampening the landing impact of the aircraft.
Abstract translation: 本发明提供了一种用于相对于预定着陆位置（P）降落飞机（50）的系统，方法和着陆装置。 该飞机至少在翼展（60）部署时配置为动力飞行，并且包括一个自动着陆系统，用于在自由动力飞行中可控制地执行飞机的着陆进场操纵，其中部署了翼型飞机以使飞机能够被带到 与着陆位置相邻。 在着陆位置处设置能量吸收着陆网装置（20）形式的着陆装置，用于使飞机在覆盖在邻近位置时至少部分垂直地落在其上，并用于减轻飞机的着陆冲击。
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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。
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50.发明申请
公开(公告)号：WO2017134659A1
公开(公告)日：2017-08-10
申请号：PCT/IL2017/050119
申请日：2017-02-01
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： ZIVAN, Lior , DEKEL, Guy
IPC: B64D1/18
CPC classification number: B64D1/18 , A01C23/00 , B64C31/036 , B64C39/024 , B64C2201/107 , B64C2201/128 , B64C2201/145
Abstract: There is provided an aerial platform comprising a spraying module, one or more actuators operatively coupled to the spraying module, at least a sensor for acquiring data indicative of altitude, wherein at least a controller is configured to control a position of the spraying module relatively to the aerial platform based on control signals generated during control cycles and applicable to the one or more actuators, the controlling comprising cyclically acquiring with said sensor data indicative of an altitude of a surface area in the flight path direction of the aerial platform, wherein said surface area is to be sprayed in a next control cycle, generating a control signal based on at least said acquired data, so as to maintain the altitude of the spraying module at a required distance of the altitude of the surface, and applying the generated control signal to the one or more actuators. There is also provided methods and systems for controlling a motion of the spraying module.
Abstract translation: 提供了一种高空平台，其包括喷射模块，可操作地耦合到喷射模块的一个或多个致动器，至少一个用于采集表示高度的数据的传感器，其中至少一个控制器被配置为控制 基于在控制周期期间生成的并且可应用于所述一个或多个致动器的控制信号来确定所述喷洒模块相对于所述高空平台的位置，所述控制包括利用所述传感器周期性地采集指示飞行路径方向上的表面区域的高度的数据 其中所述表面区域将在下一个控制循环中被喷射，至少基于所述获取的数据生成控制信号，以便将喷射模块的高度保持在所述高度的所需距离处 表面，并且将生成的控制信号应用于一个或多个致动器。 还提供了用于控制喷涂模块的运动的方法和系统。
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