公开(公告)号：WO0189650A3

公开(公告)日：2002-03-07

申请号：PCT/US0116772

申请日：2001-05-23

Applicant: LIOTTA LANCE A

Inventor： LIOTTA LANCE A

IPC: A63H27/00 ,  B64C39/02 ,  B64C39/06 ,  B64C3/00

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。

公开(公告)号：WO01089650A2

公开(公告)日：2001-11-29

申请号：PCT/US2001/016772

申请日：2001-05-23

IPC: A63H27/00 ,  B64C39/02 ,  B64C39/06 ,  A63H

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 arranged in a radially symmetrical configuration around a central cavity, e.g., in a diagonal cube configuration. Suspended within the cavity is a thrust generating propeller system that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity 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: 一种专为遥控慢飞，室内或室外小场或场地设计的飞机。 空中提升体由一系列轻型的平面或薄翼型表面限定，例如以对角立方体构型围绕中心腔以径向对称的构造布置。 悬挂在空腔内的是推力发生螺旋桨系统，其向上倾斜并且可以远程调节，以便改变用于转向的空腔内的推力矢量的角度。 飞行中的运动方向的提升，稳定性，转动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。

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：WO2014207732A1

公开(公告)日：2014-12-31

申请号：PCT/IB2014/062731

申请日：2014-06-30

Applicant: BELLEZZA QUATER, Paolo

Inventor： BELLEZZA QUATER, Paolo

IPC: B64C27/20 ,  B64B1/34 ,  B64C3/30 ,  B64C39/02 ,  B64B1/30

CPC classification number: B64C39/024 ,  B64B1/34 ,  B64C3/30 ,  B64C27/20 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/101 ,  B64C2201/105 ,  B64C2201/165

Abstract: Described herein is a multi-rotor aircraft (10; 200) including: - a load-bearing structure (10A; 200A); and - a plurality of propulsion assemblies (M1, M2, M3, M4, M5, M6; M1', M2', M3', M4') each including a rotor (R1, R2, R3, R4, R5, R6; R1', R2', R3', R4'), which can be driven in rotation about a respective axis of rotation (X1, X2, X3, X4, X5, X6; X1', X2', X3', X4'), these propulsion assemblies being coupled to and supported by the load-bearing structure (10A; 200A), wherein the load-bearing structure (10A; 200A) is inflatable (C11, C12, C13, C14, C15, C16; C200).

Abstract translation: 这里描述的是多转子飞机（10; 200），包括： - 承重结构（10A; 200A）; 每个包括转子（R1，R2，R3，R4，R5，R6; R1）的多个推进组件（M1，M2，M3，M4，M5，M6; M1'，M2'，M3'，M4' （X1，X2，X3，X4，X5，X6; X1'，X2'，X3'，X4'）相对旋转驱动， 这些推进组件联接到承载结构（10A; 200A）并由其承载，其中承载结构（10A; 200A）是可膨胀的（C11，C12，C13，C14，C15，C16; C200）。

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：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

IPC: B64C39/02 ,  B63B35/52 ,  B64D17/80 ,  B64F1/02

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。

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：WO2005000671A2

公开(公告)日：2005-01-06

申请号：PCT/US2004/002979

申请日：2004-02-03

Applicant: ILC DOVER, INC.

Inventor： CADOGAN, David, P. ,  GRAZIOSI, David, Allen ,  LEE, Grant, Ryan ,  SCARBOROUGH, Stephen, Emerson ,  SMITH, Timothy, R.

IPC: B64C

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C2201/105

Abstract: A novel design and construction method for an inflatable, rigidizable wing for a terrestrial or planetary flying vehicle. The wing is caused to deploy from an initially packed condition and to assume its functional shape by means of an inflation gas. After inflation, the wing is rigidized by any of several means, such that the inflation gas is no longer required. The composite wing is fabricated from a base reinforcement material, often a fabric, which is coated with a polymer resin that hardens when exposed to a curing mechanism. Several activation mechanisms exist by which to initiate rigidization of such a structure, including elevated temperature, ultraviolet light, and chemical constituents of the inflation gas. The resultant wing has fundamental advantages compared to existing inflatable wings, including improved stiffness, and reduced susceptibility to structural failure in response to puncture.

Abstract translation: 一种用于陆地或行星飞行器的可充气，可固定翼的新颖设计和施工方法。 使机翼从初始包装状态部署，并通过充气气体承担其功能形状。 在膨胀之后，机翼通过几种手段中的任何一种来固定，使得不再需要膨胀气体。 复合翼片由基底增强材料制成，通常是织物，其涂覆有当暴露于固化机构时硬化的聚合物树脂。 存在几种启动机制，其通过其启动这种结构的刚性化，包括升高的温度，紫外线和膨胀气体的化学成分。 与现有的充气翼相比，所得的翼具有基本的优点，包括改善的刚度，以及减少对穿刺的结构性破坏的敏感性。