公开(公告)号：WO2006112578A1

公开(公告)日：2006-10-26

申请号：PCT/KR2005/003266

申请日：2005-10-04

Applicant: OH, Won-Sup

Inventor： OH, Won-Sup

IPC: B64C29/00

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/162

Abstract: The present invention relates to a vertical take-off and landing (VTOL) aircraft, including a body (120), two or more rotary units (130) coupled to the body, each having both a rotating shaft (131) and a blade (135), and a casing (201) covering both the body and the rotary units and being provided with openings (201a). The casing (201) may be formed into a duct shape with an opening to receive the rotary unit therein, or may be provided with a sidewall (203) to surround the blade. Each opening (201a) may have a protective means (207). The reaction torques of the rotary units can balance each other without requiring a separate balancing device. The casing covers the blades, thus preventing the generation of unbalanced lift on the rotating blades, unlike conventional helicopters, when the VTOL aircraft flies forwards. Furthermore, because the rotary units are prevented from coming into contact with outside articles, the aircraft prevents breakage of the rotary units and damage to outside articles. Due to a structural feature of the casing, the thrust to propel the VTOL aircraft can be increased by about 10 ~ 15%. Furthermore, a rudder (301) is provided in the casing, thus allowing the VTOL aircraft to freely yaw or fly forwards and backwards according to the orientation of the rudder.

Abstract translation: 本发明涉及一种垂直起飞和降落（VTOL）飞行器，其包括主体（120），联接到主体的两个或更多个旋转单元（130），每个具有旋转轴（131）和叶片 135）和覆盖所述主体和所述旋转单元的外壳（201），并且设置有开口（201a）。 外壳（201）可以形成具有开口的导管形状，以在其中容纳旋转单元，或者可以设置有围绕叶片的侧壁（203）。 每个开口（201a）可以具有保护装置（207）。 旋转单元的反作用力可相互平衡，而不需要单独的平衡装置。 与常规直升机不同，当VTOL飞机向前飞行时，壳体覆盖叶片，从而防止在旋转叶片上产生不平衡的升力。 此外，由于防止旋转单元与外部物品接触，所以飞机防止旋转单元的破坏并损坏外部物品。 由于外壳的结构特点，推进VTOL飞机的推力可以提高约10〜15％。 此外，舵（301）设置在壳体中，从而允许垂直起落飞机根据舵的方向自由地偏航或向前和向后飞行。

公开(公告)号：WO2005060381A2

公开(公告)日：2005-07-07

申请号：PCT/US2004/020596

申请日：2004-06-25

Applicant: ADVANCED PROPULSION TECHNOLOGIES ,  HOFBAUER, Peter ,  MCCLEER, Patrick

Inventor： HOFBAUER, Peter ,  MCCLEER, Patrick

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/162 ,  F02B61/04 ,  F02B75/24 ,  F03G7/08 ,  H02K7/183 ,  H02K7/1884 ,  Y02E10/725

Abstract: The present invention is a rotary device that may be adapted for use as a propeller assembly and electrical generator for aerial vehicles or other vehicles intended for fluid media. In one example, the device includes a ring assembly having a plurality of centrally linked blades coupled to a rotatable common hub. Rotary motion of the ring assembly is facilitated by coupling it to an opposed cylinder, opposed piston, internal combustion. The ring assembly includes components of an electrical power generating system so that electrical power is produced from the rotation of the ring assembly.

Abstract translation: 本发明是一种旋转装置，其可适于用作用于飞行器或用于流体介质的其它车辆的螺旋桨组件和发电机。 在一个示例中，该装置包括环组件，其具有联接到可旋转公共毂的多个中心连接的叶片。 环组件的旋转运动通过将其联接到相对的气缸，相对的活塞，内燃来实现。 环组件包括发电系统的部件，使得从环组件的旋转产生电力。

公开(公告)号：WO2004060743A3

公开(公告)日：2005-03-31

申请号：PCT/US0339332

申请日：2003-12-09

Applicant: UNIV FLORIDA ,  IFJU PETER ,  LEE KYU-HO ,  ALBERTANI ROBERTO ,  MITRYK SHAWN J ,  BORIA FRANK J ,  ABDULRAHIM MUJAHID

Inventor： IFJU PETER ,  LEE KYU-HO ,  ALBERTANI ROBERTO ,  MITRYK SHAWN J ,  BORIA FRANK J ,  ABDULRAHIM MUJAHID

IPC: A63H27/00 ,  B64C3/56 ,  B64C39/02 ,  B64C33/02

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle (10) having a bendable wing (12) enabling the micro air vehicle to fly. The bendable wing (12) may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing (12) may be formed from one or more layers of material (22), and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle (10). In addition, the wing may be bent severely downwards by applying a force to tips (13) of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲机翼（12）的微型飞行器（10）。 可弯曲翼（12）可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼（12）可以由一层或多层材料（22）形成，并且翼可以具有弯曲，使得翼的凹面面向下。 机翼可以基本上抵抗向上弯曲并且可以将隆起力传递到微型飞行器（10）的中心体。 此外，机翼可能通过向机翼的尖端（13）施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过简单地从管中释放微型飞行器而从管展开。

公开(公告)号：WO2003004351A2

公开(公告)日：2003-01-16

申请号：PCT/IL2002/000529

申请日：2002-06-27

Applicant: E.L.S.E. ADVANCED SOLUTIONS LTD. ,  A.D. & D. AERO DESIGN DEVELOPMENT LTD. ,  YIFRACH, Aharon

Inventor： YIFRACH, Aharon

IPC: B64B

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract translation: 无人驾驶飞行器包括具有至少两个围绕中心部分大致对称​​布置的翼部的自主飞行翼。 每个翼部可枢转地附接到每个相邻部分，使得翼部可折叠以用于存储并且可展开。 优选的形式是所谓的具有四个翼部的海鸥翼。 车辆可以从母机飞行器编程，同时使用可能是无线的数据链路承载到部署区域。

公开(公告)号：WO01060692A1

公开(公告)日：2001-08-23

申请号：PCT/FR2001/000405

申请日：2001-02-13

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud (40) integral with a cylindrical fairing (16) wherein rotates a propeller (10) powered by an engine (12) housed in a fuselage (18) secured to the fairing (16) with radial arms (28) and straightening vanes (30).

Abstract translation: 本发明涉及一种远程控制的飞行器，特别是用于监视和检查，能够悬停并包括与圆柱形整流罩（16）成一体的球形耐开裂的护罩（40），其中旋转由螺旋桨（10）供电的螺旋桨 发动机（12），其容纳在用径向臂（28）和矫直叶片（30）固定到整流罩（16）的机身（18）中。

公开(公告)号：WO1993017908A1

公开(公告)日：1993-09-16

申请号：PCT/US1993002267

申请日：1993-03-12

Applicant: SCHMITTLE, Hugh

IPC: B64C03/38

CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) 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 (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).

Abstract translation: 垂直起落架飞机（10）包括一个自由翼（16），其在机身（12）的相对侧上具有彼此连接的翼，用于联合自由旋转，并且在飞行员，计算机或遥控器下进行差速俯仰设置。 在电梯（26），方向舵（24）和机翼的差距俯仰设置上分别进行垂直发射，俯仰，偏转和滚转控制。 在发射时，升降机（26）将机身（12）向下方延伸以改变推力矢量并向飞行器提供水平速度，由此自由翼（16）相对于机身（12）旋转成大致水平的方向以提供 在水平飞行期间升降。 从水平到垂直飞行的过渡是通过相反的过程实现的，并且飞机可以在弹性表面（例如网）（66）中或其上轻轻回收。