公开(公告)号：US20050153812A1

公开(公告)日：2005-07-14

申请号：US10756031

申请日：2004-01-12

Applicant: J. Box ,  Jules Kish

Inventor： J. Box ,  Jules Kish

IPC: B64C39/02 ,  B64D35/00 ,  F16H1/20 ,  F16H1/22 ,  F16H1/28 ,  F16H13/04 ,  F16H3/74

CPC classification number: B64C39/024 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/00 ,  F16H1/20 ,  F16H1/227 ,  F16H13/04

Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The transmission system includes a traction drive stage that provides a reduction ratio preferably having a value of at least 7, and most preferably greater than 9. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.

Abstract translation: 与微型涡轮发动机结合使用的用于推进飞机机体（例如基于螺旋桨的固定翼飞行器或基于转子的垂直升降飞机）或用于各种其它应用的传动系统。 微型涡轮发动机的输出轴优选地在72,000RPM和150,000RPM之间的转速下工作，输出功率在150HP和5HP之间（最优选地在50,000RPM和200,000RPM之间的扩展范围内工作，并且输出 功率在200 HP和5 HP之间）。 传动系统包括牵引驱动台，其优选地具有至少7的值，最优选地大于9的减速比。传动系统的尺寸最小，最好具有小于12英寸的最大直径。 优选地，传动系统的输入级是自平衡的，使得第一轴可以被支撑而没有轴承，并且通过外径引导的花键联接机构可操作地联接到微型涡轮发动机的输出轴。 对于垂直升降应用，可以使用单个牵引台以及锥齿轮组件或其他轴传动机构来提供必要的RPM减小。

公开(公告)号：US06691949B2

公开(公告)日：2004-02-17

申请号：US10191733

申请日：2002-07-08

Applicant: John M. Plump ,  Neil R. Gupta

Inventor： John M. Plump ,  Neil R. Gupta

IPC: B64C2722

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.

Abstract translation: 一种包括具有纵向轴线的环形机身的航空器以及沿着纵向轴线在机身的前缘和后缘之间延伸的管道，同轴地安装在机身的管道内的第一和第二反向旋转的变桨距转子组件 机身，以及至少一个固定在环形机身上的鸭翼，其前缘位于机身的导管之外并且在机身的前缘的轴向前方，其中，所述鸭翼的至少一部分包括控制表面 具有可变的迎角。 本发明提供一种能够垂直起飞并垂直着陆的飞行器，在固定的空间点上长时间悬停，并在密闭区域内操作。 飞行器还具有在悬停和高速前进飞行之间转换的能力。

公开(公告)号：US06607162B2

公开(公告)日：2003-08-19

申请号：US10049044

申请日：2002-02-07

Applicant: Clyde Warsop ,  Mike Woods ,  James Henderson ,  Gary Lock

Inventor： Clyde Warsop ,  Mike Woods ,  James Henderson ,  Gary Lock

IPC: B64C3906

CPC classification number: B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

Abstract: A ring-wing aircraft suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion element (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces center of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its center of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the center of mass towards the front of the aircraft thereby giving improved stability in all three axes.

Abstract translation: 特别适用于环形翼的微型无人驾驶飞行器（UAV）的环形飞机虽然并非完全适用。 根据本发明的飞机（10）包括限定具有纵向延伸的中心轴线（31）的管道（16）的环形翼（11），位于管道内的推进元件（15）和可移动的机翼（13,18） ）用于控制飞行中的飞行器，环形翼在一端倾斜地截取，当水平飞行时，该端部是后部（11b），以形成具有不相等长度的相对侧的环形翼。 这种布置产生的偏心距离环形翼的中心轴线，摆锤效应将确保飞机将滚动，使其质心总是在飞机空降时始终处于最低的高度。 因此，飞行器具有优选的取向，并且控制表面可以相对于该优选取向被定向。 此外，后方的倾斜截面使质心朝向飞机的前方，从而提高了所有三个轴线的稳定性。

公开(公告)号：US06604706B1

公开(公告)日：2003-08-12

申请号：US09763714

申请日：2001-02-22

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C2900

CPC classification number: B64C17/06 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: An unmanned air vehicle (UAV) having a ducted fan configuration with a propeller mounted inside of an opening that extends longitudinally through a fuselage. A gyroscopic stabilization device is attached to the propeller shaft such that rotation of the propeller shaft also results in rotation of the gyroscopic stabilization device. The gyroscopic stabilization device has sufficient mass and rotates at a sufficient angular velocity such that the aircraft is gyroscopically stabilized during flight. In one embodiment, the gyroscopic stabilization device comprises a ring mounted to the outer tips of the propeller and in another embodiment is comprised of a disc.

Abstract translation: 具有风扇构造的无人驾驶飞行器（UAV），其具有安装在通过机身纵向延伸的开口内部的螺旋桨。 陀螺稳定装置连接到传动轴上，使得传动轴的旋转也导致陀螺稳定装置的旋转。 陀螺稳定装置具有足够的质量并以足够的角速度旋转，使得飞行器在飞行期间被陀螺稳定。 在一个实施例中，陀螺稳定装置包括安装到螺旋桨的外部尖端的环，并且在另一个实施例中由圆盘组成。

公开(公告)号：US06588701B2

公开(公告)日：2003-07-08

申请号：US09961447

申请日：2001-09-25

Applicant: Arie Yavnai

Inventor： Arie Yavnai

IPC: B64C2900

CPC classification number: G05D1/0038 ,  B62D57/02 ,  B62D57/04 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/0044

Abstract: A remotely-controlled unmanned mobile device (UMD) adapted to function as a robot scout to enter and reconnoiter the site of a disaster and to communicate to a rescue mission information regarding conditions prevailing at the site, making it possible for the mission to decide on rescue measures appropriate to these conditions. The UMD is operable in either of two modes. In its air-mobility mode the UMD is able to vertically take off and land, to fly to the site and then hover thereover. In its ground-mobility mode, the UMD can walk on legs over difficult terrain and through wrecked structures and ruins. The UMD is provided with condition-sensitive sensors for gathering data regarding conditions prevailing at the site, and position-sensitive sensors for avoiding obstacles in the path of the walking UMD, thereby assuring safe mobility. Other sensors govern geo-referenced navigation and flight control functions.

公开(公告)号：US06224452B1

公开(公告)日：2001-05-01

申请号：US09395706

申请日：1999-09-14

Applicant: Stewart H. Morse

Inventor： Stewart H. Morse

IPC: A63B6510

CPC classification number: A63H27/00 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: A radio controlled aerial disc capable of flight in any direction when airborne. The invention provides upper and lower body portions which form a disc shaped housing when connected. Within the housing there is a servo motor and drive assembly coupled to a quadripartite blade to provide lift and motion to the aerial disc. A servo control mechanism and a rear prop assembly are also components of the invention for controlling the movement of the aerial disc. A receiver mounted on the aerial disc provides a method of receiving signals from a remote transmitter to control the movement of the aerial disc.

Abstract translation: 一种无人机控制的天线，能够在空中时沿任何方向飞行。 本发明提供了连接时形成盘形壳体的上部和下部主体部分。 在壳体内部有一个伺服电机和驱动组件，它连接到四分之一刀片，以提供升降和运动到天线盘。 伺服控制机构和后支撑组件也是用于控制天线的移动的本发明的组件。 安装在天线盘上的接收机提供从远程发射机接收信号以控制天线的移动的方法。

公开(公告)号：US06170778B2

公开(公告)日：2001-01-09

申请号：US09296716

申请日：1999-04-22

Applicant: James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

Inventor： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

IPC: B64C2730

CPC classification number: B64C27/20 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

Abstract: A method for reducing a nose-up pitching moment in an unmanned aerial vehicle during forward flight. The unmanned aerial vehicle includes counter-rotating rotor assemblies that are mounted within a duct. Each rotor assembly includes a plurality of rotor blades. The method involves adjusting the rotor blades to have substantially zero pitch. Then rotating the rotor assemblies to produce a virtual plane across the duct. The virtual plane is operative for substantially deflecting air passing over the fuselage away from the duct. In one embodiment of the invention, the method involves the further step of obstructing at least a portion of the bottom of the duct to inhibit air that is flowing across the bottom of the duct from passing into the duct.

Abstract translation: 一种用于在远程飞行期间减少无人驾驶飞行器中的起搏俯仰力矩的方法。 无人驾驶飞行器包括安装在管道内的反向旋转转子组件。 每个转子组件包括多个转子叶片。 该方法包括调整转子叶片以使其基本上为零。 然后旋转转子组件以在管道上产生虚拟平面。 虚拟平面可操作用于使穿过机身的空气基本上偏转远离管道。 在本发明的一个实施例中，该方法包括阻碍管道底部的至少一部分的进一步的步骤，以阻止流过管道底部的空气进入管道。

公开(公告)号：US5575438A

公开(公告)日：1996-11-19

申请号：US239645

申请日：1994-05-09

Applicant: Kevin P. McGonigle ,  John Ferraro ,  James P. Cycon

Inventor： Kevin P. McGonigle ,  John Ferraro ,  James P. Cycon

IPC: B64C27/10 ,  B64C27/20 ,  B64C39/02 ,  B64D47/00 ,  B64D47/08

CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) has a toroidal fuselage and a rotor assembly having a pair of counter-rotating rotors secured in fixed coaxial combination with the toroidal fuselage to provide a vertical takeoff and landing (VTOL) capability for the UAV. One embodiment of the VTOL UAV is especially configured for ground surveillance missions by the inclusion of an externally mounted, remotely controllable stowable sensor subsystem that provides an azimuthal scanning capability and a predetermined elevation/depression scanning capability to accomplish the ground surveillance mission and a foldable landing gear subsystem to facilitate landing of the VTOL UAV at unprepared ground surveillance sites.

Abstract translation: 无人飞行器（UAV）具有环形机身和转子组件，其具有与环形机身固定的同轴组合的一对反向旋转转子，以为无人机提供垂直起飞和着陆（VTOL）能力。 VTOL UAV的一个实施例通过包括外部安装的远程可控的可收缩传感器子系统特别地配置用于地面监视任务，其提供方位扫描能力和预定的仰角/凹陷扫描能力以完成地面监视任务和可折叠着陆 齿轮子系统，以便于在未准备的地面监视场所着陆无人机。

公开(公告)号：US5419513A

公开(公告)日：1995-05-30

申请号：US60337

申请日：1993-05-11

Applicant: Robert J. Flemming, Jr. ,  Kenneth M. Rosen ,  Thomas W. Sheehy

Inventor： Robert J. Flemming, Jr. ,  Kenneth M. Rosen ,  Thomas W. Sheehy

IPC: B64C27/20 ,  B64C27/26 ,  B64C39/02 ,  B64C27/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An unmanned aerial vehicle (UAV) having a toroidal fuselage and a rotor assembly including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures aerodynamically configured and mounted in combination with the toroidal fuselage to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures have a cambered airfoil profile to provide high lifting forces. The ancillary aerodynamic structures may have centers of lift located significantly aft of the quarter-chord line of the airfoil, and are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes such that the ancillary aerodynamic structures generate a nose-down pitching moment to counteract the nose-up pitching moment due to airflow over the toroidal fuselage in forward translational flight. In a first embodiment, the ancillary aerodynamic structures are fixedly mounted in combination with the toroidal fuselage at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures are rotatably mounted in combination with the toroidal fuselage to provide variable incidence ancillary aerodynamic structures for the UAV.

Abstract translation: 具有环形机身的无人飞行器（UAV）和包括相对于环形机身同轴安装的反向旋转转子的转子组件包括空气动力学构造并与环形机身组合安装的辅助空气动力学结构，以提供俯仰俯仰时刻 以抵抗在无人机的前向平移飞行期间由环形机身上的气流产生的起搏俯仰力矩。 辅助空气动力学结构具有弧形的翼型轮廓以提供高的提升力。 辅助空气动力学结构可以具有位于翼型的四分之一弦线明显地后方的电梯中心，并且与环形机身的侧面对称地安装，使得电梯的中心位于机身轴线的后方 在正向平移飞行模式下的环形机身，使得辅助空气动力学结构产生一个向下俯仰的俯仰时刻，以抵消由于向前平移飞行中的环形机身上的气流引起的上升俯仰时刻。 在第一实施例中，辅助空气动力结构以预定的入射角度与环形机身固定安装。 在第二实施例中，辅助空气动力学结构与环形机身组合地可旋转地安装，以为UAV提供可变入射辅助空气动力学结构。

公开(公告)号：US5364230A

公开(公告)日：1994-11-15

申请号：US903061

申请日：1992-06-22

Applicant: Timothy A. Krauss ,  David H. Hunter ,  Robert D. Beatty

Inventor： Timothy A. Krauss ,  David H. Hunter ,  Robert D. Beatty

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

CPC classification number: B64C27/605 ,  B64C27/20 ,  B64C27/33 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

Abstract: A rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a flexbeam, an integrated torque tube/spar member, and an aerodynamic fairing or rotor blade. The flexbeam is a laminated composite structure that reacts centrifugal loads and a majority of the bending loads of the rotor assembly. The flexbeam has a spanwise predetermined linear twist so that the pretwisted flexbeam is unstrained during specified forward flight conditions. The integrated torque tube/spar member is formed as a continuous, filament wound tubular composite structure having high torsional and bending stiffness that provides a continuous torsional load path and facilitates load coupling between the rotor blade and the pretwisted flexbeam. The spar segment of the functions as the primary structural member of the rotor blade subassembly and, is operative to react all bending, torsional, shear, and centrifugal dynamic loads of the rotor assembly. The torque tube segment reacts all torsional loads and some of the bending loads of the rotor assembly. The rotor blade is fabricated from a high modulus composite material and has a high aerodynamic taper such that the tapered rotor blade has a low outboard mass, a high inboard stiffness, and a high chordwise frequency. The high chordwise frequency allows the rotor assembly to be operated over a weaker modal response zone. The tapered rotor blade includes a triangularly shaped trailing edge segment that is responsive to the aerodynamic pressures encountered during operation of the shrouded counter-rotating rotors.

Abstract translation: 具有导管的同轴反转转子的转子组件的转子叶片子组件包括柔性梁，集成的扭矩管/翼梁构件和空气动力学整流罩或转子叶片。 柔性梁是一种叠层复合结构，可使离心载荷和转子组件的大部分弯曲载荷反应。 柔性梁具有翼展方向预定的线性扭曲，使得预弯曲的柔性梁在指定的向前飞行条件下是不受约束的。 集成的扭矩管/翼梁构件形成为具有高扭转和弯曲刚度的连续的长丝缠绕管状复合结构，其提供连续的扭转载荷路径并且有助于转子叶片和预扭曲挠曲梁之间的负载耦合。 作为转子叶片子组件的主要结构构件的功能的翼梁段，可操作以对转子组件的所有弯曲，扭转，剪切和离心动态载荷作出反应。 扭矩管段对转子组件的所有扭转载荷和一些弯曲载荷作出反应。 转子叶片由高模量复合材料制成并且具有高空气动力学锥度，使得锥形转子叶片具有低的外侧质量，高的内侧刚度和高的弦向频率。 高弦弦频率允许转子组件在较弱的模态响应区域上运行。 锥形转子叶片包括三角形的后缘段，其响应于在遮蔽的反向旋转转子的操作期间遇到的空气动力学压力。