公开(公告)号：US08157203B2

公开(公告)日：2012-04-17

申请号：US12262747

申请日：2008-10-31

Applicant: Lloyd E. Kinsey ,  Patrick Kranking

Inventor： Lloyd E. Kinsey ,  Patrick Kranking

IPC: B64C27/22

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。

公开(公告)号：US20110001020A1

公开(公告)日：2011-01-06

申请号：US12829423

申请日：2010-07-02

Applicant: Pavol Forgac

Inventor： Pavol Forgac

IPC: B64C27/26

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/127

Abstract: The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight.

Abstract translation: 所公开的发明包括对众所周知的四角倾斜转子（QTR）飞机的若干改进。 第一个是在机翼飞行期间，一对倾斜转子可以比另一对大得多，被羽毛和停止。 这可以提高车辆空气动力学效率，并且可以用于提高车辆速度。 第二是机翼不像传统的QTR飞机那样以固定的入射角度附着在机身上，而且也可以独立于倾斜转子而相对于机身倾斜。 此外，每个转子和每个机翼可以相对于机身倾斜到任何倾斜角度，无限制，这给予车辆以相对于车辆飞行方向的任何姿态将机身定位的前所未有的能力。

公开(公告)号：US20110001001A1

公开(公告)日：2011-01-06

申请号：US12865429

申请日：2009-02-02

Applicant: Ashley Christopher Bryant

Inventor： Ashley Christopher Bryant

IPC: B64C29/00 ,  B64C39/10

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms (56) are employed, the arms (56) of fore and aft propulsion units (52,54; 53,55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51 ; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Only one propulsion unit (21) may be mounted at each extremity and additional fan units (48,83) may be used.

Abstract translation: 垂直起降（VTOL）飞翼飞机具有一对推进矢量推进单元（2,3; 4,5），其安装在飞行器俯仰轴线（PA）的前后，位于横梁（6,7） ）在机翼结构（1）的相对两端，前部单元（2; 4）和下方的后部单元（3; 5），机翼结构（1）。 推进单元（2-5）直接地或经由臂（56）枢转到斜面（6,7），用于单独的角位移，用于偏航，俯仰和滚动中的推进向导操纵的飞行器，并且用于悬停和 向前和向后飞行 当使用臂（56）时，前后推进单元（52,54; 53,55）的臂（56）通过链条驱动器（57-60）或连杆（61）相互配合。 机翼结构（1; 51; 78）可以具有翅片（47; 84），板条（81）和翼片（82）和其它空气动力学控制表面，并且扩大的横条（84）可以包括舵表面（80）。 每个末端只安装一个推进单元（21），并且可以使用附加的风扇单元（48,83）。

公开(公告)号：US20100288889A1

公开(公告)日：2010-11-18

申请号：US12735312

申请日：2009-01-02

Applicant: Marian Pruzina

Inventor： Marian Pruzina

IPC: B64C29/00

CPC classification number: B64C39/064 ,  B64C2201/027 ,  B64C2201/088

Abstract: The Spring flying device (1) preferably of circular, oval or polygon shape, capable of vertical take-off and landing, comprises the source (5) of flowing medium (6), which flows through chamber (2) consisting of curved bottom face generating buoyancy during flow (3) and curved top medium attracting face (4). The faces (3) and (4) making up chamber (2) have adequate spacing from each other which allows their interaction still; control is provided by deflection (9) and swivelling (10) flaps, pivot-mounted in chamber (2) and acting upon the flowing medium (6). The device (1) may carry missile ramp (18) with protective guide shield (14) with horizontal (15) and radial (16) deflection flaps which streamline the missile exhaust gases (17) to outer top buoyancy face (12), while the missile exhaust gases (17) may be streamlined to apertures (19) of the chamber simultaneously.

Abstract translation: 优选具有垂直起飞和着陆的圆形，椭圆形或多边形形状的弹簧飞行装置（1）包括流动介质（6）的源（5），其流过由弯曲底面 在流动（3）和弯曲顶部介质吸引面（4）期间产生浮力。 组合室（2）的面（3）和（4）彼此之间具有足够的间距，这使得它们的相互作用是静止的; 通过偏转（9）和旋转（10）襟翼提供控制，枢转安装在腔室（2）中并作用在流动介质（6）上。 装置（1）可以携带带有水平（15）和径向（16）偏转翼片的保护引导屏蔽（14）的导弹斜坡（18），其将导弹废气（17）简化为外顶部浮力面（12），同时 导弹废气（17）可以同时流线化到腔室（19）。

公开(公告)号：US07665688B2

公开(公告)日：2010-02-23

申请号：US11691971

申请日：2007-03-27

Applicant: David A Cylinder ,  James C Kellogg

Inventor： David A Cylinder ,  James C Kellogg

IPC: B64C27/24 ,  B64C27/28

CPC classification number: B64C27/24 ,  B64C27/28 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

Abstract: A micro aerial vehicle can be converted during flight between a fixed wing flight mode and a rotary wing flight mode. The canard design micro aerial vehicle includes a fuselage, two tiltable propellers and airfoils arranged at a forward portion of fuselage, a pair of coaxial drive shafts positioned aft of the tiltable propeller and airfoil arranged for contra-rotation, a stop rotor mechanism, and a pair of wing panels, each of the wing panels attached to one of the coaxial drive shafts. The wing panels act as contra-rotating rotor blades in the rotary wing flight mode, and act as fixed wing panels in the fixed wing mode.

Abstract translation: 微型飞行器可以在固定翼飞行模式和旋翼飞行模式之间的飞行过程中转换。 鸭子设计的微型飞行器包括机身，两个可倾斜的螺旋桨和机身，其布置在机身的前部，一对同轴驱动轴，位于可倾斜推进器和翼型的后方，布置成用于反向转动，止动转子机构和 一对翼板，每个翼片连接到同轴驱动轴之一。 翼板作为旋转翼飞行模式中的反转叶片，以固定翼模式作为固定翼板。

公开(公告)号：US07658346B2

公开(公告)日：2010-02-09

申请号：US11338558

申请日：2006-01-24

Applicant: Emray R. Goossen

Inventor： Emray R. Goossen

IPC: B64C27/08

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract translation: 双管风扇装置，其中管道部件，发动机和航空电子设备/有效载荷容器能够快速拆卸以适合普通的背包系统。 风扇，定子和控制叶片设计中的每个风道都相同。 管道风扇和电子模块之间的组装连接也相同。 发动机或APU通过花键轴驱动双管道风扇到差速器或通过电动机驱动。 能量通过安装在定子毂上的单个齿轮传递到管道风扇。 单个管道风扇的相对速度通过在差速风扇和管道风扇之间的每个花键轴上的单独的摩擦或发电机负载控制制动机构来控制。 在电动机壳体中，相对速度是通过电子速度控制。 风扇反向旋转以进行扭矩平衡。 电子模块位置对于纵向重心是垂直可变的，用于有效载荷的变化。

公开(公告)号：US20080272226A1

公开(公告)日：2008-11-06

申请号：US11947585

申请日：2007-11-29

Applicant: John C. Colclough

Inventor： John C. Colclough

IPC: B64C37/00 ,  B64C3/56

CPC classification number: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

Abstract translation: 公开了一种管道风扇空气动力车辆和操作方法，用于在前进飞行操作中获得空气动力学提升和效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼包括在管道式风扇飞行器上，并且在向前飞行期间部署以提供空气动力学提升。 当车辆悬停时，翼或翼缩回，以减少翼对风中的稳定性的影响。 每个翼可以在缩回时符合车辆的曲率或轮廓，并且可以构造在一个或多个翼部中。 机翼或机翼可以自动部署和撤回，或者在操作员的指令下进行。 每个翼和相关部件可以集成到车辆中或者可以是可拆卸的。

公开(公告)号：US20070023581A1

公开(公告)日：2007-02-01

申请号：US11182877

申请日：2005-07-16

Applicant: William La

Inventor： William La

IPC: B64G1/28

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

Abstract: An omni-directional aircraft with flight capabilities surpassing those of a regular VTOL or helicopter, being able to take full advantage of the simultaneous six degrees of freedom of motion possible in the atmosphere, undergoing any desired combination of translational and rotational movement, and keeping station in the air in any arbitrary attitude. In the preferred embodiment, the flying object comprises a cubic body on the six faces of which are mounted six propulsion units, such that the propellers on each pair of opposite faces are coplanar with each other and with the main axis passing through the centers of these opposite faces, and their thrusts act along the direction of another main axis, each of the three pairs of propellers acting along a different one of the cube's three main axes. The thrust from each motion-inducing assembly being continuously variable and reversible, the resultant translational and rotational thrust vectors can be positioned arbitrarily within their respective solid envelopes. A control element with equal freedom of motion allows intuitive piloting of the vehicle. In an alternate embodiment, the propulsion units are disposed along the sides of a tetrahedron.

Abstract translation: 全方位飞机的飞行能力超过常规垂直起降或直升机的飞行能力，能够充分利用大气中可能同时进行的六种运动自由度，经历任何所需的平移和旋转运动的组合，并保持站 在空中任意任意的态度。 在优选实施例中，飞行物体包括立方体，其六个面上安装有六个推进单元，使得每一对相对面上的螺旋桨彼此共面并且主轴线穿过其中心 相对的面，它们的推力沿另一个主轴的方向作用，三对螺旋桨中的每一对沿着立方体的三个主轴的不同的一个作用。 来自每个运动感应组件的推力是连续可变和可逆的，所得到的平移和旋转推力矢量可以任意地定位在它们各自的实心包络内。 具有相同运动自由度的控制元件允许车辆的直观驾驶。 在替代实施例中，推进单元沿着四面体的侧面设置。

公开(公告)号：US20060192047A1

公开(公告)日：2006-08-31

申请号：US11338558

申请日：2006-01-24

Applicant: Emray Goossen

Inventor： Emray Goossen

IPC: B64C27/08

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems.. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract translation: 双管风扇装置，其中管道部件，发动机和航空电子设备/有效载荷容器能够快速拆卸以适合普通的背包系统。每个管道在风扇，定子和控制叶片设计中是相同的。 管道风扇和电子模块之间的组装连接也相同。 发动机或APU通过花键轴驱动双管道风扇到差速器或通过电动机驱动。 能量通过安装在定子毂上的单个齿轮传递到管道风扇。 单个管道风扇的相对速度通过在差速风扇和管道风扇之间的每个花键轴上的单独的摩擦或发电机负载控制制动机构来控制。 在电动机壳体中，相对速度是通过电子速度控制。 风扇反向旋转以进行扭矩平衡。 电子模块位置对于纵向重心是垂直可变的，用于有效载荷的变化。

公开(公告)号：US20030025032A1

公开(公告)日：2003-02-06

申请号：US10218885

申请日：2002-08-14

Applicant: Bertin Technologies

Inventor： Marc Lepretre ,  Georges Chastang

IPC: B64C027/22

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 integral with a cylindrical fairing wherein rotates a propeller powered by an engine housed in a fuselage secured to the fairing with radial arms and straightening vanes.

Abstract translation: 本发明涉及一种遥控飞行器，特别是用于监视和检查，其能够悬停并包括与圆柱形整流罩成一体的球形耐开度的护罩，其中旋转由容纳在固定到整流罩上的机身中的发动机驱动的螺旋桨 具有径向臂和矫直叶片。