公开(公告)号：US20100108809A1

公开(公告)日：2010-05-06

申请号：US12262428

申请日：2008-10-31

Applicant: Bruce Dan Bouldin ,  Ricardo Burdisso

Inventor： Bruce Dan Bouldin ,  Ricardo Burdisso

IPC: B64C1/40

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  B64D2033/0206

Abstract: A strut support system for a ducted fan unmanned aerial vehicle to suppress noise comprising: a ducted fan fuselage that defines an opening; an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts extending between the ducted fan fuselage and the engine each comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight of the ducted fan fuselage's leading edge.

Abstract translation: 一种用于管道风扇无人机的用于抑制噪声的支柱支撑系统，包括：限定开口的管道风扇机身; 发动机纵向延伸穿过机身中的开口; 驱动机构，其可旋转地安装在所述发动机上，其中风扇安装在由所述开口限定的导管内的所述驱动机构上; 以及在所述风扇风扇机身和所述发动机之间延伸的多个支柱，每个支柱包括通过曲线连接部连接在一起的第一腿部和第二腿部，其中所述第一腿部连接到所述风扇风扇机身，并且所述第二腿部连接到所述发动机 ，其中所述多个支柱位于所述风扇的上游，其中，所述多个支柱中的每一个的所述第一支腿与所述风扇风扇机身之间的连接处在所述风扇风扇机身的前缘的突出部之外。

公开(公告)号：US20100044496A1

公开(公告)日：2010-02-25

申请号：US12594719

申请日：2008-04-16

Applicant: Harry George Dennis Gosling

Inventor： Harry George Dennis Gosling

IPC: B64C15/12 ,  B64C9/00

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis. A direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device and/or a magnitude of thrust of the first propulsion device can be adjusted independently of the magnitude of thrust of the second propulsion device. In certain embodiments the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle.

Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 提供了包括一对或多对推进装置的推进系统，每对推进装置包括安装到翼体上并定位在包括翼体轴线的平面的第一侧上的第一推进装置，以及安装到 翼体并且定位在包括翼体轴线的平面的第二侧上。 可以独立于第二推进装置的推力方向来调节第一推进装置的推力方向，和/或可以独立于第二推进装置的推力的大小来调节第一推进装置的推力的大小。 在某些实施例中，当从第一视角观察时，翼体呈向前扫掠，并且当从与第一视角成直角的第二观察位置观看时向后扫掠。

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：US07581381B2

公开(公告)日：2009-09-01

申请号：US10519526

申请日：2003-06-27

Applicant: Ashley Christopher Bryant

Inventor： Ashley Christopher Bryant

IPC: F02K1/00 ,  B64C29/00

CPC classification number: F02K3/025 ,  A63H27/00 ,  B64C11/001 ,  B64C15/02 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/162 ,  F02K1/004 ,  Y02T50/672

Abstract: A ducted air power plant, comprising a motor driven fan (7) situated in a duct (4), the fan (7) having an air intake side and in operation providing a high pressure air stream in the duct, and the fan being located adjacent air splitter mechanism (18), the air splitter mechanism (18) being arranged to divert the air stream into two or more subsidiary streams for delivery to respective jet nozzles (9) of the plant. The plant may be used in a vehicle such as an aircraft in order to provide a vertical take-off and hover capability as well a level flight power source.

Abstract translation: 一种管道空气动力装置，包括位于管道（4）中的电机驱动风扇（7），所述风扇（7）具有进气侧并且在所述管道中提供高压气流，并且所述风扇位于 相邻的空分机机构（18），空分机机构（18）被布置成将空气流转移到两个或更多个辅助流中，以便输送到设备的相应的喷嘴（9）。 该工厂可用于诸如飞行器的车辆中，以提供垂直起飞和悬停能力以及水平飞行动力源。

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：US20060262646A1

公开(公告)日：2006-11-23

申请号：US11135931

申请日：2005-05-23

Applicant: Dan Horak ,  Richard Burne

Inventor： Dan Horak ,  Richard Burne

IPC: G01S3/80

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165 ,  F42B12/365 ,  G01S3/8083

Abstract: Embodiments for determining the bearings to targets from a remote location are disclosed. The apparatus consists of an array of acoustic sensors that is capable of autonomous flight. The array may be large in diameter, approximately one meter or greater. The apparatus is capable of navigating its flight to arrive at a predetermined location, measuring acoustic sound waves emitted by targets both during flight and after landing. The apparatus may then calculate the bearings to the targets and transmit this information to a remote location.

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：US20050011990A1

公开(公告)日：2005-01-20

申请号：US10620793

申请日：2003-07-16

Applicant: Yuriy Gmirya

Inventor： Yuriy Gmirya

IPC: B64C29/00 ,  B64C39/02 ,  B64D35/04 ,  B64D27/00

CPC classification number: F16H1/22 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/04

Abstract: A powerplant system for a vehicle such as a hybrid UAV includes a miniature gas turbine engine and a gearbox assembly. The engine is mounted to the gearbox assembly through a support structure which provides for pivotal movement of the engine relative thereto. The input gear is engaged with two gears such that the pivoted engine arrangement permits the input gear to float until gear loads between the input gear and the first and second gear are balanced. Regardless of the gear teeth errors or gearbox shaft misalignments the input gear will float and split the torque between the two gears.

Abstract translation: 用于诸如混合UAV的车辆的动力装置系统包括微型燃气涡轮发动机和齿轮箱组件。 发动机通过支撑结构安装到齿轮箱组件，该支撑结构提供发动机相对于其的枢转运动。 输入齿轮与两个齿轮接合，使得枢转的发动机装置允许输入齿轮浮动，直到输入齿轮与第一和第二齿轮之间的齿轮负载平衡。 齿轮齿轮误差或齿轮箱轴不对准，输入齿轮将浮动并分离两个齿轮之间的转矩。

公开(公告)号：US20040167682A1

公开(公告)日：2004-08-26

申请号：US10639267

申请日：2003-08-12

Applicant: Lockheed Martin Corporation

Inventor： Michael S. Beck ,  Wendell H. Chun ,  Jon T. Stinchcomb

IPC: G06F017/00

CPC classification number: B64C39/028 ,  B60K7/0007 ,  B60K17/046 ,  B60K17/356 ,  B60T1/062 ,  B62D61/10 ,  B62D61/12 ,  B64B1/50 ,  B64C27/20 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/162 ,  B64C2201/208

Abstract: A virtual sensor mast for a ground vehicle and a method for operating a ground vehicle using a virtual sensor mast are disclosed. The virtual sensor mast includes an unmanned airborne vehicle capable of lifting itself from the ground vehicle upon deployment therefrom; a sensor suite mounted to the unmanned airborne vehicle; and a tether between the unmanned airborne vehicle and the ground vehicle over which the sensor suite is capable of communicating sensed data upon deployment. The method includes elevating a tethered unmanned airborne vehicle from the ground vehicle to a predetermined height; sensing environmental conditions surrounding the ground vehicle; and terminating the deployment.

Abstract translation: 公开了一种用于地面车辆的虚拟传感器桅杆和使用虚拟传感器桅杆操作地面车辆的方法。 虚拟传感器桅杆包括能够在其从其展开时从地面车辆提升自身的无人机载机; 安装在无人机载体上的传感器套件; 以及在无人驾驶的机载车辆和地面车辆之间的系绳，传感器套件能够在部署时传送感测数据。 该方法包括：将有系带的无人机载体从地面车辆升高到预定的高度; 感测地面车辆周围的环境条件; 并终止部署。

公开(公告)号：US06672538B2

公开(公告)日：2004-01-06

申请号：US10153970

申请日：2002-05-23

Applicant: Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

Inventor： Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

IPC: B64C2730

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/06

Abstract: A transmission system for a hybrid aircraft is driven by a plurality of driveshafts and drives a translational propulsion system. Each driveshaft is mounted to a pinion gear which mesh with an upper and lower counter-rotating gear. The upper and lower counter-rotating gears drive a respective upper and lower rotor shaft which powers a counter-rotating rotor system. A first angle is defined between a first and a second driveshaft while a second angle is defined between the second and a third driveshaft. The angle between the driveshafts are a whole number multiple of the formula: &thgr;=(CP/R)*(180/&pgr;). By so angularly locating the driveshafts, proper meshing of the pinion gears and the upper and lower counter-rotating gears is assured and tolerances are less stringent as the support structure is effective designed around optimal location of the driveshafts for gear meshing rather than vice versa.

Abstract translation: 用于混合飞机的传动系统由多个驱动轴驱动并驱动平移推进系统。 每个驱动轴安装在与上下反转齿轮啮合的小齿轮上。 上下反转齿轮驱动相应的上下转子轴，其对反向旋转的转子系统供电。 在第一和第二驱动轴之间限定第一角度，而在第二和第三驱动轴之间限定第二角度。 驱动轴之间的角度是以下公式的整数倍：θ=（CP / R）*（180 / pi）。 通过如此角度地定位传动轴，确保小齿轮和上下相对转动齿轮的适当啮合，并且由于支撑结构有效地围绕用于齿轮啮合的驱动轴的最佳位置设计而不是反之亦然，公差不太严格。