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    Ring generator
    201.
    发明申请
    Ring generator 失效
    环形发电机

    公开(公告)号：US20060138777A1

    公开(公告)日：2006-06-29

    申请号：US10560147

    申请日：2004-06-25

    Applicant: Peter Hofbauer ,  Patrick McCleer

    Inventor： Peter Hofbauer ,  Patrick McCleer

    IPC: H02K7/18 ,  F03G7/08 ,  F02B63/04

    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，其可以适用于用作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。

    Cargo aircraft
    202.
    发明申请
    Cargo aircraft 有权
    货机

    公开(公告)号：US20060108477A1

    公开(公告)日：2006-05-25

    申请号：US10996799

    申请日：2004-11-23

    Applicant: Elie Helou

    Inventor： Elie Helou

    IPC: B64D9/00

    CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

    Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

    Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

    Ducted air power plant
    206.
    发明申请
    Ducted air power plant 失效
    管道空气发电厂

    公开(公告)号：US20050223694A1

    公开(公告)日：2005-10-13

    申请号：US10519526

    申请日：2003-06-27

    Applicant: Ashley Bryant

    Inventor： Ashley Bryant

    IPC: A63H27/00 ,  B64C11/00 ,  B64C15/02 ,  B64C29/00 ,  B64C39/02 ,  F02K1/00 ,  F02K3/02 ,  F04D29/56 ,  F02K1/78

    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。

    Convertible vertical take-off and landing miniature aerial vehicle
    207.
    发明授权
    Convertible vertical take-off and landing miniature aerial vehicle 失效
    可转式垂直起降小型飞行器

    公开(公告)号：US06502787B1

    公开(公告)日：2003-01-07

    申请号：US10082814

    申请日：2002-02-22

    Applicant: Ronald Martin Barrett

    Inventor： Ronald Martin Barrett

    IPC: B64C2720

    CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

    Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment and a lower fuselage segment that extend in opposite directions from a rotor guard assembly. A rotor rotates within the rotor guard assembly between the fuselage segments. Plural turning vanes extend from the rotor guard assembly beneath the rotor. Moreover, plural grid fins extend radially from the lower fuselage segment below the turning vanes. The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins.

    Abstract translation: 垂直起飞和着陆的微型飞行器包括从转子保护组件沿相反方向延伸的上部机身段和下部机身段。 转子保护组件内的转子在机身段之间旋转。 多个转向叶片从转子下方的转子保护组件延伸。 而且，多个格栅翅片从转向叶片下方的下部机身段径向延伸。 飞行器能够垂直起飞和着陆。 在飞行中，飞行器可以使用网格散热片在水平飞行模式和垂直飞行模式之间悬停和转换。

    Flight control system for a hybrid aircraft in the yaw axis
    208.
    发明授权
    Flight control system for a hybrid aircraft in the yaw axis 有权
    飞行控制系统用于混合飞机在偏航轴上

    公开(公告)号：US06478262B1

    公开(公告)日：2002-11-12

    申请号：US09907068

    申请日：2001-07-17

    Applicant: W. Douglas Kinkead ,  Mark W. Scott

    Inventor： W. Douglas Kinkead ,  Mark W. Scott

    IPC: G05D100

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/0858

    Abstract: A flight control system includes a blending algorithm which evaluates the current flight regime and determines the effectiveness of the flight controls to effect the rotational moment of a hybrid vehicle about the yaw axis. Gain schedules for both differential collective and rudder control provide a quantitative measure of control effectiveness. Based on the respective gain schedules, the algorithm determines how much of the control commands should be sent to each control surface. The result is that for a given control command, the same amount of yaw moment will be generated regardless of flight regime. This simplifies the underlying flight control law since the commands it generates are correct regardless of flight regime.

    Abstract translation: 飞行控制系统包括混合算法，其评估当前飞行状态并且确定飞行控制器实现混合动力车辆绕偏转轴线的旋转力矩的有效性。 差异集体和方向舵控制的增益时间表提供了控制有效性的定量测量。 基于相应的增益计划，该算法确定应将多少控制命令发送到每个控制表面。 结果是对于给定的控制命令，将产生与飞行状态无关的相同量的横摆力矩。 这简化了潜在的飞行控制规则，因为它产生的命令是正确的，无论飞行情况如何。

    Unmanned aerial vehicle with counter-rotating ducted rotors and shrouded pusher-prop
    210.
    发明授权
    Unmanned aerial vehicle with counter-rotating ducted rotors and shrouded pusher-prop 有权
    无人机具有反向旋转的导向转子和带盖的推杆

    公开(公告)号：US06270038B1

    公开(公告)日：2001-08-07

    申请号：US09296624

    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: B64C2900

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

    Abstract: An unmanned aerial vehicle that includes a fuselage with a partial toroidal forward portion, and an aft portion. A duct is formed through the fuselage and extends from the top to the bottom of the fuselage. Two counter-rotating rotor assemblies are mounted within the duct for providing downward thrust through the duct. The rotor assemblies are supported by a plurality of support struts. At least one engine is mounted within the fuselage and engages with the rotor assemblies. A pusher prop assembly is mounted to the aft portion of the fuselage. The pusher prop assembly is designed to provide forward thrust along the longitudinal axis of the aircraft. The pusher prop assembly includes a drive shaft that is engaged with the engine. A plurality of propellers are attached to and rotated by the drive shaft. A shroud is mounted to the aft portion of the fuselage around the propellers and is operative for channeling the air passing through the propellers in a substantially aft direction. A pair of wings is removably attached to the sides of the fuselage. Each wing preferably includes a fixed portion and a pivotal flaperon portion hinged to the fixed portion. Directional vanes are preferably mounted to the shroud downstream from the propellers and control flow out of the shroud. Deflectors may be mounted to the bottom of the fuselage across a portion of the duct to control flow of air into the duct.

    Abstract translation: 一种包括具有部分环形前部的机身的无人飞行器和后部。 通过机身形成管道，并从机身的顶部延伸至底部。 两个反向旋转的转子组件安装在管道内，以提供通过管道的向下推力。 转子组件由多个支撑支柱支撑。 至少一个发动机安装在机身内并与转子组件接合。 推进支架组件安装在机身的后部。 推进支架组件被设计成沿着飞行器的纵向轴线提供向前的推力。 推进器组件包括与发动机接合的驱动轴。 多个螺旋桨附接到驱动轴并由驱动轴旋转。 护罩安装在机身周围的螺旋桨的后部，并且可操作用于沿基本向后的方向引导通过螺旋桨的空气。 一对机翼可拆卸地连接到机身侧面。 每个翼优选地包括固定部分和铰接到固定部分的枢转襟副翼部分。 定向叶片优选地安装到螺旋桨下游的护罩并且控制流出护罩。 导向器可以穿过管道的一部分安装到机身的底部，以控制进入管道的空气流。

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