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    CARGO AIRCRAFT
    167.
    发明申请
    CARGO AIRCRAFT 审中-公开
    货运飞机

    公开(公告)号：US20100116932A1

    公开(公告)日：2010-05-13

    申请号：US12636381

    申请日：2009-12-11

    Applicant: ELIE HELOU, JR.

    Inventor： ELIE HELOU, JR.

    IPC: B64C39/02 ,  B64C1/06 ,  B64C1/20

    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: In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight.

    Abstract translation: 在一个实施例中，公开了一种用于运输至少一个货物集装箱的飞机。 飞行器包括前机身，尾翼，梁结构，以及可拆卸地和结构地接合具有梁结构的至少一个货物集装箱的安装件。 梁结构设置在前机身和尾翼之间，梁结构被配置成接收至少一个货物集装箱。 梁结构和结构上接合的货物集装箱提供足够的结构刚度以支持飞行中的飞机。

    Gyro-stabilized air vehicle
    168.
    发明授权
    Gyro-stabilized air vehicle 有权
    陀螺稳定型飞行器

    公开(公告)号：US07520466B2

    公开(公告)日：2009-04-21

    申请号：US11384167

    申请日：2006-03-17

    Applicant: Nicolae Bostan

    Inventor： Nicolae Bostan

    IPC: B64C17/00

    CPC classification number: B64C3/385 ,  B64C17/06 ,  B64C27/20 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/14

    Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

    Abstract translation: 一架垂直起降（VTOL）的空中客车。 机动车可以载人或无人驾驶。 在一个实施例中，空中交通工具包括安装在机身中的两个被覆盖的螺旋桨，机身和陀螺仪稳定盘。 陀螺稳定盘可以被配置成通过足够的质量和/或足够的角速度来提供足够的角动量，使得在飞行的各个阶段期间航空器的陀螺仪稳定。 在一个实施例中，机身固定地附接到被覆盖的螺旋桨。 在另一个实施例中，被覆盖的螺旋桨可枢转地安装在机身上。

    Tailboom-stabilized VTOL aircraft
    169.
    发明申请
    Tailboom-stabilized VTOL aircraft 审中-公开
    尾部稳定的垂直起降飞机

    公开(公告)号：US20070114325A1

    公开(公告)日：2007-05-24

    申请号：US11479833

    申请日：2006-06-30

    Applicant: G. Baldwin

    Inventor： G. Baldwin

    IPC: B64C27/00

    CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

    Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimzes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

    Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂并且最小化来自提升单元的降洗阻力。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

    Small-size high-speed transmission system for use in microturbine-powered aircraft
    170.
    发明申请
    Small-size high-speed transmission system for use in microturbine-powered aircraft 有权
    用于微型涡轮动力飞机的小型高速传动系统

    公开(公告)号：US20070051846A1

    公开(公告)日：2007-03-08

    申请号：US11398375

    申请日：2006-06-14

    Applicant: J. Box ,  Jules Kish

    Inventor： J. Box ,  Jules Kish

    IPC: B64D35/00

    CPC classification number: B64C27/14 ,  B64C39/028 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D35/02

    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 two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. The two stages of the transmission system may comprise any one (or parts of) of a number of configurations, including an in-line lay shaft configuration, an in-line star-star configuration, an offset star-spur configuration, an offset compound idler configuration, an inline traction-internal gear configuration, and an inline traction-planetary gear configuration. 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）。 两个还原阶段提供优选具有至少19的值，最优选大于24的减小率。传动系统的尺寸最小，最好具有小于12英寸的最大直径。 传动系统的两个阶段可以包括许多构造的任何一个（或部分）构造，包括在线卧轴构造，直列星星构造，偏移星形支路构造，偏移化合物 惰轮构造，在线牵引内齿轮配置和在线牵引行星齿轮配置。 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。

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