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    AIRCRAFT
    71.
    发明申请
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：US20130082139A1

    公开(公告)日：2013-04-04

    申请号：US13432422

    申请日：2012-03-28

    Applicant: SARKIS AGAJANIAN

    Inventor： SARKIS AGAJANIAN

    IPC: B64C1/06

    CPC classification number: B64C1/068 ,  B64C3/185 ,  B64C39/02 ,  B64C39/04 ,  B64C2211/00

    Abstract: An aircraft is disclosed which is analogous to a tractor motor vehicle. In alternative fixed wing and helicopter embodiments, an airframe is adapted to transport different cargo modules. Some modules are adapted to carry freight and other modules are adapted to carry passengers. The aircraft arrives at a destination with an attached module, decouples from that module and attaches a different module to be transported to a different destination.

    Abstract translation: 公开了类似于拖拉机动车辆的飞机。 在替代的固定翼和直升机实施例中，机身适于运输不同的货物模块。 一些模块适用于运输货物和其他模块适应携带乘客。 飞机到达带有附件模块的目的地，与该模块分离，并将不同的模块连接到不同的目的地。

    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED THRUST CONTROL
    72.
    发明申请
    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED THRUST CONTROL 有权
    具有显着控制的模块化MINIATURE UNMANNED飞机

    公开(公告)号：US20110057074A1

    公开(公告)日：2011-03-10

    申请号：US12556225

    申请日：2009-09-09

    Applicant: Adam Woodworth ,  Brandon Suarez

    Inventor： Adam Woodworth ,  Brandon Suarez

    IPC: G05D1/00 ,  B64C13/00

    CPC classification number: B64C15/00 ,  B64C29/0033 ,  B64C39/02 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2211/00

    Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

    Abstract translation: 描述了一种无人驾驶飞机。 飞机包括机身，连接到机身后部的一对翅片，连接到机身底部的一对二面支架，第一推力矢量模块和第二推力矢量模块以及电子模块。 电子模块向两个推力矢量模块提供命令。 两个推力矢量模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接铰接的电动机作为推力矢量模块使飞机能够在宽范围的空速下执行紧半径的转弯。

    AIR TRANSPORT WITH SCALLOPED UNDERBODY
    74.
    发明申请
    AIR TRANSPORT WITH SCALLOPED UNDERBODY 有权
    航空运输与SCALLOPED的下属

    公开(公告)号：US20080149763A1

    公开(公告)日：2008-06-26

    申请号：US11614052

    申请日：2006-12-20

    Applicant: Sean R. Wakayama ,  Richard C. Odle

    Inventor： Sean R. Wakayama ,  Richard C. Odle

    IPC: B64C1/00

    CPC classification number: B64C1/22 ,  B64C1/0009 ,  B64C39/02 ,  B64C2039/105 ,  Y02T50/12

    Abstract: An exemplary embodiment provides an air transport that has a scalloped aerodynamic underside that includes at least one depression. The depression is configured to receive at least an upper portion of a cargo pod to preclude an air passage way between an upper surface of a pod and the scalloped underside of the transport. Certain embodiments provide conformal pods that nest into the depressions so that pod under surfaces blend smoothly with the scalloped underside of the transport to provide a smooth aerodynamic underside. The scalloped underside may be retrofitted to existing aircraft or supplied as original equipment on new transports, and may be of composite, plastic or other light weight materials.

    Abstract translation: 一个示例性的实施例提供了具有扇形空气动力下侧的空气输送器，其包括至少一个凹陷部。 凹陷构造成容纳货物舱的至少一个上部，以防止在舱的上表面和运输工具的扇形下侧之间的空气通道。 某些实施例提供嵌套在凹陷中的保形荚，使得表面下面的荚与输送机的扇形底侧平滑地混合，以提供平滑的空气动力学下侧。 扇形底面可以改装到现有的飞机上，或作为原始设备提供新的运输工具，并且可以是复合材料，塑料或其他轻质材料。

    Boarding device for aircraft and flying wings equipped with such a device
    75.
    发明授权
    Boarding device for aircraft and flying wings equipped with such a device 失效
    装有这种装置的飞机和飞翼的登机装置

    公开(公告)号：US06595466B2

    公开(公告)日：2003-07-22

    申请号：US09983469

    申请日：2001-10-24

    Applicant: Alain Depeige ,  Jean-Luc Jarrige

    Inventor： Alain Depeige ,  Jean-Luc Jarrige

    IPC: B64D900

    CPC classification number: B64D25/14 ,  B64C39/02 ,  B64C39/10 ,  B64C2039/105

    Abstract: Boarding device for aircraft and flying wings equipped with such a device. The boarding device consists of at least one tunnel (20) connected to the outside of the aerodynamic shell (12) of the aircraft. More precisely, the tunnel is attached to the trailing edge of the fairing (12) and it extends aft approximately parallel to the longitudinal axis of the aircraft. A door (22) closes off the opening between the passenger cabin (10) and the tunnel (20). The rear part (26) of the tunnel (20) is articulated and/or detachable. In order to evacuate the passengers in an emergency, the front, fixed part of the tunnel (24) can be fitted with an inflatable escape slide or an articulated floor.

    Abstract translation: 配备有这种装置的飞机和飞翼的登机装置。登机装置由至少一个连接到飞行器的空气动力学外壳（12）的外部的隧道（20）组成。 更准确地说，隧道连接到整流罩（12）的后缘，并且其大致平行于飞行器的纵向轴线延伸。 门（22）关闭客舱（10）和隧道（20）之间的开口。 隧道（20）的后部（26）铰接和/或可拆卸。 为了在紧急情况下撤离乘客，隧道（24）的前部，固定部分可以装有可充气逃生滑道或铰接地板。

    Rotary wing aircraft mast arrangement
    76.
    发明授权
    Rotary wing aircraft mast arrangement 失效
    旋翼飞机桅杆安排

    公开(公告)号：US4127244A

    公开(公告)日：1978-11-28

    申请号：US799174

    申请日：1977-05-23

    Applicant: David R. Pender

    Inventor： David R. Pender

    IPC: B64C21/06 ,  B64C39/02 ,  B64C27/22

    CPC classification number: B64C21/06 ,  B64C39/02 ,  Y02T50/166

    Abstract: A universally flexible rotor mast for a rotary wing aircraft wherein the universal flexing of the mast is accomplished by the use of multiple elastomer mounts of elastomer metal plate sandwich formation and with high strength cables embedded in the elastomer and anchored to opposing metal plates of the sandwich mounts. A static on-ground rotor mast lock is employed to secure the rotor mast in an upright position, the mast lock is used in conjunction with the elastomer mounts of the flexible mast.

    Abstract translation: 一种用于旋翼飞机的普遍灵活的转子桅杆，其中桅杆的通用弯曲通过使用弹性体金属板夹层结构的多个弹性体安装件和嵌入弹性体中的锚固到夹层的相对金属板上的高强度电缆来实现 安装。 采用静态地面转子桅杆锁将转子桅杆固定在直立位置，桅杆锁与柔性桅杆的弹性体支架结合使用。

    Semibuoyant composite aircraft
    77.
    发明授权
    Semibuoyant composite aircraft 失效
    Semibuoyant复合飞机

    公开(公告)号：US3976265A

    公开(公告)日：1976-08-24

    申请号：US535417

    申请日：1974-12-23

    Applicant: Donald B. Doolittle

    Inventor： Donald B. Doolittle

    IPC: B64B1/00 ,  B64C27/04 ,  B64C39/02 ,  B64C37/02

    CPC classification number: B64C39/02 ,  B64B1/00 ,  B64C37/02 ,  B64C2001/0072 ,  B64C27/04 ,  Y02T50/433

    Abstract: Various modifications are disclosed of the composite aircraft, which is the subject of U.S. Pat. No. 3,856,236 by this same inventor. The control console is supported from the center of the upper rotating balloon sphere instead of its south pole to reduce the periodic motion of the console about its point of attachment to the sphere. The console is supported from the center of an inner framework through a tapered indentation in the bottom of the sphere. A lift command control system determines the angle of attack of each wing about the periphery of the sphere to provide the force required to generate movement of the sphere in a preselected direction. If the wing experiences a gust, the force reaction compels the wing to seek a different angle of attack to keep the new force in balance with the command force exerted by the control on the wing to automatically provide gust control. A pneumatic lift command control system is illustrated. The altitude of the aircraft is controlled by maintaining the gas pressure at constant temperature by heat, such as obtained from the engine. Other variations for reducing drag include: boundary layer control of air pressure about the sphere to overcome the Magnus effect enclosing the sphere in an envelope, which does not rotate relative to the air, flattening the sphere and driving it by auxiliary engines instead of tilting it or by applying cone-shaped sections to one hemisphere and translating a substantially horizontal position.

    Abstract translation: 公开了复合飞机的各种修改，这是美国专利No. 同一发明人的3,856,236号。 控制台从上旋转球囊的中心而不是其南极支撑，以减少控制台围绕其与球体的连接点的周期性运动。 控制台通过球体底部的锥形凹槽从内框架的中心支撑。 提升命令控制系统确定围绕球体周边的每个翼的迎角，以提供在预选方向上产生球的运动所需的力。 如果机翼遇到阵风，强制反应迫使机翼寻求不同的攻角，以保持新的力与控制器对机翼施加的指挥力平衡，以自动提供阵风控制。 示出了气动升力指令控制系统。 通过如发动机获得的热量将气体压力维持在恒定温度来控制飞行器的高度。 减少阻力的其他变化包括：边界层控制围绕球体的空气压力，以克服将球体包围在不相对于空气旋转的信封中的马格纳斯效应，使球体平坦化并用辅助发动机驱动，而不是倾斜 或者通过将锥形部分应用于一个半球并平移基本上水平的位置。

    Air surface rapid transit vehicle
    78.
    发明授权
    Air surface rapid transit vehicle 失效
    空气表面快速运输车辆

    公开(公告)号：US3605935A

    公开(公告)日：1971-09-20

    申请号：US3605935D

    申请日：1970-01-06

    Applicant: RICHARD H GILBERT

    Inventor： GILBERT RICHARD H

    IPC: B60F5/02 ,  B60P3/42 ,  B60V3/04 ,  B61B13/04 ,  B61B15/00 ,  B62D31/02 ,  B64C37/00 ,  B60K35/00 ,  B64C37/02 ,  B64D9/00

    CPC classification number: B61B15/00 ,  B60F1/00 ,  B60F5/02 ,  B60P3/42 ,  B60V3/04 ,  B61B13/04 ,  B62D31/02 ,  B64C39/02 ,  B64D1/22 ,  B64F1/31

    Abstract: A PASSENGER- OR CARGO-CARRYING POD IS DETACHABLY CONNECTED TO A HELICOPTER FOR HIGH-SPEED TRANSPORT THEREBY BETWEEN METROPOLITAN AND SUBURBAN DEPOTS, AND IS THEN TRANSFERRED TO AND LOCKED ONTO A SELF-PROPELLED POWER UNIT OF ONE TYPE OR ANOTHER, FOR TRANSPORT ON THE GROUND. IN ONE CASE, THE POWER UNIT COMPRISES AN AUTOMOTIVETYPE CHASSIS HAVING WHEELS THAT RUN ON THE STREET OR HIGHWAY. THE CHASSIS HAS A SELF-CONTAINED POWER PLANT AND TRANSMISSION FOR DRIVING THE WHEELS, AS WELL AS STEERING MECHANISM, BRAKES, LIGHTS, ETC., WHICH ARE OPERATED BY CONTROLS WITHIN TEH POD. IN ANOTHER CASE, THE POWER UNIT COMPRISES A CHASSIS HAVING WHEELS THAT RUN ON ONE OR MORE TRACKS, SUCH AS A MONORAIL. WHEN MOUNTED ON EITHER OF THE POWER UNITS, THE POD CAN BE TRANSPORTED OVER A FIXED ROUTE WITHIN THE CITY TO PICK UP AND DISCHARGE PASSENGERS OR CARGO.

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