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    Inflatable airfoils, and elevated and propulsion driven vehicles
    161.
    发明授权
    Inflatable airfoils, and elevated and propulsion driven vehicles 失效
    充气翼型，高架和推进驱动的车辆

    公开(公告)号：US06398160B1

    公开(公告)日：2002-06-04

    申请号：US09617765

    申请日：2000-07-17

    Applicant: Chih-Yu Hsia

    Inventor： Chih-Yu Hsia

    IPC: B64C330

    CPC classification number: B64C3/30 ,  B64B2201/00 ,  B64C31/028 ,  B64C31/04 ,  Y10S244/903

    Abstract: An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes.

    Abstract translation: 一种航空装置，该组合包括具有至少一个面板的主要翼型件，其具有上板，下板和与翼型件相关的并且纵向延伸的多个气体，所述管包括相对较大的横截面管， 并且相对较小的横截面定位器被定位成稳定相对较大的横截面管。

    Articulated drive
    162.
    发明申请
    Articulated drive 失效

    公开(公告)号：US20020003189A1

    公开(公告)日：2002-01-10

    申请号：US09903782

    申请日：2001-07-11

    Inventor： Hermann Kuenkler

    IPC: B64B001/34

    CPC classification number: B64C29/0033 ,  B63H5/125 ,  B64B1/32 ,  B64B2201/00 ,  B64C11/02 ,  B64C27/28 ,  B64C27/52 ,  B64D35/00

    Abstract: An aircraft has a fuselage designed essentially as an aerostatic lift body and combined lift and propulsion devices which are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case are tiltable between a lift position, in which the respective propeller rotation plane is essentially horizontal and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially vertical, and a propulsion position, in which the respective propeller rotation plane is essentially vertical and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially horizontal. The propeller rotation plane has all-round inclinability relative to the output shaft of the associated drive, said output shaft acting on the propeller shaft.

    Semi-buoyant vehicle with aerodynamic lift capability
    163.
    发明授权
    Semi-buoyant vehicle with aerodynamic lift capability 有权
    具有气动提升能力的半浮力车辆

    公开(公告)号：US06196498B1

    公开(公告)日：2001-03-06

    申请号：US09467971

    申请日：1999-12-21

    Applicant: David B. Eichstedt ,  John P. Morehead ,  John B. Kalisz

    Inventor： David B. Eichstedt ,  John P. Morehead ,  John B. Kalisz

    IPC: B64B120

    CPC classification number: B64B1/20 ,  B64B1/28 ,  B64B2201/00

    Abstract: The invention is a non-ridged, semi-buoyant vehicle. In detail, the invention includes a pressure stabilized gasbag having front and rear ends and an aerodynamic shape capable of producing lift, and longitudinal, vertical and horizontal axis, the tail end of the gasbag extending outward along the horizontal axis from each side of the longitudinal axis toward said front end at an acute angle to the horizontal axis. A horizontal tail surface is mounted outboard of the rear end of the gasbag, having a trailing edge extending outward along the horizontal axis from each side of the longitudinal axis toward the front end at the acute angle to the horizontal axis. A horizontal ridged beam is mounted outboard of the rear end of the gasbag that extends outward along the horizontal axis from each side of the longitudinal axis toward the front end at the acute angle to the horizontal axis with the horizontal tail surface mounted to the beam. The preferred acute angle is approximately 20 degrees. The gasbag further includes a plurality of vertical catenary curtains attached between the top and bottom surfaces of the gasbag. A vertical extending flexible bean is attached to each of catenary curtains. These straps have top and bottom ends extending out of the top and bottom surfaces, respectively, of said gasbag. Top and bottom attachment fittings are mounted by a first end to the top and bottom ends, respectively, of the ridged beam and by their second ends to the top and bottom ends, respectively, of the flexible straps.

    Abstract translation: 本发明是一种非脊状，半浮力的车辆。 详细地，本发明包括具有前端和后端的压力稳定的气囊，以及能够产生升力和纵向，垂直和水平轴线的空气动力学形状，气囊的尾端沿纵向方向从水平轴向外延伸 轴线以与水平轴成锐角的方式朝向所述前端。 水平尾部表面安装在气囊的后端的外侧，具有沿水平轴线从纵向轴线的每一侧向前端向水平轴线锐角向后延伸的后缘。 水平脊状梁安装在气囊的后端外侧，该气囊的后端沿水平轴线从纵向轴线的每一侧向前端以水平轴线的锐角向外延伸，水平尾部表面安装在梁上。 优选的锐角约为20度。 气囊还包括附接在气囊的顶表面和底表面之间的多个垂直悬链帘。 垂直延伸的柔性豆连接到每个悬链帘。 这些带子具有分别从所述气囊的顶表面和底表面延伸出的顶端和底端。 顶部和底部附件配件分别通过第一端安装到脊状梁的顶端和底端，并将其第二端分别安装到柔性带的顶端和底端。

    Balopod (hybrid flying machine)
    164.
    发明授权
    Balopod (hybrid flying machine) 失效
    Balopod（混合飞行机）

    公开(公告)号：US4838501A

    公开(公告)日：1989-06-13

    申请号：US847523

    申请日：1986-04-03

    Applicant: Edward G. Judson

    Inventor： Edward G. Judson

    IPC: B64C37/02

    CPC classification number: B64C37/02 ,  B64B2201/00

    Abstract: A flying machine (L.T.A.-H.T.A. Hybrid) connected through the fuselage . . . using a two-point-lift system wherein the lifts are static and dynamic . . . separately and simultaneously. The static lift is supplied by an aerostat (#36) while the dynamic lift is supplied by an atmospheric deflector (#48) . . . This system, by the clever use of 180 degrees pivotable pusher (blower) engine (#1), being and becoming capable of:1. S. T. O. L. and/or V.T.O.L.2. Rearward FlightA two-point-lift system, as stated in the preferred embodiment (technical description), employing L. T. A. and H. T. A. method (separately and simultaneously) to be allowed development on a non-exclusive basis (excluding Balopod). The process levels the device by coordinating static lift, thrust, and dynamic lift.

    Abstract translation: 通过机身连接的飞行器（L.T.A.-H.T.A.混合动力）。 。 。 使用两点升降系统，其中升降机是静态和动态的。 。 。 分别和同时。 静电提升由空气调节器（＃36）提供，而动力升降由大气偏转器（＃48）提供。 。 。 该系统通过巧妙地使用180度可枢转推动器（鼓风机）发动机（＃1），并且变得能够：1. S.T.L.L.和/或V.T.O.L. 2.向后飞行如优选实施例（技术说明）所述，采用L.T.A.和H.T.A.方法（分别和同时）的两点升降机系统被允许在非排他性基础上开发（不包括Balopod）。 该过程通过协调静电提升，推力和动态升程来平衡设备。

    Aircraft having buoyant gas balloon
    165.
    发明授权
    Aircraft having buoyant gas balloon 失效
    飞机具有浮力气球

    公开(公告)号：US4366936A

    公开(公告)日：1983-01-04

    申请号：US318248

    申请日：1981-11-04

    Applicant: Frederick D. Ferguson

    Inventor： Frederick D. Ferguson

    IPC: B64B1/22 ,  B64B1/00 ,  B64B1/24 ,  B64C39/00 ,  B64B1/02 ,  B64B1/58

    CPC classification number: B64B1/00 ,  B64B2201/00

    Abstract: An airship is provided utilizing a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric so that its dimensions are substantially unaffected by changes in atmospheric pressure or temperature. The spherical balloon is rotatably mounted on a normally horizontal axle having end portions projecting from opposite sides of the balloon, and includes a rigid load supporting yoke including two arms extending upwardly from a central load supporting structure and each with an upper end suspended from the axle. The yoke arms carry engines which propel the airship in a forward direction transverse to the axle, and means are provided for rotating the balloon about the axle so that the balloon front surface moves upward relative to the centre of the balloon and provides lift due to the Magnus effect.

    Abstract translation: 使用充满浮力气体（例如氦气）的气球以大大大于大气压的压力提供飞艇，使其尺寸基本上不受大气压力或温度变化的影响。 球形球囊可旋转地安装在具有从球囊的相对侧突出的端部的正常水平轴上，并且包括刚性负载支撑轭，其包括从中心负载支撑结构向上延伸的两个臂，并且每个具有从轴悬挂的上端 。 轭臂携带发动机，其沿着横向于轴的向前方向推动飞艇，并且提供用于使球囊围绕轴旋转的装置，使得球囊前表面相对于球囊的中心向上移动，并且由于 马格努斯效应。

    Semi-buoyant aircraft
    166.
    发明授权
    Semi-buoyant aircraft 失效
    半自动飞机

    公开(公告)号：US4052025A

    公开(公告)日：1977-10-04

    申请号：US564853

    申请日：1975-04-03

    Applicant: Frank M. Clark ,  George M. Christner

    Inventor： Frank M. Clark ,  George M. Christner

    IPC: B64B1/20 ,  B64C1/34 ,  B64B1/08

    CPC classification number: B64C1/34 ,  B64B1/20 ,  B64B2201/00

    Abstract: The disclosed semi-buoyant lift-augmented aircraft, preferably of immense size, includes a fuselage of airfoil shape formed by a rigid geodesic type web framework enclosing buoyant cells pressurized to reinforce the framework. Wings are provided which impart aerodynamic lift to the aircraft, with the airfoil fuselage. The buoyancy is provided to counteract a major proportion of the great weight of the structure and to thus improve the aircraft's payload capability and range. These features maintain it airborne at reasonable speeds over a substantial altitude range.

    HYBRID AIRSHIP AND RELATED ASSEMBLY AND/OR MAINTENANCE METHOD
    170.
    发明申请
    HYBRID AIRSHIP AND RELATED ASSEMBLY AND/OR MAINTENANCE METHOD 审中-公开

    公开(公告)号：WO2019092472A1

    公开(公告)日：2019-05-16

    申请号：PCT/IB2017/001549

    申请日：2017-11-13

    Applicant: TOTAL SA ,  FLYING WHALES

    Inventor： KUHLMANN, Hervé

    IPC: B64B1/22

    CPC classification number: B64B1/22 ,  B64B2201/00

    Abstract: The present invention concerns hybrid airship (10) comprising at least one buoyancy enclosure (32) containing a gas lighter than air, a gondola (34) attached below the buoyancy enclosure (32), the gondola (34) extending along a longitudinal axis, at least one propeller (36) configured to propel the hybrid airship (10), the at least one propeller (36) being attached to the buoyancy enclosure (32), at least one generator (38), configured to provide power to the propeller (36), the generator (38) being connected to the gondola (34). The hybrid airship (10) comprises an arm (40) protruding from the gondola (34) and connecting the generator (38) to the gondola (34).

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