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    TAILBOOM-STABILIZED VTOL AIRCRAFT
    124.
    发明公开
    TAILBOOM-STABILIZED VTOL AIRCRAFT 审中-公开
    具有稳定LEITWERK CARRIER垂直STARTER

    公开(公告)号：EP1689638A2

    公开(公告)日：2006-08-16

    申请号：EP04817324.9

    申请日：2004-10-19

    Applicant: Baldwin, Douglas G.

    Inventor： Baldwin, Douglas G.

    IPC: B64C27/28

    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 (100) includes a suspension structure (110) having a first end and a second end, a lift unit (150), and a payload unit (190). The lift unit includes a nacelle (128) and a tailboom (140), 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 minimizes 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.

    CIRCULAR VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    125.
    发明公开
    CIRCULAR VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
    立式圆STARTER

    公开(公告)号：EP1370460A1

    公开(公告)日：2003-12-17

    申请号：EP02703709.2

    申请日：2002-02-26

    Applicant: Walmsley, Eric Ronald

    Inventor： Walmsley, Eric Ronald

    IPC: B64C39/00 ,  B64C39/06 ,  B64D27/26

    CPC classification number: B64C27/20 ,  B64C39/001 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/162

    Abstract: A circular VTOL aircraft with a central vertically mounted turboprop engine (14), driving contra-rotating co-axial propellers (24), above a central jet engine, or engines (12), horizontally mounted on a turntable (11) and steerable through 360 degrees. The turboprop provides vertical thrust from propellers compressing air from an upper circular intake (5) downward through a circular funnel-shaped rotor-chamber (6), to a circular vent (10) at the base of the aircraft. The resulting column of compressed air gives lift for VTOL operations and a cushion of air in flight. The horizontally mounted turbine provides acceleration, retro-thrust and directional control for horizontal flight and vectored thrust for VTOL. An alternative engine configuration (Figure 9), replaces the turboprop and propellers with a vertical turbojet or rocket-engine system providing direct vertical thrust via four control vents (12/14), with an optional horizontal vectored thrust vent (15/37). he aircraft. Fuel-tanks are installed around the central engines. The flight-deck is at the top-centre of the craft above the engines, which are detachable for maintenance.

    MODULAR AIRCRAFT SYSTEM
    127.
    发明申请
    MODULAR AIRCRAFT SYSTEM 审中-公开
    模块化飞机系统

    公开(公告)号：WO2017180392A1

    公开(公告)日：2017-10-19

    申请号：PCT/US2017/026146

    申请日：2017-04-05

    Applicant: AL-SABAH, Nasser M. ,  33100.81 PATENT TRUST

    Inventor： AL-SABAH, Nasser M.

    IPC: B64C3/38 ,  B64C3/34 ,  B64C9/00 ,  B64C9/32 ,  B64C13/00 ,  B64C13/20 ,  B64C39/02 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14

    CPC classification number: B64C3/38 ,  B64C1/26 ,  B64C3/34 ,  B64C5/06 ,  B64C9/00 ,  B64C9/326 ,  B64C13/00 ,  B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/063 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/16 ,  B64C2201/165 ,  B64C2211/00 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D37/00 ,  B64D39/00 ,  B64D47/08 ,  Y02T50/32

    Abstract: The modular aircraft system includes a single fuselage (10) having a permanently installed empennage (12) and plural sets of wing modules (46a, 46b, 66a, 66b, 68a, 68b) and engine modules (56, 60, 64), with each wing and engine module optimized for different flight conditions and missions. The fuselage (10) and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings (46a, 46b) having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings (68a, 68b) having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module (66a, 66b) is also provided. Turboprop (56), single turbojet (60), and dual turbojet (64) engine modules are provided for installation depending upon mission requirements.

    Abstract translation: 模块化飞行器系统包括具有永久安装的尾翼（12）和多组翼模块（46a，46b，66a，66b，68a，68b）的单个机身（10）和发动机模块 56,60,64），每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身（10）和每个模块被配置为用于模块的快速移除和安装以最小化飞行器的停机时间。 当高度耐力和/或重量承载能力不受重视时，提供具有相对低纵横比的短翼（46a，46b）用于相对高速飞行。 提供具有高纵横比的长翼（68a，68b）用于速度不是绝对重要的较长距离和耐力飞行。 还提供了中跨翼模块（66a，66b）。 根据任务要求，提供涡轮螺旋桨发动机（56），单涡轮喷气发动机（60）和双涡轮喷气发动机（64）发动机模块用于安装。

    FLYING, GLIDING AND/OR AIRDROP CRAFT
    128.
    发明申请
    FLYING, GLIDING AND/OR AIRDROP CRAFT 审中-公开
    飞行，玻璃和/或空气压缩机

    公开(公告)号：WO2011002309A1

    公开(公告)日：2011-01-06

    申请号：PCT/NZ2010/000124

    申请日：2010-06-25

    Applicant: BLUE SKY VENTURES ,  HARRIS, Robert

    Inventor： HARRIS, Robert

    IPC: B64D5/00 ,  B64C5/12 ,  B64C37/00 ,  B64C1/32 ,  B64C31/00 ,  B64C39/10 ,  B64C3/56 ,  B64C31/02

    CPC classification number: B64D17/80 ,  B64C1/0009 ,  B64C5/02 ,  B64C39/024 ,  B64C39/026 ,  B64C2039/105 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/146 ,  B64D5/00

    Abstract: A carapaced blended wing-body gliding, flying or airdrop aircraft having rearwardly stowed wings able to assume and/or be caused to assume a flight mode condition, and stowed stabilator components able to assume and/or be caused to assume a flight mode condition. The craft can carry a prone operator or passenger, head to the fore or advance direction, and is able to deploy, post drop from a drop condition (i.e. with stowed wings and stabilator components) into an in flight condition to provide a better than 4:1 glide ratio.

    Abstract translation: 一架装有机翼的混合翼体滑翔，飞行或空投飞机后方收起能够承担和/或被引起飞行模式状态的机翼，并收起能够承受和/或被引起飞行模式状态的稳定器部件。 该工艺可以携带倾斜的操作员或乘客，前进或前进方向，并且能够部署，从下降状态（即，收起的翼和稳定器部件）落下到飞行状态以提供优于4 ：1次滑行比。

    REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT
    130.
    发明申请
    REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT 审中-公开
    减少可视性转轮和控制可视性转轮的飞行方法

    公开(公告)号：WO2005019029A3

    公开(公告)日：2006-02-16

    申请号：PCT/US2004016776

    申请日：2004-05-27

    Applicant: DAMMAR MICHAEL A

    Inventor： DAMMAR MICHAEL A

    IPC: B64C27/00 ,  B64C39/00 ,  B64C39/02

    CPC classification number: B64C39/00 ,  B64C27/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22

    Abstract: A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

    Abstract translation: 旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。 当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。 飞机可以通过固定无线电发射机进行控制，该发射机发出俯仰，滚动，偏航和高度的指令。 飞机中的接收机使用传输的信号来结合发送的命令建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。 俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

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