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    Anti-submarine warfare UAV and method of use thereof
    31.
    发明授权
    Anti-submarine warfare UAV and method of use thereof 失效
    反潜战无人机及其使用方法

    公开(公告)号：US06409122B1

    公开(公告)日：2002-06-25

    申请号：US09761076

    申请日：2001-01-17

    Applicant: Leland M. Nicolai

    Inventor： Leland M. Nicolai

    IPC: B64C3500

    CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

    Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

    Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。

    Wing design using a high-lift center section, augmented by all-moving wing tips and tails
    32.
    发明授权
    Wing design using a high-lift center section, augmented by all-moving wing tips and tails 失效
    翼设计使用高升力中心部分，增加了全方位的翼尖和尾巴

    公开(公告)号：US5918832A

    公开(公告)日：1999-07-06

    申请号：US818582

    申请日：1997-03-14

    Applicant: Siegfried Hermann Zerweckh

    Inventor： Siegfried Hermann Zerweckh

    IPC: B64C3/38 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C3/38 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  Y02T50/145

    Abstract: An air vehicle defining a plane of symmetry includes a pair of outboard panels which are rotatably mounted on the lifting body of the vehicle and respectively extend in opposite directions from the plane of symmetry. A control system collectively rotates the outboard panels to selectively contribute forces from the panels to the lift on the air vehicle. The control system also differentially rotates the outboard panels to control roll of the air vehicle. A pair of empennage panels are also rotatably mounted on the lifting body to establish a dihedral angle centered on the plane of symmetry. The control system collectively rotates these empennage panels to control pitch, and differentially rotates the empennage panels to control yaw, of the air vehicle. In a high speed flight regime the lifting body alone is sufficient and the outboard panels are collectively rotated to reduce drag and contribute substantially zero lift. In a slow speed flight regime, the outboard panels are collectively rotated to contribute to the lift on the air vehicle.

    Abstract translation: 限定对称平面的空中车辆包括一对舷外面板，其可旋转地安装在车辆的提升体上并且分别沿着对称平面的相反方向延伸。 控制系统共同地旋转外侧面板，以选择性地贡献从面板到机动车辆上的电梯的力。 控制系统还将外侧面板差分地旋转以控制空中车辆的滚动。 一对尾翼也可旋转地安装在提升体上，以建立以对称平面为中心的二面角。 控制系统将这些尾翼面板共同旋转以控制俯仰，并差速旋转尾翼面板以控制飞行器的偏航。 在高速飞行状态下，单独的提升体就足够了，并且外侧面板共同旋转以减少阻力并大体上提供零升力。 在慢速飞行状态下，外侧面板被集体旋转以对飞行器上的电梯做出贡献。

    Rotor Assembly having Collective Pitch Control
    33.
    发明申请
    Rotor Assembly having Collective Pitch Control 审中-公开

    公开(公告)号：US20180339769A1

    公开(公告)日：2018-11-29

    申请号：US15606257

    申请日：2017-05-26

    Applicant: Bell Helicopter Textron Inc.

    Inventor： John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C27/54 ,  B64C29/00

    CPC classification number: B64C27/605 ,  B64C27/54 ,  B64C29/0016 ,  B64C29/0033 ,  B64C2201/086 ,  B64C2201/108

    Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

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