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    Wing design using a high-lift center section, augmented by all-moving wing tips and tails
    51.
    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。

    Outrigger air bag landing system
    52.
    发明授权
    Outrigger air bag landing system 失效
    悬臂式气囊着陆系统

    公开(公告)号：US4032088A

    公开(公告)日：1977-06-28

    申请号：US675004

    申请日：1976-04-08

    Applicant: John Jerome McAvoy

    Inventor： John Jerome McAvoy

    IPC: B60V3/08 ,  B64C39/02 ,  B64C25/56

    CPC classification number: B60V3/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187 ,  B64D2201/00

    Abstract: An air bag landing system for an aircraft. The landing system has an air bag assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with either two or three folding portions and an inflatable bag attached to the underside of the arm. The inflatable bag cushions the impact of the aircraft at landing. Actuators are provided to extend and retract the assembly.

    Abstract translation: 飞机的气囊着陆系统。 着陆系统具有气囊组件，其在巡航期间存储在飞行器的机身中并且延伸以着陆。 该组件包括具有两个或三个折叠部分的刚性臂和附接到臂的下侧的可充气袋。 充气袋缓冲飞机在着陆时的冲击。 提供致动器以延伸和缩回组件。

    IMAGE SENSOR BASED AUTONOMOUS LANDING
    53.
    发明申请
    IMAGE SENSOR BASED AUTONOMOUS LANDING 审中-公开

    公开(公告)号：US20190235523A1

    公开(公告)日：2019-08-01

    申请号：US16334418

    申请日：2017-12-18

    Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

    Inventor： Ohad Rozenberg ,  Haim Somech

    IPC: G05D1/04 ,  B64D47/08 ,  B64C39/02 ,  G06K9/00

    CPC classification number: G05D1/042 ,  B64C39/024 ,  B64C2201/141 ,  B64C2201/187 ,  B64D47/08 ,  G06K9/00624

    Abstract: A computer-implemented method of controlling an aircraft during autonomous landing. The method includes using a computer for performing the following: applying image processing on an image captured by a camera on board the aircraft while approaching a runway for identifying in the image a touchdown point (TDP) of the runway; calculating a deviation, in image parameters, of the TDP relative to the center of the image; converting the deviation in image parameters to angular and distance deviation values based on predefined ratios; calculating an offset of the aircraft's position relative to a landing corridor ending at the identified TDP based on the calculated angular and distance deviation; and transmitting the calculated offset to an aircraft control system configured to provide instructions for controlling the aircraft; wherein the offset is used for controlling the aircraft for guiding the aircraft towards the landing corridor to enable landing.

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