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    Ducted fan air vehicle with deployable wings
    141.
    发明公开
    Ducted fan air vehicle with deployable wings 审中-公开
    Mantelgebläse-Luftfahrzeug mit ausfahrbarenFlügeln

    公开(公告)号：EP1988014A2

    公开(公告)日：2008-11-05

    申请号：EP08155550.0

    申请日：2008-05-01

    Applicant: Honeywell International Inc.

    Inventor： Colclough, John C.

    IPC: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/02

    CPC classification number: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

    Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward fliglit operation without significantly impacting hover stability. One or more retractable wings (301) are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

    Abstract translation: 公开了一种管道式风扇空气动力车辆和操作方法，用于获得空气动力提升和前进光束操作的效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼（301）被包括在管道式风扇空气车辆上，并且在向前飞行期间展开以提供空气动力提升。 当车辆悬停时，翼或翼缩回，以减少机翼对风中稳定性的影响。 每个翼可以在缩回时符合车辆的曲率或轮廓，并且可以构造在一个或多个翼部中。 机翼或机翼可以自动或根据操作员的指令进行展开和撤回。 每个翼和相关部件可以集成到车辆中或者可以是可拆卸的。

    Micro air-vehicle transport container and launch system
    142.
    发明公开
    Micro air-vehicle transport container and launch system 审中-公开
    Luftfahrzeug的运输和运输

    公开(公告)号：EP1884463A1

    公开(公告)日：2008-02-06

    申请号：EP07106798.7

    申请日：2007-04-24

    Applicant: HONEYWELL INC.

    Inventor： Goossen, Emray R ,  Mantych, Glen A. ,  Campbell, William T.

    IPC: B64C39/02 ,  B64F1/04

    CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/201

    Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container (110) and a container lid (101) with the MAV (200) clamped to the lid. Also disposed on the container lid is a starting assembly (111). The lid (101) which doubles as a launching pad with the attached MAV (200) is removed from the container (110), placed on the ground, the MAV (200) is started with the starling mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

    Abstract translation: 微型飞行器（MAV）启动系统，提供组合功能：敏感车辆部件的包装保护，机械启动组件和发射台。 优选实施例包括容器（110）和容纳盖（101），其中MAV（200）夹在盖子上。 还设置在容器盖上的是起动组件（111）。 将具有连接的MAV（200）的作为发射台的盖（101）从容器（110）中取出，放置在地面上，MAV（200）以起落机构启动并启动。 这种安排可最大限度地减少操作者的身体风险，最大限度地减少总体MAV系统的重量，消耗操作员运输系统的最小空间，并消除对电池更换或充电的供电线路的依赖。

    Autonomous Launch Pad for Micro Air Vehicles
    143.
    发明公开
    Autonomous Launch Pad for Micro Air Vehicles 有权
    Autonome StartrampefürMikroflugzeuge

    公开(公告)号：EP1767453A1

    公开(公告)日：2007-03-28

    申请号：EP06121033.2

    申请日：2006-09-21

    Applicant: Honeywell International Inc.

    Inventor： Horak, Dan T.

    IPC: B64C39/02 ,  B64F1/04 ,  A63H27/14

    CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

    Abstract: Autonomous micro air vehicles (102) surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad (120). The MAV has an engine (103) that is adapted to power the MAV. The launch pad has a starter (128) that is adapted to start the engine in the MAV when the MAV is resting on a launching surface (142) of the launch pad. The launch pad further has a battery (126) to power the starter.

    Abstract translation: 提供自动微型飞行器（102）监视系统。 一个实施例的MAV系统包括MAV和发射台（120）。 MAV具有适于为MAV供电的发动机（103）。 所述发射台具有起动器（128），当所述MAV处于所述发射台的发射表面（142）上时，所述起动器适于在所述MAV中启动所述发动机。 发射台还具有用于为起动器供电的电池（126）。

    Aircraft Rotor with Variable Collective Blade Angle
    146.
    发明公开
    Aircraft Rotor with Variable Collective Blade Angle 审中-公开

    公开(公告)号：US20230339602A1

    公开(公告)日：2023-10-26

    申请号：US17727531

    申请日：2022-04-22

    Applicant: Baxter Aerospace LLC.

    Inventor： Jeffrey Baxter ,  Michael Baxter

    IPC: B64C11/44 ,  B64C39/02 ,  B64C29/02

    CPC classification number: B64C11/44 ,  B64C39/024 ,  B64C29/02 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/104 ,  B64C2201/021

    Abstract: An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.

    Aircraft with Active Aerosurfaces
    148.
    发明申请
    Aircraft with Active Aerosurfaces 审中-公开

    公开(公告)号：US20180339771A1

    公开(公告)日：2018-11-29

    申请号：US15606163

    申请日：2017-05-26

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Paul K. Oldroyd ,  John Richard McCullough

    IPC: B64C29/00 ,  B64C11/46 ,  B64C5/02 ,  B64C3/10

    CPC classification number: B64C5/02 ,  B64C3/10 ,  B64C11/46 ,  B64C29/0033 ,  B64C29/02 ,  B64C2201/088 ,  B64C2201/108

    Abstract: An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode. The aircraft includes an airframe having first and second wings. A plurality of propulsion assemblies is attached to the airframe with each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface. A flight control system is operable to independently control each of the propulsion assemblies. For each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings.

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