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    Autonomous launch pad for micro air vehicles
    111.
    发明申请
    Autonomous launch pad for micro air vehicles 审中-公开
    微型飞行器自动发射台

    公开(公告)号：US20070228214A1

    公开(公告)日：2007-10-04

    申请号：US11235057

    申请日：2005-09-26

    Applicant: Dan Horak

    Inventor： Dan Horak

    IPC: B64F1/04

    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 surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad. The MAV has an engine that is adapted to power the MAV. The launch pad has a starter that is adapted to start the engine in the MAV when the MAV is resting on a launching surface of the launch pad. The launch pad further has a battery to power the starter.

    Abstract translation: 提供自动微型飞行器车辆监视系统。 一个实施例的MAV系统包括MAV和发射台。 MAV具有适用于为MAV供电的发动机。 发射台具有一个启动器，当MAV在发射台的发射表面上时，该启动器适于在MAV中启动发动机。 发射台还有一个电池为起动器供电。

    Methods and apparatuses for launching, capturing, and storing unmanned aircraft, including a container having a guide structure for aircraft components
    115.
    发明授权
    Methods and apparatuses for launching, capturing, and storing unmanned aircraft, including a container having a guide structure for aircraft components 有权
    用于发射，捕获和存储无人飞行器的方法和装置，包括具有用于飞行器部件的引导结构的容器

    公开(公告)号：US07104495B2

    公开(公告)日：2006-09-12

    申请号：US11269395

    申请日：2005-11-08

    Applicant: Brian T. McGeer

    Inventor： Brian T. McGeer

    IPC: B64F5/00

    CPC classification number: B64F1/04 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06

    Abstract: Methods and apparatuses for launching, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

    Abstract translation: 描述了用于发射，捕获和存储无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞机部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

    METHODS AND APPARATUSES FOR LAUNCHING UNMANNED AIRCRAFT, INCLUDING METHODS AND APPARATUSES FOR TRANSMITTING FORCES TO THE AIRCRAFT DURING LAUNCH
    116.
    发明申请
    METHODS AND APPARATUSES FOR LAUNCHING UNMANNED AIRCRAFT, INCLUDING METHODS AND APPARATUSES FOR TRANSMITTING FORCES TO THE AIRCRAFT DURING LAUNCH 有权
    发射无人机的方法和装置，包括发射飞机发射力的方法和装置

    公开(公告)号：US20060151667A1

    公开(公告)日：2006-07-13

    申请号：US10758948

    申请日：2004-01-16

    Applicant: Brian Dennis ,  Andreas von Flotow

    Inventor： Brian Dennis ,  Andreas von Flotow

    IPC: B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/06

    Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes an extendable boom. A launch carriage is positioned on a launch guide structure of the boom and carries the aircraft during takeoff. An energy reservoir is configured to provide energy to the launch carriage during takeoff of the aircraft, and can absorb energy from the launch carriage to decelerate the launch carriage after takeoff. The apparatus can further include a transmission that smoothly and rapidly accelerates and/or decelerates the launch carriage.

    Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括可扩展起重臂的装置发射。 发射架位于起重臂的发射导向结构上，并在起飞时承载飞机。 能量储存器构造成在飞行器起飞期间向发射台提供能量，并且可以从起飞台吸收能量，以在起飞后减速发射台。 该装置还可以包括使发射台平滑且快速地加速和/或减速的变速器。

    Landing and take-off assembly for vertical take-off and landing and horizontal flight aircraft
    119.
    发明授权
    Landing and take-off assembly for vertical take-off and landing and horizontal flight aircraft 失效
    垂直起降飞机着陆和起飞组装

    公开(公告)号：US5799900A

    公开(公告)日：1998-09-01

    申请号：US680000

    申请日：1996-07-15

    Applicant: William R. McDonnell

    Inventor： William R. McDonnell

    IPC: B64C29/02 ,  B64F1/12 ,  B64C29/00

    CPC classification number: B64C39/024 ,  B64C29/02 ,  B64F1/02 ,  B64F1/12 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/182 ,  Y02T50/82

    Abstract: An aircraft adapted for flight in helicopter mode with its longitudinal axis oriented generally vertically and in airplane mode with its longitudinal axis oriented generally horizontally is provided with the capability of launching and landing with the tail end directed skyward. The invention also includes improvements to the controllability and efficiency of aircraft in helicopter mode provided by the stabilizer wings and relative rotation of the fuselage section about the aircraft's longitudinal axis. The aircraft has an elongate boom positioned between the rear fuselage and the stabilizer wings for engagement with a base structure. The base structure may be attached to a building, a trailer transporter, a ship or some other structure. The base may be a beam having latching arms that swing inward when pressure from the boom is applied, then trap the boom in a recess between the latching arm and beam, thereby suspending the aircraft. An actuator for releasing the latching arms is provided to allow the aircraft to launch.

    Abstract translation: 适用于以直升机模式飞行的飞机，其纵轴大致竖直地定向，并且在其纵向轴线大致水平地定向的飞行模式中具有以尾端朝向天空的方式发射和着陆的能力。 本发明还包括对由稳定翼提供的直升机模式的飞行器的可控性和效率的改进以及机身部分围绕飞机的纵向轴线的相对旋转。 飞机具有位于后机身和稳定翼之间的细长吊杆，用于与基座结构接合。 基座结构可以附接到建筑物，拖车运输工具，船舶或其他结构上。 基座可以是具有当来自起重臂的压力施加时向内摆动的闩锁臂的梁，然后将吊杆捕获在闩锁臂和梁之间的凹部中，从而悬挂飞行器。 提供用于释放锁定臂的致动器以允许飞行器发射。

    Point-landing method for non vertical take off and landing flying objects
    120.
    发明授权
    Point-landing method for non vertical take off and landing flying objects 失效
    非垂直起飞和着陆飞行物体的点着陆方法

    公开(公告)号：US4790497A

    公开(公告)日：1988-12-13

    申请号：US58815

    申请日：1987-06-05

    Applicant: Meir Yoffe

    Inventor： Meir Yoffe

    IPC: B64F1/00

    CPC classification number: B64F1/02 ,  B64C2201/182

    Abstract: The present invention relates to a point landing method for a flying object, e.g., an aircraft (manned or unmanned), a helicopter, a missile, in a location which may be stationary, e.g., a ground plot or the roof of a building or a moving one, e.g., a car, ship, train.

    Abstract translation: 本发明涉及一种用于飞行物体的点着陆方法，例如飞行器（载人或无人驾驶），直升机，导弹，位于可能是静止的位置，例如地面或建筑物的屋顶，或 一个移动的，例如汽车，船只，火车。

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