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    Runway-independent omni-role modularity enhancement (ROME) vehicle
    31.
    发明授权
    Runway-independent omni-role modularity enhancement (ROME) vehicle 有权
    跑道独立的全能模块化增强（ROME）车辆

    公开(公告)号：US06926235B2

    公开(公告)日：2005-08-09

    申请号：US10600400

    申请日：2003-06-20

    Applicant: Richard P. Ouellette ,  Aaron J. Kutzmann

    Inventor： Richard P. Ouellette ,  Aaron J. Kutzmann

    IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

    CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

    Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

    Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

    Autonomous payload recovery system
    32.
    发明授权
    Autonomous payload recovery system 有权
    自主有效载​​荷恢复系统

    公开(公告)号：US06808144B1

    公开(公告)日：2004-10-26

    申请号：US10331009

    申请日：2002-12-26

    Applicant: Leland M. Nicolai ,  William R. Ramsey, Jr. ,  Douglas J. Robinson

    Inventor： Leland M. Nicolai ,  William R. Ramsey, Jr. ,  Douglas J. Robinson

    IPC: B64D1700

    CPC classification number: G05D1/105 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D17/025 ,  B64D17/343

    Abstract: A parafoil recovery system capable of autonomously controlling the descent profile of a payload to a recovery area and maneuvering the parafoil to execute a soft landing in the recovery area is disclosed. A descent profile management system determines wind speed and direction, altitude, heading, and position of the payload based on sensor input. The descent profile management system also determines a gliding flight path profile from the launch point to the desired recovery area. A flare and stall maneuver is executed at the end of the landing sequence by braking the parafoil to slow the vertical descent speed and groundspeed for a soft landing. The pitch attitude of the payload can be adjusted by the descent profile management system to prevent nose-first impact with the ground. The parafoil canopy is released from the payload upon touchdown to prevent the canopy from dragging the payload on the ground after landing.

    Abstract translation: 公开了一种能够自主地将有效载荷的下降曲线自动控制到恢复区域并操纵石灰石以在恢复区域中执行软着陆的石蜡回收系统。 下降轮廓管理系统基于传感器输入确定有效载荷的风速和方向，高度，航向和位置。 下降概况管理系统还确定从发射点到期望的恢复区域的滑翔飞行路径轮廓。 在着陆顺序结束时执行火炬和失速机动，通过制动铲车来减慢垂直下降速度和地面速度进行软着陆。 有效载荷的俯仰姿态可以通过下降轮廓管理系统进行调整，以防止与地面的鼻尖碰撞。 登陆时，Parafoil冠层从有效载荷中释放出来，以防止雨篷在着陆后拖动地面上的载荷。

    Recoverable airborne instrument platform
    33.
    发明授权
    Recoverable airborne instrument platform 有权
    可恢复的机载仪表平台

    公开(公告)号：US6144899A

    公开(公告)日：2000-11-07

    申请号：US410883

    申请日：1999-10-04

    Applicant: Michael L. Babb ,  Michael William Douglas ,  Davis M. Egle ,  Kenneth Wayne Howard

    Inventor： Michael L. Babb ,  Michael William Douglas ,  Davis M. Egle ,  Kenneth Wayne Howard

    IPC: B64C13/18 ,  B64C39/02 ,  B64D17/80 ,  G05D1/10 ,  B64D1/00

    CPC classification number: G05D1/101 ,  B64C13/18 ,  B64C39/024 ,  B64D17/80 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/125 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187

    Abstract: The recoverable airborne instrument platform accurately determines its present position and uses this data to execute a predetermined flight plan and ultimately guide its descent to a predetermined landing site. This is accomplished by installing the instrument package payload in the aerodynamic exterior housing of the recoverable airborne instrument platform, which has a plurality of moveable control surfaces thereon to autonomously control the altitude, attitude and flight path of the recoverable airborne instrument platform. A navigation circuit contained within the aerodynamic housing determines the geographic location of the recoverable airborne instrument platform as well as the location of at least one predetermined recovery site. The determined position data is used to dynamically calculate a flight path which allows the guidance control circuit to both execute a predetermined flight plan and controllably descend the recoverable instrument platform to a selected predetermined recovery site. Upon arrival at the selected predetermined recovery site, the recoverable airborne instrument platform descends to a predetermined height over the selected predetermined recovery site and activates a parachute release mechanism to controllably descend to the selected predetermined recovery site.

    Abstract translation: 可恢复的机载仪表平台精确地确定其当前位置，并使用该数据执行预定的飞行计划，并最终指导其下降到预定的着陆点。 这是通过在可恢复的机载仪表平台的空气动力学外壳中安装仪器包装有效载荷来实现的，该平台在其上具有多个可移动的控制表面以自主地控制可恢复的机载仪表平台的高度，姿态和飞行路径。 包含在空气动力学壳体内的导航电路确定可恢复的机载仪表平台的地理位置以及至少一个预定的恢复位置的位置。 所确定的位置数据用于动态地计算飞行路径，其允许引导控制电路执行预定的飞行计划并且可控地将可恢复的仪器平台下降到所选择的预定恢复位置。 在到达所选择的预定恢复站点时，可恢复的机载仪表平台在所选择的预定恢复站点上下降到预定高度，并激活降落伞释放机构以可控地下降到所选择的预定恢复站点。

    UAV retrieval system and method
    39.
    发明授权
    UAV retrieval system and method 有权
    无人机检索系统及方法

    公开(公告)号：US09221557B1

    公开(公告)日：2015-12-29

    申请号：US13788053

    申请日：2013-03-07

    Applicant: Lockheed Martin Corporation

    Inventor： Mark A. Friesel

    IPC: B64F1/02

    CPC classification number: B64F1/025 ,  B64C39/024 ,  B64C2201/182 ,  B64C2201/187 ,  B64F1/02

    Abstract: An apparatus for capture of an unmanned aerial vehicle (UAV) comprises a wind tunnel including at least one fan for generating airflow in the wind tunnel; sensors for sensing characteristics of the UAV; and a control system coupled to said sensors and said at least one fan. The control system is configured to cause the at least one fan to generate airflow based on the sensed characteristics of the UAV to bring the UAV that is in the wind tunnel to a low or zero airspeed above a floor of the wind tunnel, thereby allowing the UAV to be dropped onto the floor of the wind tunnel when the airflow and a motive force of the UAV are stopped.

    Abstract translation: 用于捕获无人驾驶飞行器（UAV）的装置包括风洞，其包括用于在风洞中产生气流的至少一个风扇; 用于感测无人机特性的传感器; 以及耦合到所述传感器和所述至少一个风扇的控制系统。 控制系统被配置成使得至少一个风扇基于UAV的感测特征产生气流，以使处于风洞中的无人机在风洞地板上方的低空或零空速，从而允许 当无人机的气流和无人机的动力停止时，无人机落在风洞的地板上。

    Unmanned aerial vehicle having an improved aerodynamic configuration
    40.
    发明授权
    Unmanned aerial vehicle having an improved aerodynamic configuration 有权
    具有改进的空气动力学配置的无人机

    公开(公告)号：US08905358B2

    公开(公告)日：2014-12-09

    申请号：US13140233

    申请日：2009-12-01

    Applicant: Abraham Abershitz

    Inventor： Abraham Abershitz

    IPC: B64C3/58 ,  B64C39/10 ,  B64C39/00 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187

    Abstract: An unmanned air vehicle includes a body having front and rear sections with at least one pair of end plates connected to the body, wherein one end plate within the at least one pair of end plates is connected to the left side of the body and another end plate within the at least one pair of end plates is connected to the right side of the body, each end plate having upper and lower sections, wherein: a) the upper section is positioned above a mean line of the body; b) the lower section is positioned below the mean line of the body; and c) a ratio of the area of the upper section to the area of the lower section is less than 1.

    Abstract translation: 一种无人驾驶飞行器包括具有连接到主体的至少一对端板的前部和后部的主体，其中至少一对端板内的一个端板连接到主体的左侧，另一端 所述至少一对端板中的板连接到所述主体的右侧，每个端板具有上部和下部，其中：a）所述上部位于所述主体的平均线之上; b）下部位于身体的平均线之下; 和c）上部区域与下部区域的面积的比率小于1。

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