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    Autonomous control of a parafoil recovery system for UAVs
    252.
    发明申请
    Autonomous control of a parafoil recovery system for UAVs 审中-公开
    无人机的parafoil恢复系统的自主控制

    公开(公告)号：US20030025038A1

    公开(公告)日：2003-02-06

    申请号：US09922167

    申请日：2001-08-06

    Applicant: Lockheed Martin Corporation

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

    IPC: B64D017/14 ,  B64D017/18 ,  B64D017/34

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

    Abstract: A parafoil system for autonomously controlling the gliding descent of a payload/UAV from a launch point to a predetermined recovery area and manipulating the parafoil to execute a soft landing in the recovery area, a sensing means associated with the system for determining wind speed and direction, as well as altitude, heading and position of the system, a means housed within the system for processing information received from the sensing means to determine the gliding flight path from the launch point to a predetermined recovery area and the execution of a flare maneuver to achieve a soft landing, control surface means on the parafoil canopy, mechanical means coupling the information processing means with the control surface means for adjusting the control surface means to accomplish the steering to the recovery area during gliding flight and the flare maneuver during landing, and a power source in the payload/UAV.

    Abstract translation: 一种用于自主地控制有效载荷/ UAV从发射点到预定恢复区域的滑翔下降并操纵石灰石以在恢复区域中执行软着陆的石蜡系统系统，与用于确定风速和方向的系统相关联的感测装置 ，以及系统的高度，航向和位置，装在系统内的装置，用于处理从感测装置接收的信息，以确定从发射点到预定恢复区域的滑行飞行路径，以及执行火炬操纵 实现软着陆，控制表面装置在parafoil冠层上，机械装置将信息处理装置与控制面相结合，用于调整控制面装置，以实现滑行飞行期间的恢复区域的转向和着陆期间的火炬机动，以及 有效载荷/无人机中的电源。

    Liquid hydrogen aircraft
    254.
    发明申请
    Liquid hydrogen aircraft 审中-公开
    液氢飞机

    公开(公告)号：US20020070312A1

    公开(公告)日：2002-06-13

    申请号：US10073518

    申请日：2002-02-11

    Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

    IPC: B64B001/20 ,  B64C001/00 ,  B64C017/00

    CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

    Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

    Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

    Unmanned mobile device
    255.
    发明申请
    Unmanned mobile device 失效
    无人机移动设备

    公开(公告)号：US20020060267A1

    公开(公告)日：2002-05-23

    申请号：US09961447

    申请日：2001-09-25

    Inventor： Arie Yavnai

    IPC: B62D057/00

    CPC classification number: G05D1/0038 ,  B62D57/02 ,  B62D57/04 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/0044

    Abstract: A remotely-controlled unmanned mobile device (UMD) adapted to function as a robot scout to enter and reconnoiter the site of a disaster and to communicate to a rescue mission information regarding conditions prevailing at the site, making it possible for the mission to decide on rescue measures appropriate to these conditions. The UMD is operable in either of two modes. In its air-mobility mode the UMD is able to vertically take off and land, to fly to the site and then hover thereover. In its ground-mobility mode, the UMD can walk on legs over difficult terrain and through wrecked structures and ruins. The UMD is provided with condition-sensitive sensors for gathering data regarding conditions prevailing at the site, and position-sensitive sensors for avoiding obstacles in the path of the walking UMD, thereby assuring safe mobility. Other sensors govern geo-referenced navigation and flight control functions.

    Abstract translation: 适用于作为机器人侦察兵的远程控制的无人机移动设备（UMD），用于进入和侦察灾害现场，并向救援任务通报有关现场情况的信息，使特派团有可能决定 救援措施适合这些条件。 UMD可以在两种模式之一中操作。 在其空中移动模式下，UMD能够垂直起飞和着陆，飞到现场，然后悬停在此处。 在地面移动模式下，UMD可以在困难的地形上通过失落的结构和遗迹走上双腿。 UMD提供了条件敏感传感器，用于收集有关现场情况的数据，以及位置敏感传感器，用于避免步行UMD路径中的障碍物，从而确保安全的移动性。 其他传感器控制地理参考导航和飞行控制功能。

    Method for remote-controlling an unmanned aerial vehicle
    256.
    发明授权
    Method for remote-controlling an unmanned aerial vehicle 失效
    遥控无人驾驶飞行器的方法

    公开(公告)号：US06377875B1

    公开(公告)日：2002-04-23

    申请号：US09582815

    申请日：2000-06-29

    Applicant: Hans-Juergen Schwaerzler

    Inventor： Hans-Juergen Schwaerzler

    IPC: G05D100

    CPC classification number: G05D1/0022 ,  B64C39/024 ,  B64C2201/141 ,  B64C2201/146

    Abstract: To avoid an uncontrolled flight of a remotely controlled unmanned air vehicle (UAV), upon loss of radio contact between a control station (6) and the UAV (1), the UAV (1) flies on a preprogrammed safety route (3), as required the UAV is guided to a flight path (2) that is remote-controlled from the control station (6), and, in the event of an interruption of the radio contact, the UAV will fly on a substitute route calculated with on-board equipment, without active intervention from the remote control station.

    Abstract translation: 为了避免远程控制的无人驾驶飞行器（UAV）的不受控制的飞行，在控制站（6）和无人机（1）之间的无线电接触失去时，UAV（1）在预编程的安全路线（3）上飞行， 根据需要，UAV被引导到从控制站（6）远程控制的飞行路径（2），并且在无线电联系中断的情况下，UAV将以通过计算的替代路线飞行 车载设备，无需远程控制站的主动干预。

    Passively stable hovering system
    257.
    发明授权
    Passively stable hovering system 失效
    被动稳定的悬停系统

    公开(公告)号：US5070955A

    公开(公告)日：1991-12-10

    申请号：US583477

    申请日：1990-09-17

    Applicant: Peter B. S. Lissaman ,  Herman M. Drees ,  Charles J. Sink ,  William D. Watson

    Inventor： Peter B. S. Lissaman ,  Herman M. Drees ,  Charles J. Sink ,  William D. Watson

    IPC: B64C27/20 ,  B64C39/02

    CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162

    Abstract: A flight system capable of passively stable hover and horizontal translatory flight, comprises an apparatus defining a vertical axis, and including multiple ducts with substantially vertical axes in hover mode, spaced the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts in hover; and fluid flow deflector structure in the path of the flowing duct fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus, as well as stability when the entire device is tilted through approximately 90.degree. to execute horizontal translatory flight.

    Abstract translation: 能够被动地稳定悬停和水平平移的飞行系统包括限定垂直轴的装置，并且包括多个具有悬挂模式的基本垂直轴线的管道，该轴线间隔开; 管道中的流体动量发生器以在悬浮的管道中使流体向下流动; 以及在流动管道流体的路径中的流体流动偏转器结构，并且成角度以使流体流离开轴线，以便提供装置悬停的稳定性，以及当整个装置倾斜通过时的稳定性 大约90°执行水平平移飞行。

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