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    Unmanned air vehicles and method of landing same
    4.
    发明授权
    Unmanned air vehicles and method of landing same 有权
    无人驾驶飞行器和降落方法相同

    公开(公告)号：US08123162B2

    公开(公告)日：2012-02-28

    申请号：US11098529

    申请日：2005-04-05

    Applicant: Omri Sirkis

    Inventor： Omri Sirkis

    IPC: B64C25/56 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187

    Abstract: There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneuver at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

    Abstract translation: 提供了包括发动机和机身的无人机（UAV），包括用于对连接或可连接到机身的至少一个充气套筒进行深度失速操纵的装置，以及用于在飞行期间使套筒充气的装置，其中，所述膨胀套筒 沿着机身的下侧延伸，以便在深度失速着陆期间保护它们。 还提供了一种用于操作无人机（UAV）的方法，包括发动机和机身。

    Control system for vehicles
    5.
    发明授权
    Control system for vehicles 有权
    车辆控制系统

    公开(公告)号：US08014909B2

    公开(公告)日：2011-09-06

    申请号：US10575223

    申请日：2004-03-25

    Applicant: Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

    Inventor： Kenneth E. Builta ,  James E. Harris ,  Bryan P. Honza ,  Jeffrey W. Epp ,  Kynn J. Schulte

    IPC: G06F17/00 ,  B64C13/00

    CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

    Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

    Abstract translation: 用于控制飞机飞行的系统具有传感器（37,43），接收器（45）和数字控制系统（57），所有这些都被携带在飞行器上。 传感器（37,43）确定飞行器相对于地球的位置和飞行器的惯性运动。 接收器（45）接收传送参考车辆相对于地球的位置和移动的传送数据（51,55）。 控制系统（57）使用来自传感器（37,43）和接收器（45）的数据来计算飞机相对于参考车辆的位置和速度，然后命令飞行器上的飞行控制装置（33）进行操纵 飞行器以相对于参考车辆保持选定位置和/或速度的方式。 该系统允许使用图形或触觉的用户界面。

    Cargo aircraft
    6.
    发明授权
    Cargo aircraft 有权
    货机

    公开(公告)号：US07699267B2

    公开(公告)日：2010-04-20

    申请号：US11782850

    申请日：2007-07-25

    Applicant: Elie Helou, Jr.

    Inventor： Elie Helou, Jr.

    IPC: B64C1/22

    CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

    Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

    Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

    System and method for transferring airplanes
    7.
    发明申请
    System and method for transferring airplanes 有权
    飞机转运系统及方法

    公开(公告)号：US20080099600A1

    公开(公告)日：2008-05-01

    申请号：US11528647

    申请日：2006-09-28

    Applicant: Arie Perry ,  Ran Braier

    Inventor： Arie Perry ,  Ran Braier

    IPC: B64C39/00

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/187 ,  B64F1/00 ,  Y02T50/82

    Abstract: A method for transferring airplanes and an unmanned airplane transfer system. The airplane transferring system includes: receiving a transfer signal responsive of a movement of an airplane control component; and transferring an airplane, by an unmanned airplane transfer system, in response to the transfer signal.

    Abstract translation: 一种用于转移飞机和无人驾驶飞机转移系统的方法。 飞机传送系统包括：响应飞机控制部件的运动接收传送信号; 并且通过无人驾驶飞行器传送系统来响应于传送信号传送飞机。

    RUNWAY-INDEPENDENT OMNI-ROLE MODULARITY ENHANCEMENT (ROME) VEHICLE
    8.
    发明申请
    RUNWAY-INDEPENDENT OMNI-ROLE MODULARITY ENHANCEMENT (ROME) VEHICLE 有权
    跑道独立的OMNI-角色模块化增强（ROME）车辆

    公开(公告)号：US20050029400A1

    公开(公告)日：2005-02-10

    申请号：US10600400

    申请日：2003-06-20

    Applicant: Richard Ouellette ,  Aaron Kutzmann

    Inventor： Richard Ouellette ,  Aaron 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。

    Liquid hydrogen stratospheric aircraft
    9.
    发明申请
    Liquid hydrogen stratospheric aircraft 有权
    液态氢气平流层飞机

    公开(公告)号：US20020005454A1

    公开(公告)日：2002-01-17

    申请号：US09826424

    申请日：2001-04-03

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

    IPC: B64C001/00 ,  B64B001/20 ,  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。

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