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    Hydrogen powered aircraft
    64.
    发明授权
    Hydrogen powered aircraft 有权
    氢动力飞机

    公开(公告)号：US08011616B2

    公开(公告)日：2011-09-06

    申请号：US11973092

    申请日：2007-10-05

    Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

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

    IPC: B64D27/24 ,  B64D27/00

    CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  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 fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. 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。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 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。

    Systems and methods for capturing and controlling post-recovery motion of unmanned aircraft
    65.
    发明授权
    Systems and methods for capturing and controlling post-recovery motion of unmanned aircraft 有权
    捕获和控制无人机后恢复运动的系统和方法

    公开(公告)号：US07806366B2

    公开(公告)日：2010-10-05

    申请号：US11775600

    申请日：2007-07-10

    Applicant: Clifford Jackson

    Inventor： Clifford Jackson

    IPC: B64F1/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/165 ,  B64C2201/182

    Abstract: Systems and methods for capturing and controlling post-recovery motion of an unmanned aircraft are disclosed herein. An aircraft system in accordance with one embodiment of the invention, for example, can include a line capture assembly carried by an unmanned aircraft having a fuselage and a lifting surface. The line capture assembly can include a flexible support line having a first portion attached to an attachment point on the fuselage and a second portion extending from the attachment point spanwise along the lifting surface of the aircraft. The line capture assembly can also include an engagement device coupled to the second portion of the support line. The engagement device is releasably secured to the lifting surface.

    Abstract translation: 本文公开了用于捕获和控制无人飞行器的恢复后运动的系统和方法。 例如，根据本发明的一个实施例的飞行器系统可以包括由具有机身和提升表面的无人飞行器承载的线捕获组件。 线捕获组件可以包括柔性支撑线，其具有附接到机身上的附接点的第一部分和从飞行器的提升表面沿着方向从附接点延伸的第二部分。 线捕获组件还可以包括联接到支撑线的第二部分的接合装置。 接合装置可释放地固定到提升表面。

    CARGO AIRCRAFT
    66.
    发明申请
    CARGO AIRCRAFT 审中-公开
    货运飞机

    公开(公告)号：US20100116932A1

    公开(公告)日：2010-05-13

    申请号：US12636381

    申请日：2009-12-11

    Applicant: ELIE HELOU, JR.

    Inventor： ELIE HELOU, JR.

    IPC: B64C39/02 ,  B64C1/06 ,  B64C1/20

    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: In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight.

    Abstract translation: 在一个实施例中，公开了一种用于运输至少一个货物集装箱的飞机。 飞行器包括前机身，尾翼，梁结构，以及可拆卸地和结构地接合具有梁结构的至少一个货物集装箱的安装件。 梁结构设置在前机身和尾翼之间，梁结构被配置成接收至少一个货物集装箱。 梁结构和结构上接合的货物集装箱提供足够的结构刚度以支持飞行中的飞机。

    Hydrogen powered aircraft
    68.
    发明申请
    Hydrogen powered aircraft 有权
    氢动力飞机

    公开(公告)号：US20080203219A1

    公开(公告)日：2008-08-28

    申请号：US11973092

    申请日：2007-10-05

    Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

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

    IPC: B64D27/00

    CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  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 fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. 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。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 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。

    Cargo aircraft
    69.
    发明申请
    Cargo aircraft 有权
    货机

    公开(公告)号：US20060108477A1

    公开(公告)日：2006-05-25

    申请号：US10996799

    申请日：2004-11-23

    Applicant: Elie Helou

    Inventor： Elie Helou

    IPC: B64D9/00

    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。

    Unmanned aerial vehicle apparatus, system and method for retrieving data
    70.
    发明授权
    Unmanned aerial vehicle apparatus, system and method for retrieving data 失效
    无人驾驶飞行器具，检索数据的系统和方法

    公开(公告)号：US06868314B1

    公开(公告)日：2005-03-15

    申请号：US10186154

    申请日：2002-06-27

    Applicant: Bentley D. Frink

    Inventor： Bentley D. Frink

    IPC: B64C1/00 ,  B64C1/06 ,  B64C1/10 ,  B64C39/02 ,  B64D47/02 ,  H05K1/02 ,  H05K1/18 ,  B64C1/16

    CPC classification number: H05K1/02 ,  A01K79/00 ,  B64C1/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/125 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/187 ,  B64D47/02 ,  H05K1/181 ,  H05K2201/09145

    Abstract: The present invention relates to a system for retrieving data from remote difficult to reach terrain, such as wilderness areas, etc. and in particular to a system comprised of one or more surface based data collectors in communication with one or more wireless transceivers adapted to transmit the collected data to an unmanned aerial vehicle adapted to fly within a predetermined distance from the data collector and receive data collected therefrom. The present invention further relates to an unmanned aerial vehicle adapted to fly a flight pattern relative to a moveable surface object or for controlling the position of a moveable surface object relative to the flight path of the unmanned aerial vehicle. Finally, the present invention relates to an improved unmanned aerial vehicle having airframe structural elements with electrical circuits adhered to the surfaces of the structural elements.

    Abstract translation: 本发明涉及一种用于从远程难以达到的地形（例如荒野区域等）检索数据的系统，特别涉及一种由一个或多个基于表面的数据收集器组成的系统，该系统与一个或多个适于发送的无线收发器通信 将收集的数据传送到适合于从数据收集器预定距离内飞行并接收从其收集的数据的无人驾驶飞行器。 本发明还涉及一种适于相对于可移动表面物体飞行飞行图案或用于控制可移动表面物体相对于无人驾驶飞行器的飞行路径的位置的无人驾驶飞行器。 最后，本发明涉及一种具有机身结构元件的改进的无人驾驶飞行器，其中电路被粘附到结构元件的表面。

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