中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

209 records (took 0.051 seconds)

    Liquid hydrogen aircraft
    162.
    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。

    Backup navigation system for unmanned aerial vehicles
    164.
    发明授权
    Backup navigation system for unmanned aerial vehicles 有权

    公开(公告)号：US11656638B1

    公开(公告)日：2023-05-23

    申请号：US17133610

    申请日：2020-12-23

    Applicant: Wing Aviation LLC

    Inventor： Dinuka Abeywardena ,  Damien Jourdan

    IPC: G05D1/10 ,  B64D47/08 ,  G01C11/06 ,  G01C21/32 ,  G06V20/13

    CPC classification number: G05D1/106 ,  B64D47/08 ,  G01C11/06 ,  G01C21/32 ,  G06V20/13 ,  B64C2201/028 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146

    Abstract: Described is a method that involves operating an unmanned aerial vehicle (UAV) to begin a flight, where the UAV relies on a navigation system to navigate to a destination. During the flight, the method involves operating a camera to capture images of the UAV's environment, and analyzing the images to detect features in the environment. The method also involves establishing a correlation between features detected in different images, and using location information from the navigation system to localize a feature detected in different images. Further, the method involves generating a flight log that includes the localized feature. Also, the method involves detecting a failure involving the navigation system, and responsively operating the camera to capture a post-failure image. The method also involves identifying one or more features in the post-failure image, and determining a location of the UAV based on a relationship between an identified feature and a localized feature.

    Pneumatic yaw control effector for aircraft
    168.
    发明授权
    Pneumatic yaw control effector for aircraft 有权

    公开(公告)号：US09944383B2

    公开(公告)日：2018-04-17

    申请号：US15052558

    申请日：2016-02-24

    Applicant: David R. Williams ,  Jürgen Seidel

    Inventor： David R. Williams ,  Jürgen Seidel

    IPC: B64C15/14 ,  B64C39/02 ,  B64D33/00

    CPC classification number: B64C15/14 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64D33/00

    Abstract: An apparatus and method for controlling a yaw moment of a flight vehicle, such as an aircraft. A wing structure of the flight vehicle has a first opening or actuator positioned by a first apex section of a first side of the wing, and has a second opening or actuator positioned away from or at a distance from a second apex section of a second side of the wing. The first side and the second side can each be positioned or located opposite a centerline of the wing or wing structure. A pressure source or other pressure supply device is in communication with the first opening or actuator and the second opening or actuator to which a pressurized fluid, such as air, is controlled and delivered to control or vary the yaw moment of the flight vehicle.

Patent Agency Ranking