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    HYDROGEN POWERED AIRCRAFT
    272.
    发明申请
    HYDROGEN POWERED AIRCRAFT 审中-公开
    氢动力飞机

    公开(公告)号：WO2005084156A2

    公开(公告)日：2005-09-15

    申请号：PCT/US2004/019746

    申请日：2004-06-21

    Applicant: AEROVIRONMENT, INC.

    Inventor： MACCREADY, Paul, B. ,  HIBBS, Bart, D. ,  SWANSON, Kyle, D. ,  CURTIN, Robert, F.

    IPC: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/02 ,  B64C39/10 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30

    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。

    VERTICAL TAKEOFF AND LANDING AIRCRAFT
    274.
    发明申请
    VERTICAL TAKEOFF AND LANDING AIRCRAFT 审中-公开

    公开(公告)号：US20190185155A1

    公开(公告)日：2019-06-20

    申请号：US16280021

    申请日：2019-02-19

    Applicant: DeLorean Aerospace, LLC

    Inventor： Paul J. DeLorean

    IPC: B64C29/00 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64D27/24 ,  B64C27/32

    CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/028 ,  B64D27/24 ,  Y02T50/12 ,  Y02T50/64

    Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

    AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF
    275.
    发明申请
    AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF 审中-公开

    公开(公告)号：US20190061935A1

    公开(公告)日：2019-02-28

    申请号：US15767041

    申请日：2016-10-28

    Applicant: BAE Systems plc

    Inventor： David Julian Wright ,  Nicholas Giacomo Robert Colosimo ,  Clyde Warsop

    IPC: B64C29/00 ,  B64C3/38 ,  B64C39/10 ,  B64C39/02

    CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C29/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/18

    Abstract: An air vehicle comprising a main body and a pair of opposing wing members extending substantially laterally from the main body, at least a first propulsion device associated with a first of said wing members and a second propulsion device associated with a second of said wing members, each said propulsion device being arranged and configured to generate linear thrust relative to said main body, in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode and a rotary wing mode, wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device relative to the main body is the same as the direction of thrust generated by the second propulsion device, and in said second mode of flying, the direction of thrust generated by the first propulsion device relative to the main body is opposite to that generated by the second propulsion device.

    VERTICAL TAKEOFF AND LANDING AIRCRAFT
    278.
    发明申请
    VERTICAL TAKEOFF AND LANDING AIRCRAFT 审中-公开

    公开(公告)号：US20180222580A1

    公开(公告)日：2018-08-09

    申请号：US15456173

    申请日：2017-03-10

    Applicant: DeLorean Aerospace, LLC

    Inventor： Paul J. DeLorean

    IPC: B64C29/00 ,  B64D27/24 ,  B64C39/12 ,  B64C39/04 ,  B64C27/32 ,  B64C39/10

    CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C39/04 ,  B64C39/10 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/028 ,  B64D27/24 ,  Y02T50/12 ,  Y02T50/64

    Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

    TRICOPTER-TYPE ROTARY WING DRONE
    279.
    发明申请
    TRICOPTER-TYPE ROTARY WING DRONE 审中-公开

    公开(公告)号：US20170349272A1

    公开(公告)日：2017-12-07

    申请号：US15175803

    申请日：2016-06-07

    Applicant: EZNOV

    Inventor： Eric LAURENT ,  Thomas LEGRAND

    IPC: B64C27/28 ,  B64C29/00 ,  B64C39/02

    CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

    Abstract: The tricopter type rotary-wing drone includes three arms connected to a frame. Each of the free ends of the arms support a rotor with an axis perpendicular to the respective free end. The rotor is driven in rotation by a motor connected to power supply. The arms are pivotally mounted on the frame. Two arms automatically drive the rotor supported by their respective free ends into a position in which its axis forms an angle between −30° and +150° with the plane of the frame. The third arm automatically pivots, if necessary, into a position in which its free end is spaced apart from the apex being considered of the triangle by an angle between −60° and +60°.

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