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200 条记录 (耗时 0.02 秒)

    AIRCRAFT WITH EXTERNAL UPPER CARGO MODULE
    41.
    发明公开
    AIRCRAFT WITH EXTERNAL UPPER CARGO MODULE 审中-公开

    公开(公告)号：US20230339595A1

    公开(公告)日：2023-10-26

    申请号：US18004947

    申请日：2021-06-30

    申请人： ISRAEL AEROSPACE INDUSTRIES LTD.

    发明人： Uri Pinhasi ,  Rami Skladman ,  Gali Oz ,  Igor Golodriga ,  Meital Milo ,  Shay Arzi ,  Rami Zaphir ,  Michele Esther Hasid

    IPC分类号： B64C5/06 ,  B64C1/22 ,  B64D9/00 ,  A62C3/08

    CPC分类号： B64C1/22 ,  A62C3/08 ,  B64C5/06 ,  B64D9/003 ,  B64D2009/006

    摘要： There are provided examples of an enhanced cargo capacity aircraft, converted from a datum aircraft. The enhanced cargo capacity aircraft includes the datum aircraft and a cargo module. The datum aircraft includes at least a fuselage having a dorsal fuselage part. The cargo module is affixed to the datum aircraft, thereby converting the datum aircraft to the enhanced cargo capacity aircraft. The datum aircraft is designed for aerodynamic flight capability absent the cargo module. The enhanced cargo capacity aircraft is capable of aerodynamic flight. The cargo module provides enhanced cargo capacity to the datum aircraft. The cargo module includes an external aerodynamic fairing defining an internal cargo volume, and is configured for being conformally affixed in overlying relationship with respect to the dorsal fuselage part. The cargo module includes a cargo handling floor and at least one access door, and a cargo handling system configured for transporting and securing at least one cargo unit within the cargo volume. The cargo unit includes a standard unit load device (ULD).

    Leading edge structure for a flow control system of an aircraft
    42.
    发明授权
    Leading edge structure for a flow control system of an aircraft 有权

    公开(公告)号：US11673651B2

    公开(公告)日：2023-06-13

    申请号：US17277130

    申请日：2019-09-18

    申请人： AIRBUS OPERATIONS GmbH

    发明人： Alexander Büscher

    IPC分类号： B64C21/08 ,  B64C5/06 ,  B64C21/06

    CPC分类号： B64C21/08 ,  B64C5/06 ,  B64C21/06

    摘要： A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

    Gyroscopic Orbiter with Vertical Takeoff and Vertical Landing Capabilities
    46.
    发明申请
    Gyroscopic Orbiter with Vertical Takeoff and Vertical Landing Capabilities 审中-公开

    公开(公告)号：US20170088291A1

    公开(公告)日：2017-03-30

    申请号：US15184186

    申请日：2016-06-16

    申请人： Thomas Norman Hesse

    发明人： Thomas Norman Hesse

    IPC分类号： B64G1/14 ,  B64C29/02 ,  B64G1/00 ,  B64C11/46 ,  B64G1/40 ,  B64C29/00 ,  B64C5/06

    CPC分类号： B64G1/14 ,  B64C5/06 ,  B64C11/46 ,  B64C29/0033 ,  B64C29/02 ,  B64G1/002 ,  B64G1/40

    摘要： A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage.

    Method of inspecting impacts observed in fan casings
    47.
    发明授权
    Method of inspecting impacts observed in fan casings 有权
    检查风扇壳体影响的方法

    公开(公告)号：US09494486B2

    公开(公告)日：2016-11-15

    申请号：US14007269

    申请日：2012-03-15

    申请人： Julien Tran ,  Richard Lavignotte

    发明人： Julien Tran ,  Richard Lavignotte

    IPC分类号： G01M13/00 ,  F01D21/00 ,  F01D21/04 ,  G01N21/88 ,  G01N21/954 ,  B64C5/06 ,  G01N17/00 ,  G01B3/00 ,  B64D45/00 ,  B64C3/14

    CPC分类号： G01M13/00 ,  B64C5/06 ,  B64C2003/146 ,  B64D2045/0095 ,  F01D21/003 ,  F01D21/045 ,  F05B2280/6003 ,  F05D2260/80 ,  G01B3/00 ,  G01N17/00 ,  G01N21/8803 ,  G01N21/954 ,  Y02T50/672

    摘要： A method for inspecting impacts present on an internal face of a fan casing, the method including: spotting a first impact present on the internal face of the fan casing; delimiting an inspection area containing the first impact; spotting the various impacts present in the delimited inspection area, the various spotted impacts forming a set of impacts to be considered; measuring, for each impact that is to be considered, the depth of length of the impact; for each impact to be considered, determining a harmfulness value, using at least one chart relating the depth and length of each impact to be considered to a level of harmfulness; determining, for the inspection area containing the first impact, a total harmfulness value by adding together the harmfulness level determined for each impact to be considered.

    摘要翻译： 一种用于检查存在于风扇壳体的内表面上的冲击的方法，所述方法包括：检测存在于所述风扇壳体的内表面上的第一冲击; 划定包含第一冲击的检查区域; 查明划定的检查区存在的各种影响，各种影响形成一套待考虑的影响; 测量，对于要考虑的每个影响，影响的长度的深度; 为了考虑每一个影响，确定一个有害的价值，使用至少一个将每个影响的深度和长度相关的图表视为有害程度; 对于包含第一冲击的检查区域，通过将要考虑的每个影响确定的有害程度加在一起来确定总危害值。