利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

7 条记录 (耗时 0.012 秒)

    RESISTIVE SKIN SHELL INCORPORATING PERFORATED METAL BANDS, AND ACOUSTIC INNER WALL OF AN AIRCRAFT AIR INTAKE FORMED FROM SUCH RESISTIVE SKIN SHELLS
    1.
    发明申请
    RESISTIVE SKIN SHELL INCORPORATING PERFORATED METAL BANDS, AND ACOUSTIC INNER WALL OF AN AIRCRAFT AIR INTAKE FORMED FROM SUCH RESISTIVE SKIN SHELLS 有权

    公开(公告)号：US20220161939A1

    公开(公告)日：2022-05-26

    申请号：US17532830

    申请日：2021-11-22

    申请人： Airbus Operations SAS

    发明人： Alain PORTE ,  Jacques LALANE ,  François PONS

    IPC分类号： B64D33/02 ,  B64D29/00 ,  G10K11/162

    摘要： A resistive skin shell for an acoustic panel or inner wall of an aircraft air intake, comprising an alternation, in a transverse direction, of perforated metal bands and of composite solid bands extending in a longitudinal direction. The perforated metal bands and the composite solid bands form a smooth outer face configured to be in contact with an aerodynamic stream, and a crenelated inner face. The composite solid bands have a thickness greater than the perforated metal bands. Since the perforations are provided in metal bands, which are intrinsically resistant to wear and erosion, the future proofing of the acoustic performance of the resistive skin is guaranteed. Since the composite solid bands, which are thicker, can ensure the mechanical strength of the skin, the thickness of the perforated metal bands can be reduced, allowing perforations with dimensions that are also reduced, having a lower impact on drag.

    AIR INLET, NACELLE, PROPULSIVE ASSEMBLY AND AIRCRAFT WITH GROOVED LIP
    4.
    发明申请
    AIR INLET, NACELLE, PROPULSIVE ASSEMBLY AND AIRCRAFT WITH GROOVED LIP 有权

    公开(公告)号：US20210078718A1

    公开(公告)日：2021-03-18

    申请号：US17017482

    申请日：2020-09-10

    申请人： Airbus Operations SAS

    发明人： Arnaud BOURHIS ,  Gregory ALBET ,  François PONS

    IPC分类号： B64D33/02 ,  B64D15/04

    摘要： An air inlet for an aircraft nacelle, including a lip and a front frame, which together form a duct with D-shaped section receiving hot air. The front frame is arranged in an advanced position inside the lip. The lip has de-icing grooves, which communicate with the duct and extend essentially downstream of the front frame. Downstream of the front frame, outside of the de-icing grooves, the lip has perforated zones provided with sound absorption holes. The air inlet includes a foil, which hermetically seals the de-icing grooves and is provided with sound absorption holes facing the perforated zones. The air inlet comprises acoustic panels inside the lip downstream of the front frame. The advanced position of the front frame, due to the de-icing grooves which ensure the de-icing of the lip downstream of the front frame, allows the acoustic treatment surface of the air inlet to be increased.

    AIRCRAFT NACELLE WITH ROTARY FAN COWLING INCORPORATING AN ACCESS HATCH
    5.
    发明申请
    AIRCRAFT NACELLE WITH ROTARY FAN COWLING INCORPORATING AN ACCESS HATCH 审中-公开

    公开(公告)号：US20190300191A1

    公开(公告)日：2019-10-03

    申请号：US16364888

    申请日：2019-03-26

    申请人： Airbus Operations SAS

    发明人： Alain PORTE ,  François PONS ,  Gregory ALBET

    IPC分类号： B64D29/06 ,  B64D29/08

    摘要： An aircraft nacelle comprising an air inlet, with a single fan cowling made of a single piece which extends over all the circumference of the fan. The fan cowling is borne by the air inlet and is mounted to be rotationally mobile about the axis of the nacelle relative to the air inlet, via a link and guiding arrangement comprising a circular rail and a runner capable of sliding along the circular rail. The fan cowling comprises one or more openings closed by hatches allowing access to the interior of the nacelle. The fan cowling has little susceptibility to being deformed both in flight and on the ground during maintenance operations. Furthermore, no pylon portion is needed in the zone of the fan cowling since the latter is not attached to the pylon.

    AIRCRAFT ENGINE NACELLE PROVIDED WITH AN ICING PROTECTION SYSTEM AND ASSOCIATED PROTECTION METHOD
    7.
    发明申请
    AIRCRAFT ENGINE NACELLE PROVIDED WITH AN ICING PROTECTION SYSTEM AND ASSOCIATED PROTECTION METHOD 审中-公开

    公开(公告)号：US20190308737A1

    公开(公告)日：2019-10-10

    申请号：US16377813

    申请日：2019-04-08

    申请人： Airbus Operations SAS

    发明人： Alain PORTE ,  François PONS ,  Jonathan CARCONE

    IPC分类号： B64D15/22 ,  B64D29/00 ,  B64D15/12 ,  H05B1/02 ,  H05B3/00

    摘要： An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.