公开(公告)号：US11873077B2

公开(公告)日：2024-01-16

申请号：US17776373

申请日：2020-11-03

Applicant: Airbus SAS

Inventor： Mathias Farouz-Fouquet

IPC: B64C21/02

CPC classification number: B64C21/02

Abstract: An aerodynamic element includes at least one first, fixed aerodynamic part including a box section that is covered at least partly by a plate with an extreme part, and one second aerodynamic part including a peripheral surface with an end and at least one holding element provided with a shoulder which forms, with the extreme part of the plate, a groove in which the end of the peripheral surface can be housed, such that the peripheral surface and the plate form a junction having an ascending profile. The presence of the groove makes it possible to obtain a continuous ascending junction with favors a laminar airstream on the upper surface of the aerodynamic element.

公开(公告)号：US11027818B2

公开(公告)日：2021-06-08

申请号：US16108575

申请日：2018-08-22

Applicant: Airbus Operations S.A.S. ,  AIRBUS SAS

Inventor： Daniel Kierbel ,  Mathias Farouz-Fouquet ,  Laurent Malard

IPC: B64C3/26 ,  B64C3/28 ,  B64C21/10 ,  B21D53/92 ,  B29C45/14 ,  B21D26/021 ,  B64C3/24 ,  B29C70/78

Abstract: A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

公开(公告)号：US20190061908A1

公开(公告)日：2019-02-28

申请号：US16108575

申请日：2018-08-22

Applicant: Airbus Operations S.A.S. ,  AIRBUS SAS

Inventor： Daniel Kierbel ,  Mathias Farouz-Fouquet ,  Laurent Malard

IPC: B64C3/26 ,  B64C3/28 ,  B64C21/10 ,  B29C45/14 ,  B21D26/021 ,  B21D53/92

Abstract: A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

公开(公告)号：US11135793B2

公开(公告)日：2021-10-05

申请号：US16165220

申请日：2018-10-19

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Daniel Kierbel ,  Mathias Farouz-Fouquet ,  Laurent Malard

IPC: B29C73/10 ,  B64F5/00 ,  B29C73/12 ,  G05B19/18 ,  B33Y10/00 ,  B33Y40/00 ,  B33Y50/02 ,  B29C64/393 ,  B29C64/10 ,  B29C63/00 ,  B29L31/30 ,  B33Y70/00 ,  B33Y80/00 ,  B29K55/02 ,  B29K67/00

Abstract: A filling method for filling surface imperfections on a surface of a wing comprising a scanning step in which a control unit controls a movement of a scanner past the surface of the wing to scan the surface and transmit the collected data to the control unit, a computation step in which the control unit computes a digitized surface from the data, a determination step in which the control unit determines each surface imperfection by comparing the reference surface and the digitized surface, a generation step in which the control unit generates a digital model of the patch intended to fill the surface imperfection, and a printing step in which the control unit controls the movement of a 3D printer past each surface imperfection and commands the activation of the 3D printer in order to make it print the patch.

公开(公告)号：US11579050B2

公开(公告)日：2023-02-14

申请号：US17190623

申请日：2021-03-03

Applicant: AIRBUS SAS

Inventor： Mathias Farouz-Fouquet

IPC: G01N1/22 ,  B64D47/00 ,  G01N15/02

Abstract: The system, configured for being on board an aircraft, includes a probe for collecting samples of contrail, a chamber for collecting the samples, a collecting conduit for conducting the samples from the collecting probe the collecting chamber and at least one device for measuring at least one parameter characterizing the samples in the collecting conduit while they are conducted from the collecting probe to the collecting chamber. By virtue of the system, it is not necessary to use a second aircraft that follows the aircraft for collecting samples of contrail.

公开(公告)号：US20210285851A1

公开(公告)日：2021-09-16

申请号：US17190623

申请日：2021-03-03

Applicant: AIRBUS SAS

Inventor： Mathias Farouz-Fouquet

IPC: G01N1/22 ,  B64D47/00

Abstract: The system, configured for being on board an aircraft, includes a probe for collecting samples of contrail, a chamber for collecting the samples, a collecting conduit for conducting the samples from the collecting probe the collecting chamber and at least one device for measuring at least one parameter characterizing the samples in the collecting conduit while they are conducted from the collecting probe to the collecting chamber. By virtue of the system, it is not necessary to use a second aircraft that follows the aircraft for collecting samples of contrail.