公开(公告)号：US11001362B2

公开(公告)日：2021-05-11

申请号：US16166328

申请日：2018-10-22

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

Inventor： Pascal Chaumel ,  Johan Dentesano ,  Emily Parken

IPC: B64C1/14

Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

公开(公告)号：US20190118928A1

公开(公告)日：2019-04-25

申请号：US16166328

申请日：2018-10-22

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

Inventor： Pascal Chaumel ,  Johan Dentesano ,  Emily Parken

IPC: B64C1/14

Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

公开(公告)号：US12280891B2

公开(公告)日：2025-04-22

申请号：US18374175

申请日：2023-09-28

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Damien Aguera ,  Matthieu De Kergommeaux ,  Johan Dentesano

IPC: B64F5/10 ,  B64C1/06

Abstract: A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.

公开(公告)号：US20240109672A1

公开(公告)日：2024-04-04

申请号：US18374175

申请日：2023-09-28

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Damien Aguera ,  Matthieu De Kergommeaux ,  Johan Dentesano

IPC: B64F5/10 ,  B64C1/06

CPC classification number: B64F5/10 ,  B64C1/069

Abstract: A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.