公开(公告)号：US20220161939A1

公开(公告)日：2022-05-26

申请号：US17532830

申请日：2021-11-22

Applicant: Airbus Operations SAS

Inventor： Alain PORTE ,  Jacques LALANE ,  François PONS

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

Abstract: 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.

公开(公告)号：US20240253802A1

公开(公告)日：2024-08-01

申请号：US18425100

申请日：2024-01-29

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： François PONS ,  Laurent CAZEAUX ,  Arnulfo CARAZO MENDEZ ,  Florent MERCAT ,  Alexandre BELLANGER ,  Laurent PRESSEQ ,  Maxime GAUTHIER ,  Manuel TEIGNE ,  Philippe WESSEL ,  Joelle BONNEFONT

IPC: B64D33/02

CPC classification number: B64D33/02 ,  B64D2033/0206

Abstract: An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave at a sound frequency, wherein the alveolar structure comprises at least one partition provided with at least one cavity configured such that the partition vibrates at a vibrational frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.

公开(公告)号：US20210078718A1

公开(公告)日：2021-03-18

申请号：US17017482

申请日：2020-09-10

Applicant: Airbus Operations SAS

Inventor： Arnaud BOURHIS ,  Gregory ALBET ,  François PONS

IPC: B64D33/02 ,  B64D15/04

Abstract: 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.

公开(公告)号：US20190300191A1

公开(公告)日：2019-10-03

申请号：US16364888

申请日：2019-03-26

Applicant: Airbus Operations SAS

Inventor： Alain PORTE ,  François PONS ,  Gregory ALBET

IPC: B64D29/06 ,  B64D29/08

Abstract: 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.

公开(公告)号：US20250002168A1

公开(公告)日：2025-01-02

申请号：US18742140

申请日：2024-06-13

Applicant: Airbus Operations SAS

Inventor： Florent CREBASSOL ,  Grégoire SMITH ,  Florent HUET ,  François PONS

IPC: B64D33/02 ,  B64D45/02

Abstract: An acoustic attenuation panel comprising, from a first face to an opposite second face, an acoustically resistive structure, at least one cellular structure and a reflective layer. This acoustic attenuation panel comprises an induction-based frost treatment system which comprises at least one electromagnetic field generator positioned at the reflective layer and at least one electrically conductive element situated at the first face of the acoustic attenuation panel and configured to generate a heating through an induction phenomenon. Also an aircraft and an air intake of an aircraft nacelle comprising at least one such panel.

公开(公告)号：US20240253803A1

公开(公告)日：2024-08-01

申请号：US18425129

申请日：2024-01-29

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： François PONS ,  Laurent CAZEAUX ,  Arnulfo CARAZO MENDEZ ,  Florent MERCAT ,  Alexandre BELLANGER ,  Laurent PRESSEQ ,  Maxime GAUTHIER ,  Manuel TEIGNE ,  Philippe WESSEL ,  Joelle BONNEFONT

IPC: B64D33/02

CPC classification number: B64D33/02 ,  B64D2033/0206

Abstract: An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave of a sound frequency, wherein the alveolar structure comprises at least one attached element, separate from partitions, and configured for vibrating at a frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.

公开(公告)号：US20240010848A1

公开(公告)日：2024-01-11

申请号：US18249348

申请日：2021-10-18

Applicant: Airbus Operations SAS

Inventor： François PONS ,  Franck DOBIGEON ,  Cédric LOUBAT ,  Agathe BOUVET-MARCHAND ,  Julien GARCIA

IPC: C09D5/16 ,  B64C7/02 ,  B64D33/02

CPC classification number: C09D5/1687 ,  B64C7/02 ,  B64D33/02 ,  C09D5/1675 ,  B64C2230/26

Abstract: A self-cleaning external with a self-cleaning aerodynamic surface configured to extract at least some of the oxygen present in the atmosphere in contact with the aerodynamic surface so as to at least partially deprive a haemolymph of the insect residue, present on the aerodynamic surface after being hit by insects, of oxygen. Also, a vehicle with at least one such self-cleaning aerodynamic surface.

公开(公告)号：US20190308737A1

公开(公告)日：2019-10-10

申请号：US16377813

申请日：2019-04-08

Applicant: Airbus Operations SAS

Inventor： Alain PORTE ,  François PONS ,  Jonathan CARCONE

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

Abstract: 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.