FR3155809B1 - Structure principale d’un fuselage d’aéronef comprenant des cadres fixés directement à une peau et procédé associé - Google Patents

Structure principale d’un fuselage d’aéronef comprenant des cadres fixés directement à une peau et procédé associé

Info

Publication number
FR3155809B1
FR3155809B1 FR2313073A FR2313073A FR3155809B1 FR 3155809 B1 FR3155809 B1 FR 3155809B1 FR 2313073 A FR2313073 A FR 2313073A FR 2313073 A FR2313073 A FR 2313073A FR 3155809 B1 FR3155809 B1 FR 3155809B1
Authority
FR
France
Prior art keywords
fixed directly
main structure
panel
aircraft fuselage
skin
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2313073A
Other languages
English (en)
Other versions
FR3155809A1 (fr
Inventor
Laurent Dubreuil
Gilles Andrieu
Sandrine Meyer
Maxime Daubeuf
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Atlantic SAS
Original Assignee
Airbus Atlantic SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Atlantic SAS filed Critical Airbus Atlantic SAS
Priority to FR2313073A priority Critical patent/FR3155809B1/fr
Priority to PCT/EP2024/082209 priority patent/WO2025114005A1/fr
Publication of FR3155809A1 publication Critical patent/FR3155809A1/fr
Application granted granted Critical
Publication of FR3155809B1 publication Critical patent/FR3155809B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Body Structure For Vehicles (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

Une structure principale (S) d’un fuselage d’aéronef comprenant au moins un panneau (1), une pluralité de raidisseurs (2), s’étendant parallèlement à un axe longitudinal (X) et comprenant deux semelles (21) fixées directement au panneau (1), et une pluralité de cadres (3), chaque cadre (3) s’étendant sensiblement transversalement à l'axe longitudinal (X) et comprenant une base (31), la base (31) comprenant une alternance de pieds (33) fixés directement au panneau (1) et d’arches (34) contournant le corps (22) des raidisseurs (2) ; au moins un premier raidisseur (2) de la pluralité de raidisseur (2) comprend au moins une encoche (23), formée au moins en partie dans une semelle (21), définissant une première zone de jonction, un pied (33) d’un cadre (3) étant fixé directement au panneau (1) au moins en partie selon la première zone de jonction. Figure de l’abrégé : Figure 4
FR2313073A 2023-11-27 2023-11-27 Structure principale d’un fuselage d’aéronef comprenant des cadres fixés directement à une peau et procédé associé Active FR3155809B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2313073A FR3155809B1 (fr) 2023-11-27 2023-11-27 Structure principale d’un fuselage d’aéronef comprenant des cadres fixés directement à une peau et procédé associé
PCT/EP2024/082209 WO2025114005A1 (fr) 2023-11-27 2024-11-13 Structure principale d'un fuselage d'aéronef comprenant des cadres fixés directement à une peau et procédé associé

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2313073 2023-11-27
FR2313073A FR3155809B1 (fr) 2023-11-27 2023-11-27 Structure principale d’un fuselage d’aéronef comprenant des cadres fixés directement à une peau et procédé associé

Publications (2)

Publication Number Publication Date
FR3155809A1 FR3155809A1 (fr) 2025-05-30
FR3155809B1 true FR3155809B1 (fr) 2025-10-24

Family

ID=89977219

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2313073A Active FR3155809B1 (fr) 2023-11-27 2023-11-27 Structure principale d’un fuselage d’aéronef comprenant des cadres fixés directement à une peau et procédé associé

Country Status (2)

Country Link
FR (1) FR3155809B1 (fr)
WO (1) WO2025114005A1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7527222B2 (en) * 2004-04-06 2009-05-05 The Boeing Company Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections
DE102007029500B4 (de) * 2007-06-25 2013-02-14 Airbus Operations Gmbh Verfahren zum Koppeln von Versteifungsprofilelementen sowie Strukturbauteil
GB2571911A (en) * 2017-12-21 2019-09-18 Airbus Operations Gmbh A Stiffener for an Aircraft Assembly
EP3501804A1 (fr) * 2017-12-22 2019-06-26 The Boeing Company Panneau de raidisseurs renforcés avec des empilements de stratifié d'indexation intégré

Also Published As

Publication number Publication date
FR3155809A1 (fr) 2025-05-30
WO2025114005A1 (fr) 2025-06-05

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