FR2896769B1 - IMPROVED COMPOSITE STRUCTURE FOR AIRCRAFT. - Google Patents

IMPROVED COMPOSITE STRUCTURE FOR AIRCRAFT.

Info

Publication number
FR2896769B1
FR2896769B1 FR0600772A FR0600772A FR2896769B1 FR 2896769 B1 FR2896769 B1 FR 2896769B1 FR 0600772 A FR0600772 A FR 0600772A FR 0600772 A FR0600772 A FR 0600772A FR 2896769 B1 FR2896769 B1 FR 2896769B1
Authority
FR
France
Prior art keywords
bar
lengthwise
aircraft
composite structure
improved composite
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.)
Expired - Fee Related
Application number
FR0600772A
Other languages
French (fr)
Other versions
FR2896769A1 (en
Inventor
Herve Payen
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 Helicopters SAS
Original Assignee
Eurocopter France SA
Eurocopter SA
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 Eurocopter France SA, Eurocopter SA filed Critical Eurocopter France SA
Priority to FR0600772A priority Critical patent/FR2896769B1/en
Priority to CA2575332A priority patent/CA2575332C/en
Publication of FR2896769A1 publication Critical patent/FR2896769A1/en
Application granted granted Critical
Publication of FR2896769B1 publication Critical patent/FR2896769B1/en
Expired - Fee Related 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
    • B64C1/062—Frames specially adapted to absorb crash loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/185—Spars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Dampers (AREA)
  • Laminated Bodies (AREA)

Abstract

The anti-crash structure consists of transverse (18B) and lengthwise (18) walls, each made from two layers of composition material on either side of an intermediate layer (20), connected by a cruciform bar (21), also of composition material. The lengthwise walls and cruciform bar extend beneath the floor of an aircraft body structure, with one vane of the bar inserted in a slot in a lengthwise wall, and a second one extending against one layer (19) of the second wall (18B) joined to the first by the bar. The intermediate layer can have a honeycomb or cellular structure e.g. of synthetic foam.
FR0600772A 2006-01-27 2006-01-27 IMPROVED COMPOSITE STRUCTURE FOR AIRCRAFT. Expired - Fee Related FR2896769B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR0600772A FR2896769B1 (en) 2006-01-27 2006-01-27 IMPROVED COMPOSITE STRUCTURE FOR AIRCRAFT.
CA2575332A CA2575332C (en) 2006-01-27 2007-01-22 Improved composite structure for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0600772A FR2896769B1 (en) 2006-01-27 2006-01-27 IMPROVED COMPOSITE STRUCTURE FOR AIRCRAFT.

Publications (2)

Publication Number Publication Date
FR2896769A1 FR2896769A1 (en) 2007-08-03
FR2896769B1 true FR2896769B1 (en) 2009-10-09

Family

ID=37031224

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0600772A Expired - Fee Related FR2896769B1 (en) 2006-01-27 2006-01-27 IMPROVED COMPOSITE STRUCTURE FOR AIRCRAFT.

Country Status (2)

Country Link
CA (1) CA2575332C (en)
FR (1) FR2896769B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2132446A1 (en) * 1971-06-30 1973-01-18 Ver Flugtechnische Werke SANDWICH PANEL WITH SHEARING FORCE CONNECTION
DE2757965C3 (en) * 1977-12-24 1980-07-03 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Thrust transmission element and method for its production
US4671470A (en) * 1985-07-15 1987-06-09 Beech Aircraft Corporation Method for fastening aircraft frame elements to sandwich skin panels covering same using woven fiber connectors
DE4417889B4 (en) * 1994-05-21 2006-04-13 Burkhart Grob Luft- Und Raumfahrt Gmbh & Co. Kg Aircraft body and method for its production
US6945727B2 (en) * 2002-07-19 2005-09-20 The Boeing Company Apparatuses and methods for joining structural members, such as composite structural members

Also Published As

Publication number Publication date
CA2575332A1 (en) 2007-07-27
FR2896769A1 (en) 2007-08-03
CA2575332C (en) 2014-04-01

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Legal Events

Date Code Title Description
CD Change of name or company name

Owner name: AIRBUS HELICOPTERS, FR

Effective date: 20140602

PLFP Fee payment

Year of fee payment: 11

PLFP Fee payment

Year of fee payment: 12

PLFP Fee payment

Year of fee payment: 13

PLFP Fee payment

Year of fee payment: 14

ST Notification of lapse

Effective date: 20200914