CA2423665A1 - Bord d'ouverture de panneau de revetement composite et son procede de fabrication - Google Patents

Bord d'ouverture de panneau de revetement composite et son procede de fabrication Download PDF

Info

Publication number
CA2423665A1
CA2423665A1 CA002423665A CA2423665A CA2423665A1 CA 2423665 A1 CA2423665 A1 CA 2423665A1 CA 002423665 A CA002423665 A CA 002423665A CA 2423665 A CA2423665 A CA 2423665A CA 2423665 A1 CA2423665 A1 CA 2423665A1
Authority
CA
Canada
Prior art keywords
skin
panel
outer skin
core
component
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.)
Abandoned
Application number
CA002423665A
Other languages
English (en)
Inventor
Timothy Myron Hazen
John Verdi Howard
Josef Antonin Fila
Steven Joel Addison
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.)
Individual
Original Assignee
Bell Helicopter Textron Inc
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 Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Publication of CA2423665A1 publication Critical patent/CA2423665A1/fr
Abandoned legal-status Critical Current

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
    • B64C1/12—Construction or attachment of skin 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
    • 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)
  • Securing Of Glass Panes Or The Like (AREA)

Abstract

L'invention concerne un châssis de composant (18) destiné à supporter un composant (28) dans un véhicule. Ledit composant (28) peut être une porte, une fenêtre, ou une pièce d'aéronef nécessitant une interface encastrée dans l'aéronef. Le châssis de composant (18) comprend revêtement extérieur (20) doté d'un bord évidé (16) disposé généralement autour du périmètre du châssis de composant (18). Un revêtement intérieur (24) est placé dans l'aéronef et une âme en nids d'abeilles (22) est prise en sandwich entre ledit revêtement intérieur et le revêtement extérieur (20).
CA002423665A 2000-10-02 2001-09-27 Bord d'ouverture de panneau de revetement composite et son procede de fabrication Abandoned CA2423665A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US67696800A 2000-10-02 2000-10-02
US09/676,968 2000-10-02
PCT/US2001/030299 WO2002028709A1 (fr) 2000-10-02 2001-09-27 Bord d'ouverture de panneau de revetement composite et son procede de fabrication

Publications (1)

Publication Number Publication Date
CA2423665A1 true CA2423665A1 (fr) 2002-04-11

Family

ID=24716753

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002423665A Abandoned CA2423665A1 (fr) 2000-10-02 2001-09-27 Bord d'ouverture de panneau de revetement composite et son procede de fabrication

Country Status (2)

Country Link
CA (1) CA2423665A1 (fr)
WO (1) WO2002028709A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6729576B2 (en) * 2002-08-13 2004-05-04 Sikorsky Aircraft Corporation Composite tail cone assembly
US9932123B2 (en) 2011-06-07 2018-04-03 Composite Helicopters International Holdings Ltd Monocoque helicopter fuselage with integral tail boom
FR2982588B1 (fr) * 2011-11-10 2013-11-22 Aircelle Sa Panneau composite a ecope de prelevement integree
JP5811082B2 (ja) * 2012-12-19 2015-11-11 横浜ゴム株式会社 航空機用内装パネルの結合構造
EP2842865B1 (fr) 2013-08-28 2019-12-18 Airbus Operations GmbH Panneau de fenêtre pour une cellule d'aéronef et son procédé de production
US11628646B2 (en) 2019-04-05 2023-04-18 Hanwha Azdel, Inc. Composite panels including an aesthetic edge
US20200377191A1 (en) * 2019-05-29 2020-12-03 The Boeing Company Stringerless sandwich fuselage panels

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3202594A1 (de) * 1982-01-27 1983-08-11 Ford-Werke AG, 5000 Köln Kraftfahrzeugkarosserie mit einem fest verbundenen dach aus verbundwerkstoff
US4542056A (en) * 1983-08-26 1985-09-17 The Boeing Company Composite structure having conductive surfaces
US5354195A (en) * 1992-12-23 1994-10-11 United Technologies Corporation Composite molding apparatus for high pressure co-cure molding of lightweight honeycomb core composite articles having ramped surfaces utilizing low density, stabilized ramped honeycomb cores

Also Published As

Publication number Publication date
WO2002028709A1 (fr) 2002-04-11

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