ATE531508T1 - Verfahren für den entwurf einer verbundplatte - Google Patents

Verfahren für den entwurf einer verbundplatte

Info

Publication number
ATE531508T1
ATE531508T1 AT09738412T AT09738412T ATE531508T1 AT E531508 T1 ATE531508 T1 AT E531508T1 AT 09738412 T AT09738412 T AT 09738412T AT 09738412 T AT09738412 T AT 09738412T AT E531508 T1 ATE531508 T1 AT E531508T1
Authority
AT
Austria
Prior art keywords
panel
orientation angle
zones
designing
plies
Prior art date
Application number
AT09738412T
Other languages
English (en)
Inventor
Lars Krog
Original Assignee
Airbus Operations Ltd
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 Operations Ltd filed Critical Airbus Operations Ltd
Application granted granted Critical
Publication of ATE531508T1 publication Critical patent/ATE531508T1/de

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
    • B29C70/202—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • 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
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • 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
    • 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
    • B64C3/00—Wings
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/26—Composites
    • 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)
  • Composite Materials (AREA)
  • Chemical & Material Sciences (AREA)
  • Theoretical Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Geometry (AREA)
  • Textile Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Evolutionary Computation (AREA)
  • Computer Hardware Design (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Panels For Use In Building Construction (AREA)
  • Making Paper Articles (AREA)
  • Dry Formation Of Fiberboard And The Like (AREA)
AT09738412T 2008-04-28 2009-04-14 Verfahren für den entwurf einer verbundplatte ATE531508T1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0807643.2A GB0807643D0 (en) 2008-04-28 2008-04-28 Method of designing a composite panel
PCT/GB2009/050360 WO2009133382A1 (en) 2008-04-28 2009-04-14 Method of designing a composite panel

Publications (1)

Publication Number Publication Date
ATE531508T1 true ATE531508T1 (de) 2011-11-15

Family

ID=39522627

Family Applications (1)

Application Number Title Priority Date Filing Date
AT09738412T ATE531508T1 (de) 2008-04-28 2009-04-14 Verfahren für den entwurf einer verbundplatte

Country Status (10)

Country Link
US (1) US8731870B2 (de)
EP (1) EP2271479B1 (de)
JP (1) JP5401538B2 (de)
CN (1) CN102015266B (de)
AT (1) ATE531508T1 (de)
BR (1) BRPI0910827A2 (de)
CA (1) CA2721874C (de)
GB (1) GB0807643D0 (de)
RU (1) RU2491168C2 (de)
WO (1) WO2009133382A1 (de)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201006257D0 (en) 2010-04-15 2010-06-02 Airbus Operations Ltd Composite structure
FR2960179A1 (fr) * 2010-05-20 2011-11-25 Airbus Operations Sas Piece structurale composite a rigidite evolutive
CN103353916B (zh) * 2012-09-10 2017-03-01 中国航空工业集团公司科学技术委员会 基于工程的复合材料层合板铺层优化后处理方法
US20160009368A1 (en) * 2013-02-28 2016-01-14 The Boeing Company Composite laminated plate having reduced crossply angle
CN105035302B (zh) * 2015-08-18 2017-05-10 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种复合材料机翼蒙皮的加工方法及结构
US10195812B2 (en) 2015-08-26 2019-02-05 The Boeing Company Ply blending and stacking sequence
US10315783B2 (en) 2015-08-26 2019-06-11 The Boeing Company Ply blending and stacking sequence
US10380319B2 (en) * 2016-02-08 2019-08-13 The Boeing Company Sublaminate library generation for optimization of multi-panel composite parts
US10322792B2 (en) 2016-02-08 2019-06-18 The Boeing Company Ply optimization feasibility analysis for multi-layer composite parts
US10467350B2 (en) 2016-02-08 2019-11-05 The Boeing Company Optimization of ply orientations for multi-layer composite parts
JP6890431B2 (ja) * 2016-02-08 2021-06-18 ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ 多層複合部品のためのプライ最適化実行可能性分析
RU2694147C1 (ru) * 2016-04-06 2019-07-09 Сименс Акциенгезелльшафт Способ, считываемый компьютером носитель данных, компьютерная программа и симулятор для определения напряжений и отклонений форм в аддитивно изготавливаемой конструктивной структуре
US10919260B2 (en) * 2019-05-09 2021-02-16 The Boeing Company Composite structure having a variable gage and methods for forming a composite structure having a variable gage
US10913215B2 (en) * 2019-05-09 2021-02-09 The Boeing Company Composite structure having a variable gage and methods for forming a composite structure having a variable gage
US10919256B2 (en) * 2019-05-09 2021-02-16 The Boeing Company Composite structure having a variable gage and methods for forming a composite structure having a variable gage
CN110826284B (zh) * 2019-11-21 2021-04-16 北京航空航天大学 一种交织与层压混合铺层复合材料层压板建模及分析方法

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3887146T2 (de) * 1987-08-03 1994-05-05 Allied Signal Inc Flexible mehrschichtpanzerung.
GB8908507D0 (en) * 1989-04-14 1989-06-01 Fokker Aircraft Bv Method of and apparatus for non-destructive composite laminatecharacterisation
US5238725A (en) * 1990-12-21 1993-08-24 E. I. Du Pont De Nemours And Company Method for forming a structural panel with decorative facing and product thereof
US5984511A (en) * 1997-05-12 1999-11-16 Mcdonnell Douglas Corporation Knowledge driven composite design optimization process and system therefor
JP2000181950A (ja) 1998-11-19 2000-06-30 General Electric Co <Ge> 湾曲構造物から成るアセンブリの設計方法
JP2001104522A (ja) * 1999-10-04 2001-04-17 Mizuno Corp 繊維強化プラスチック製ゴルフシャフトの設計支援装置
FR2848492B1 (fr) * 2002-12-13 2006-12-29 Saint Gobain Vetrotex Procede et dispositif de fabrication d'une plaque composite
US7243055B2 (en) * 2004-01-28 2007-07-10 The Boeing Company Composite stacking sequence optimization for multi-zoned composites
US20060029807A1 (en) * 2004-08-04 2006-02-09 Peck Scott O Method for the design of laminated composite materials
EP1840775A1 (de) * 2006-03-31 2007-10-03 Airbus Espana, S.L. Computergestütztes Verfahren zum Erhalt eines Schichtmodells einer Verbundkomponente
US8181345B2 (en) * 2007-07-20 2012-05-22 Airbus Operations Sas Method for optimizing the mass of a composite panel

Also Published As

Publication number Publication date
EP2271479A1 (de) 2011-01-12
BRPI0910827A2 (pt) 2015-10-06
JP5401538B2 (ja) 2014-01-29
EP2271479B1 (de) 2011-11-02
JP2011518700A (ja) 2011-06-30
CN102015266B (zh) 2013-08-07
RU2491168C2 (ru) 2013-08-27
US20110004451A1 (en) 2011-01-06
CA2721874C (en) 2016-08-09
US8731870B2 (en) 2014-05-20
WO2009133382A1 (en) 2009-11-05
CN102015266A (zh) 2011-04-13
GB0807643D0 (en) 2008-06-04
RU2010146793A (ru) 2012-06-10
CA2721874A1 (en) 2009-11-05

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