Airbus Composite Fatigue And Damage Tolerance .
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACAIRBUS Composite fatigue &damagetolerance SessionsLouis RATIER– Chantal FUALDESSept 2015: FAA/BombardierComposite Transport DT &Maintenance WorkshopAirbus Composite Fatigueand Damage Tolerancecertification experiences.SEPT 2015
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015Composite Fatigue and damage tolerance Experience Long History of Compositetechnologies in PrimaryAirframe structureFleet experience , on Airbusprograms, show more than 200millions of Flight Hours now beencumulatedDesign & analysis & validationmethodology benefit of 50 years ofexperiences, since A300 to A380,Hundreds of large Subcomponents to full scaleComponents Tested AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.Good reliability & durabilityestablished that shouldbenefit to A350 Fatigue anddamage tolerance validation.
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015The challenge: Hybrid Fatigue Full scale Cells ?Current scenarios: Tests cells duplication schedule& cost impact Metal test scenarioComposite test scenarioFatigue sensitive features:Feature with out-of-plane stressesFatigue sensitive areas:all stress concentration areasShear and Tensile inter lamina strengthFatigue mainly driven by localtension loading R 0.1Compression: Mainly driven bycompression and alternativeloading R -1Scatter covered by Test Lifefactor : 2 3Scatter covered by LEF LoadEnhancement Factor: 1.17**from Northrop approachLEF 1LEF 1.17FC1DSG AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.2DSGFC1DSG
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015The challenge: Hybrid Fatigue Full scale Cells ?Adapted scenarios: Consolidate composite Fatigue sensitive feature,Converge on LEF (metal/composite) :Metal test scenarioComposite test scenarioFatigue sensitive features:Feature with out-of-plane stressesFatigue sensitive areas:all stress concentration areasShear and Tensile inter lamina strengthFatigue mainly driven by localtension loading R 0.1Compression: Mainly driven bycompression and alternativeloading R -1Scatter covered by Test Lifefactor : 2 3Scatter covered by LEF LoadEnhancement Factor: 1.17**from Northrop approachLEF 1LEF 1.17FC1DSG AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.2DSGFC1DSG
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015AIRBUS CERTIFICATION & TESTING EXPERIENCEOverall Approach for Fatigue & Damage Tolerance The principle : Large testing background capitalized on a buildingblock approach used to consolidate the fatigue insensitivethreshold of the material Comprehensive tests program developed forthe fatigue scattercharacteristic from keydesign/strength:Consolidate the fatigueinsensitivity thresholds,through coupon andelement testingvalidating the approachat higher levels whenrequiredArtificial damagesTest objectivesFullscaleBVID, on of fatiguesensitivity threshold forcomplex failure modesDetailElementCouponBVID: Barely Visible Impact DamageDedicated A350 tests developed AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.Validation of designprinciple at representativeload levelsEstablishing fatiguesensitivity threshold
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015AIRBUS CERTIFICATION & TESTING EXPERIENCECoupons to elements specimensGoal: Establish Suitability and Durability ofmaterials after repeated loading (as perCS25.603 & AC20.107B (8) b)How:Determine on selected feature failure mode& material : Damage onset and residual strength capability Variability in fatigue results (scatter characteristics) Environment effect (wet exposure) Relationship stress – life (SN curve and slope) Load sequence: spectrum / constant amplitudeloading effect No material degradation from repeatedloading was demonstrated. AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015LEF definition: Northrop’s analysisLoad Enhancement Factor has been introduced onfatigue composite full scale test as a response tothe higher scatter observed on fatigue compositetestsComposite standard approach:1986-Northrop’s report proposed a 2 parameters Weibulllaw analysis.Resulting from a large number of coupon tests,N11.5313.3LEF1.1771.1481.101Remarks : Test campaign with all failure mode (notfocused on sizing criteria) AIRBUS S.A.S. All rights reserved. Confidential and proprietary document. N LEF F N NF R LpgNn L RNF 1 L L ln( p) 2 (2n) / 2n 1 Lis the resulting life factor for LEF 1Weibull shape parameter for the scatter on residual strength propertiesWeibull shape parameter for the scatter on fatigue life propertiesSurvival probability (90% for the B-value definition)Confidence (95%)Coefficient applied on the life (N Life Factor when LEF 1)Number of test articles (usually one for a full-scale test)
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015LEF definition: Northrop’s analysis (con’t )Load Enhancement Factor has been introduced onfatigue composite full scale test as a response tothe higher scatter observed on fatigue compositetestsComposite standard approach:AIRBUS Applied LEF.Resulting from a large number of coupon tests,N11.5313.3LEF1.1771.1481.101Remarks : Test campaign with all failure mode (notfocused on sizing criteria) AIRBUS S.A.S. All rights reserved. Confidential and proprietary document. N LEF F N NF R LpgNn L RNF 1 L L ln( p) 2 (2n) / 2n 1 Lis the resulting life factor for LEF 1Weibull shape parameter for the scatter on residual strength propertiesWeibull shape parameter for the scatter on fatigue life propertiesSurvival probability (90% for the B-value definition)Confidence (95%)Coefficient applied on the life (N Life Factor when LEF 1)Number of test articles (usually one for a full-scale test)
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCACSEPT 2015ConclusionsExtensive works performed to understand Composite Fatigueperformance Current composite material show no fatigue degradation Fatigue Design sensitivity adress by Coupons to Element testspecimen Failure mode with higher LEF may-be accomplished at subcomponent test levelDemonstrator principle tests properly support durability , combiningimpact damage demonstration and no detrimental fatiguepropagation Potential to reduce testing at full scale level, using ‘conventional ‘metallic tests specimens AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
FAA/Bombardier Industry Composite Transport Damage Tolerance& Maintenance Workshop ESCAC AIRBUS S.A.S. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of AIRBUS S.A.S. No intellectual property rights are granted by thedelivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS S.A.S. This document and its content shall not beused for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supportinggrounds for these statements are not shown, AIRBUS S.A.S. will be pleased to explain the basis thereof.AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks. AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.SEPT 2015
The challenge: Hybrid Fatigue Full scale Cells ? Metal test scenario . Fatigue sensitive areas: all stress concentration areas Fatigue mainly driven by local tension loading R 0.1 Scatter covered by Test Life factor : 2 3 . Composite test scenario . Fatigue sensitive features: Feature with out-of-plane stresses
HL7538 Airbus A330-200 1998-07 HL7539 Airbus A330-200 1998-08 HL7552 Airbus A330-200 1999-02 HL8211 Airbus A330-200 2010-06 HL8212 Airbus A330-200 2010-08 HL8227 Airbus A330-200 2011-01 HL8228 Airbus A330-200 2011-01 HL8276 Airbus A330-200 2013-02 HL7550 Airbus A330-300 1997-01 HL7551 Airbus A330-300 1997-04
which are 10 Airbus A320-200, 4 Airbus A321-200, 7 Airbus A330-200 and 3 Airbus A330-300. In our package you ll find the modern fleet of an: Airbus A320-200 and Airbus A321-200. To select one of these aircraft go to „Select Aircraft“. From the list „Aircraft manufacturer“ choose the entry „AIRBUS BY AEROSOFT“. TheFile Size: 1MBPage Count: 35
Airbus Commercial Aircraft Specification / Nadcap commodity Cross Table issued Januar 25, 2021 Sorted by Airbus Specification Reference Foreword: This table is given for information only and shall not be considered as a reference. It is an help for establishing the link betweeen Airbus specifications and Nadcap commodities mandated by Airbus.
such as the Boeing 737-800 or Airbus A380. This is likely to lead to an overestimate in emissions as newer, more efficient planes are not represented. 0 200 400 600 800 1000 1200 0 2000 4000 6000 8000 10000 12000 Distance flown (km) kg CO 2 per seat Airbus A310 Airbus A320 Airbus A330 Airbus A340 Boeing737-400 Boeing 747-200 Boeing 747-400 .
structural components or structures. Consequently, fatigue of composite structures is of growing interest and leads industrials to develop accurate fatigue modeling, as well as a better prediction of delamination in laminates during fatigue loading. Since fatigue of metallic
Application of ASME Fatigue Code: 3-F.1 ASME Smooth Bar Fatigue Curves Alternative Effective Stress vs Fatigue Cycles (S-N Curve) With your weld quality level assessed and an accurate FEA stress number, one can use the ASME fatigue curve to calculate the number of Fatigue Cycles. In our prior example, the fatigue stress could be 25.5 ksi or as .
Types of composite: A) Based on curing mechanism: 1- Chemically activated composite 2- Light activated composite B) Based on size of filler particles: 1 - Conventional composite 2- Small particles composite 3-Micro filled composite 4- Hybrid composite 1- Chemically activated, composite resins: This is two - paste system:
initially created for the AST committee of API and later encouraged by the RBI committee of API. The initial scope was mainly tank floor thinning. The methodology was later extended to include a quantitative method for shell thinning, as well as susceptibility analysis (supplement analysis) for shell brittle fracture and cracking. Figure 2 shows a typical process plant hierarchy and the AST .
