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Failure and Damage Analysis of Aeronautical Composite Structures Aeronautical Composite Structures Prof. Dr. Volnei Tita [email protected] 1 November, 2010
Transcript of Failure and Damage Analysis of Aeronautical Composite ... · Failure and Damage Analysis of...
Failure and Damage Analysis of Aeronautical Composite StructuresAeronautical Composite Structures
Prof. Dr. Volnei Tita [email protected]
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November, 2010
ContentsContents
I USP/Sã C l d A ti l E i iI - USP/São Carlos and Aeronautical EngineeringAircraft Structures Group
II - Aeronautical StructuresStructures made from Composite Materials
Applications (Light Weight Structures)Failure Mechanisms and Challenges
III - Damage and Failure for Composite: Models and ApplicationsLaminate StructuresAdhesive JointsSandwich StructuresActive Fiber Composites
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Acknowledgements
I - USP/São Carlos A ti l E i iAeronautical Engineering
Aircraft Str ct res Gro pAircraft Structures Group
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Aeronautical EngineeringAeronautical Engineeringg gg g
History:History:
1973 Aeronautical activities beginning at the EESC/USP:Development of a general aviation aircraft, the IPAI-26 (“Tuca”)
beginning at the EESC/USP:
1983 Mechanical Engineering Major in Aeronautics
( Tuca ).
Major in Aeronautics begins at the EESC/USP:Average of 15 students per
2002 Aeronautical Engineering
year.
begins:40 students per year.
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Aircraft Structures GroupAircraft Structures GroupppMaterial Model
Load Cases (Flight and Ground)
Material ModelModel
Structural M d l I
Structural M d l II
(Flight and Ground)
Structural M d l III
Model
Model I Model II Model III
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Aircraft Structures GroupAircraft Structures Grouppp
Aeroelasticity Group
Structural Model III
e oe as c y G oup
Aeroelastic Models
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II - Aeronautical Structures (C it St t )(Composite Structures)
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Structures made from Composite MaterialsStructures made from Composite Materials
Glass fiber
Aluminium Carbon sandwich composites
Carbon composite laminates
Aluminium / steel / titanium
Materials used by weight
Composites Aluminium Titatium Steel Others
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[Boeing - 787]
Structures made from Composite MaterialsStructures made from Composite Materials
Concept Project: Metal x Composite
Aileron
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Structures made from Composite MaterialsStructures made from Composite Materials
S ifi Stiff dSpecific Stiffness and Strength
x Heterogeneity and
AnisotropyAnisotropy
Prevision of Failure M dModes
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Failure Mechanisms and ChallengesFailure Mechanisms and Challenges
InterInter‐‐ply failureply failureIntraIntra‐‐ply failureply failure
Pull-outFiber bridgingDebonding
How to predict the mechanical
behavior?
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DelaminationDebondingFiber rupture
behavior?
III - Damage and Failure for C it M d l d A li tiComposite: Models and Applications
Laminate StructuresAdhesive JointsAdhesive JointsSandwich StructuresActive Fiber Composites
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Laminate StructuresLaminate StructuresLaminate
-Orthotropic MaterialTransversal Isotropic
33Fiber
E11 = elasticity modulus in longitudinal direction;E = elasticity modulus in transversal direction(=E );
- Transversal Isotropic22
E22 = elasticity modulus in transversal direction(=E33);G12 = shear modulus in plane1-2 (=G13);
G23 = shear modulus in plane 2-3;ν = Poisson ratio at plane 1-2 (= ν );
Matrix
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ν12 = Poisson ratio at plane 1-2 (= ν13);ν23 = Poisson ratio at plane 2-3.11
Material Model: LaminateMaterial Model: LaminateFailure Mode Failure Criteria Degradation LawFailure Mode Failure Criteria Degradation Law
FiberFiberε−⎥
⎦
⎤⎢⎣
⎡⎟⎟⎠
⎞⎜⎜⎝
⎛−= BH
AAexpEE
o11
df11
( ) ( )( ) ( ) =α+
ασ+σ+⎟⎟
⎠
⎞⎜⎜⎝
⎛ σ .,e.i,eS3GS2
3G2X
2F4
1212212
41212
212
2
T
1
FiberFibertensiontension
⎦⎣ ⎠⎝ o
ε−⎥⎦
⎤⎢⎣
⎡⎟⎟⎠
⎞⎜⎜⎝
⎛−= BH
AAexpGG
o12
df12
( ) ( )
⎩⎨⎧
→≤→>
=+⎟⎟⎠
⎞⎜⎜⎝
⎛ σ
α+⎠⎝
damageno1edamage1e
eFF
X
S3GS2
F
F2F
2
1
2
T
1
121212T
FiberFiberCompressionCompression ⎩
⎨⎧
→≤→>
=⎟⎟⎠
⎞⎜⎜⎝
⎛ σdamageno1e
damage1ee
X F
F2F
2
C
1
0df12 →ν
0Edm22 →
2MatrixMatrixtensiontension
MatrixMatrix0Edf
22 →
⎧ →>⎤⎡ ⎞⎛⎞⎛ d1FY22
11dm11 EE →
⎩⎨⎧
→≤→>
=+⎟⎟⎠
⎞⎜⎜⎝
⎛ σdamageno1e
damage1ee
FF
Y M
M2M
2
12
T
2
Matrix Matrix compressioncompression ⎩
⎨⎧
→≤→>
=+σ
⎥⎥⎦
⎤
⎢⎢⎣
⎡−⎟⎟
⎠
⎞⎜⎜⎝
⎛+⎟⎟
⎠
⎞⎜⎜⎝
⎛ σdamageno1e
damage1ee
FF
Y1
S2Y
S2 M
M2M
2
1
C
2
23
C
23
2
0dm12 →ν
50
60
212
12
12
311
γσ+=
G
G20
30
40
Shea
r Stre
ss [M
Pa]
3126666126612 SS σ+σ=γ
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12
0,0 0,5 1,0 1,5 2,0 2,5 3,0 3,50
10
shear strain [%]
Identification ParametersIdentification Parameters
•Tensile
Experimental tests Computationalmodel
Ab•Compression•Shear •Bending
d Abaqus implicit subroutines
Modelparameters
Abaqus
•Mode I•Mode II•Mix Mode•Hopkinson’sbar
Abaqus implicit subroutinesfor plane and curved geometryUELUMAT•Hopkinson s bar
Abaqusexplicit subroutines for plane and curved geometryVUELVUMAT•4 point Bending
•Indentation on planeand curvedplane and curved specimens•Impact on plane and curved
Modelevaluation
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specimens
Experimental Experimental TestsTestsppO MIB, Instituto de Materiais Tecnológicos do Brasil Ltda., é uma empresa , g , p
privada, prestadora de serviços em projetos de P&D, consultoria em Fundição e execução de ensaios, na área de Ciência e Engenharia de
M t i i M táli C ó itMateriais Metálicos e Compósitos.
Fone – 3376-1863E mail info@mib eng br
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E-mail – [email protected] - www.mib.eng.br
Results Results –– Impact TestImpact Testpp
K th li k U i it it L Impact TestKatholieke Universiteit Leuven (Belgium)
3500
4000
Impact TestExponential Contact Law: (Co=10-4, Po=102) - with NLGEOM
Elastic Model Shell Model - (δ=0,05 - H=0,05)
SupportSupport 2000
2500
3000
F[N
]
Load Cell
LED
dartLoad CellLoad Cell
LEDLED
dart1000
1500 Ei = 5,91 J
Optic SensorOptic Sensor
0 1 2 3 40
500
time[ms]
[+45/-45/+45/0/90]s
SpecimenSpecimen
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Application: UAVApplication: UAVppppComposite Spar Failure AnalysisComposite Spar - Failure Analysis
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Application: Pressure Vessel and Application: Pressure Vessel and DuctesDuctespppp
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Application: Beam FloorApplication: Beam Floorpppp
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III - Damage and Failure for C it M d l d A li tiComposite: Models and Applications
Laminate StructuresAdhesive JointsAdhesive JointsSandwich StructuresActive Fiber Composites
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Adhesive Joints Adhesive Joints -- MotivationMotivation
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Adhesive JointsAdhesive Joints
Failure Mechanisms: Adhesive and AdherentFailure Mechanisms: Adhesive and Adherent
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System Analysis of Joints (SAJSystem Analysis of Joints (SAJTMTM))
S t A l i f J i t (SAJ)
y y (y y ( ))
System Analysis of Joints (SAJ)(software developed by GEA)
Adherent 2
Adherent 1
Adhesive
Adherent 1
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Results: Results: σσzz ee ττzxzx field for composite jointsfield for composite joints
Single Lap Joint σz and τzx.
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Application: Structure RepairApplication: Structure Repairpp ppp p
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III - Damage and Failure for C it M d l d A li tiComposite: Models and Applications
Laminate StructuresJoints: Adhesive and FastenersJoints: Adhesive and FastenersSandwich StructuresActive Fiber Composites
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Sandwich StructuresSandwich Structures
2(3)
1
2(3)
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Material Model: FoamMaterial Model: FoamCrushable FoamCrushable Foam
Yeld Surface
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Application: FuselageApplication: Fuselagepp gpp g
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III - Damage and Failure for C it M d l d A li tiComposite: Models and Applications
Laminate StructuresJoints: Adhesive and FastenersJoints: Adhesive and FastenersSandwich StructuresActive Fiber Composites
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Piezoelectric Composites Piezoelectric Composites -- MotivationMotivationpp
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Piezoelectric CompositesPiezoelectric Compositespp
Schemas to create electrical fieldSecondary Effect
Schemas to create electrical field
Primary Effect
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FEMFEM ModelsModelsFEM FEM ModelsModels
( ) d (d) d th t d d i it id t l t i t(c) and (d) are necessary due the symmetry needed in opposite sides to apply constraint eqs
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Application: Sensor / ActuatorApplication: Sensor / Actuator
Experimental evaluation of a fuzzy control for vibration reduction beam
pppp
Experimental evaluation of a fuzzy control for vibration reduction beam with piezoelectric patch (Aeronautical Engineering - USP)
uF(t)
u(t)
time [s]
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AcknowlegmentsAcknowlegmentsgg
GEA would like to thank FAPESP, CAPES and CNPq for the financialfunds to develop the researches.
Research Collaboration:Partners: Research Collaboration:
Katholieke Universiteit Leuven, BelgiumLMT Cachan France
FAB (Brazil – Air Force) CTM (Brazil – Navy) LMT-Cachan, France
Chemistry Institute of São Carlos, BrazilCarleton University, CanadaU i it f Li l UK
C ( a a y)US – Air Force and US – ArmyAir BusEMBRAER University of Liverpool, UK
Virginia Tech, USAEMBRAERTAM – Air LinesAeroalcool
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Thank you very much Thank you very much f tt tif tt tifor your attentionfor your attention
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