Fiber / Toughened Epoxy Composites under
|
|
- Beatrix Osborne
- 5 years ago
- Views:
Transcription
1 Fatigue Behavior o Impact-Damaged Carbon Fiber / Toughened Epoxy Composites under Compressive loading Toshio Ogasawara, Hisaya Katoh, unao ugimoto, and Takashi Ishikawa Advanced d Composite Technology Center (ACE-TeC) C) Japan Aerospace Exploration Agency (JAXA) Tokyo Japan CDW-15 (15th Composites Durability Workshop) October 17-19, 21, Kanazawa, Japan
2 Outline Introduction Experimental procedure Materials Compression ater impact (CAI) and atigue testing Results and discussion tatic strength Fatigue lie (-N curves) Rough estimation o atigue lietime distribution ib ti o an impact-damaged specimen CAI atigue lietime prediction Conclusion
3 Background Fatigue behavior o impact-damaged carbon iber composite (CFRP) laminates has been studied since the late 197s. The atigue data o early CFRP materials were published in ATM-TP, NAA reports, and other reports o the literature.
4 Fatigue behaviors o impact-damaged carbon iber composites (CMH-17-3G, Vol. 3, Chapter 12.7) p The endurance limit at 1 6 cycles turned out as between 5 and 75% o the initial strength. Damage growth starts very close to the end o the specimen lietime -N curves or the IM7/977-2 and the T8H/F material Damage growth as measured using C-CAN, versus atigue cycles or the T8H/ F655-2 material The ratio between the endurance limit at 1 6 cycles, and the initial static strength turned out as between.5 and.75. Thereore, sizing a structure (with these materials) using Ultimate Loads is expected to push atigue loads down to a level that is likely to limit atigue problems with low energy impact damage. Unrealistic atigue stress (greater than 75% o the static strength) was necessary to produce such measurements. This igure shows that, despite the log axis, damage growth starts very close to the end o the specimen lietime (between 85% and 95% or all cases investigated in this program), with a very high slope.
5 Background Damage growth under cyclic compressive loading is extremely sensitive to stress, and it starts very close to the end o the specimen lietime. A conventional damage tolerance methodology or aluminum alloys is not applicable or CFRP. No damage growth (allowable stress design) is becoming the most common concept or designing composite structures. For this methodology, atigue strength o composite laminates which have barely visible impact damage (BVID) is important to determine the allowable stress. BVID: The minimum impact damage surely detectable by scheduled inspection
6 Objectives Experimental results that clariy the atigue lietime distribution o impact-damaged CFRP laminates have not been published because they are sensitive or material suppliers as well as aircrat companies. tatistical methods or predicting CAI atigue lietime have not been understood suiciently. The objective o this study is to obtain the atigue lietime data o impact-damaged d carbon iber composites under compressive loading to elucidate the lietime prediction methodology based on statistical approaches.
7 Experimental procedures Materials Carbon iber / toughened epoxy composites Toray T8/39-2B Quasi-isotropic laminates [45//-45/9]4s (32 ply) (Elastic modulus 49.2 GPa) Low-speed Impact loading (in accordance with ATM D7136) Drop weight type impact tester pecimen geometry 1 mm width, 15 mm length 6 mm thickness Drop weight Weight 5.5 kg, Radius 5/8 inch Impact energy 6.7 J/mm Low speed Impact
8 Experimental procedure Compression ater impact (CAI) testing (ATM D7137) Test ixture ATM D7137 Electromechanical testing system (25 kn, 5885; Instron Corp.) Number o samples: 9 CAI atigue testing ervo-hydraulic testing system (5 kn, 884; Instron Corp.) Test ixture ATM D7137 ide: simple support Top & bottom: ixed support tress ratio R = σ mim / σ max=1 Frequency = 3 Hz inusoidal wave Run-out 1 7 Number o samples > 36
9 CAI strength distribution (Weibull plot) -F)) ln (-ln ( CAI strength (ATM D7137) CAI (m=17.5) Average 272MPa (.55%) CV 5.4% m=17.5 NHC (m=53.2) NHC strength (ATM D6144) Average 583 MPa (1.18%) 18%) CV 1.8 % m= trength (MPa) F ( ) = 1 exp( ( / ) m ) The Weibull shape parameter (m) or CAI strength is much lower than that or NHC strengths. th This result seems to derive rom the variation in impact damage size.
10 -N curves (peak compressive stress vs. atigue lie) Pea ak stress s (MPa) Impact 6.7 J/m R = 1 = 3 Hz CAI strength (average 272 MPa) 73% o CAI strength (2 MPa) Number o cycles to ailure pecimen ailed at ( σ min = 22 MPa ) cycles CAI atigue lietime exhibits relatively lat -N curves and considerable scattering. Fatigue ailures occurred at the 73% o CAI strength, which agrees with the data ound in some literatures.
11 Fatigue lie distribution (Weibull plot) ln (-ln (1-F F)) MPa M =.6 22 MPa tress (MPa) 21 MPa Weibull parameters M N Number o samples Impact t67j/ 6.7 J/m F ( N ) = 1 exp( ( N / N ) M ) Number o cycles to ailure Weibull plots showing atigue lietime distribution or 21, 22, and 23 MPa are shown here. The Weibull shape parameters (M) are apparently independent o the stress.
12 Evaluation o damage growth using ultrasonic C-scan CAI-B-4 (σ min = 22 MPa, R=1, = 3 Hz, atigue lie ) cycle 1 5 cycles 1 6 cycles Damage growth is not clearly visible until 1 6 cycles, even though the lietime was However, the pulse-echo intensity rom damage increases with the number o cycles.
13 Observations o damage growth using digital video recording CAI-A-4 (σ min = 2 MPa, R=1, = 3 Hz, atigue lie ) 15 cycles (no growth) 1 cycles 3 cycles Final ailure ( Cycles) Damage growth to transverse direction was observed very close to the end o the specimen lietime (1-15 cycles beore the inal ailure ( )). Until then, no visible damage growth was observed.
14 Rough estimation o atigue lietime distribution o an impact-damaged specimen (1) We made two assumptions The mode-ratio (G II /G I, G III /G I ) at the critical point o a damage is independent o damage growth during a atigue test. tress redistribution attributable to damage growth is ignored. Based on dimensional analysis, the energy release rate G is roughly approximated by the ollowing relation. G 2 : Compressive stress (=P/A) a (1) a : Representative damage size Then strength o the impact-damaged specimen,, is given as G / a (2) c G c is a mixed mode racture toughness (see appendix). a
15 Rough estimation o atigue lietime distribution o an impact-damaged specimen (2) Paris law is applied or damage growth under cyclic compressive loading. da / dn Δ ) Δ = ( 1 1/ R ) n / 2 n ( Δ G ) = ( Δ a (3) Integrating Eq. (3) rom the initial damage size a to the inal size a, the atigue lie N under a constant stress amplitude Δ is given as n 2 N = Q /( Δ) n (4) For these calculations, l a -n <<a -n is assumed because n > 1. Q is a atigue parameter which depends on the material properties, damage geometries, damage size, specimen geometries, loading constraint, etc. CAI strength ( ) distribution is given as, F ( ) = 1 exp( ( / ) m ) (5) ubstituting Eq.(4) into Eq. (5) yields the atigue lie distribution unction. F ( N M M ) = 1 exp( ( N / N ) ) (6) = m /( n 2) n 2 n N = ( Q ) /( Δ)
16 Rough estimation o atigue lietime distribution o an impact-damaged specimen (3) This equation shows that two methods can be used to determine the damage growth exponent (n). A) Weibull shape parameters m ( CAI strength) and M (CAI atigue) F B) Weibull scale parameters (N ) and compressive stress () ( N ) = 1 exp( ( N / N ) M = m /( n 2) n 2 n N = ( Q ) /( Δ) Method A M m = 17.5 M =.6 (=21, 22 MPa) M ) = m /(nn 2) n=31 (6) Method B Pe ak stress (M MPa) n 2 n N = ( α ) /( Δ) Δ = ( 1 1/ R) 3 n= Weibull scale parameter, N
17 Typical exponent value in delamination growth rate reported in literatures Detailed investigations using DCB and ENF methods in literatures revealed delamination growth behaviors o carbon iber composites. Exponent values in delamination growth rate are reportedly between 2 and 5. n = 2 n = 32 M. Hojo et al., Comp. ci. Technol., 29 (1987), J. chön et al., Comp. ci. Technol., 6 (2),
18 CAI atigue lietime prediction Pea ak stress s (MPa) Mean 3 F= F=.1 B-basis value Impact 6.7 J/m R = 1 = 3Hz tatic strength 272 MPa Fatigue strength Lietime F=1% B-value* 1X 1 6 1X MPa 167 MPa (67 %) (61 %) 17 MPa (63 %) 155 MPa (57 %) * Number o samples 9 Number o cycles to ailure Fatigue lietime is predicted or ailure probability (F) o 1 %, 5 %, and 9%. Numerical results agree with the experimental data. The ratio between the endurance limit (B-value) at 1 6 cycles and the initial static strength was estimated as 61%. B-Basis value At least 9% o the population o material values is expected to equal or exceed this tolerance bound with 95% conidence.
19 Conclusion Fatigue lietime data o impact-damaged carbon iber / epoxy composites (Impact energy 6.7 J/mm) were obtained. The CAI strength and atigue lietime exhibit considerable scattering. A simple statistical model was proposed p or predicting the lietime o impact-damaged CFRP laminates. In spite o rough approximation, the estimates agreed with the experimental results. The ratio between the endurance limit (B-value) at 1 6 cycles and the initial static strength was estimated as 61%. In uture the eect o stress ratio on CAI atigue behaviors In uture, the eect o stress ratio on CAI atigue behaviors will be investigated.
20 Appendix Mixed mode racture toughness Gc A mixed mode ailure criterion is assumed as ollows. GI GII GIII (1) G G G IC IIC IIIC The energy release rate o each mode (i = I, II, II) is given as a G i = κ (2) 2 i a κ i : constant (i =, I, II, III) Failure stress is assumed to be given as the ollowing equation. 2 κ a G c (3) ubstituting Eq.(2) into Eq. (1), a mixed mode racture toughness Gc is obtained as G c 1 κ I κ II κ III = κ + + (4) G IC G IIC G IIIC
FATIGUE DURABILITY OF CONCRETE EXTERNALLY STRENGTHENED WITH FRP SHEETS
FATIGUE DURABILITY OF CONCRETE EXTERNALLY STRENGTHENED WITH FRP SHEETS H. Diab () and Zhishen Wu () () Department o Urban and Civil Engineering, Ibaraki University, Japan Abstract A primary concern o the
More informationPREDICTION OF OPEN HOLE COMPRESSIVE FAILURE FOR QUASI-ISOTROPIC CFRP LAMINATES BY MMF/ATM METHOD
HE 19 H INERNAIONAL CONFERENCE ON COMPOSIE MAERIALS PREDICION OF OPEN HOLE COMPRESSIVE FAILURE FOR QUASI-ISOROPIC CFRP LAMINAES BY MMF/AM MEHOD. Hioki 1*, M. Nakada 2, Y. Miyano 2, H. Katoh 3 1 Graduate
More informationLong-term Life Prediction of CFRP Structures Based on MMF/ATM Method
The 5 th Coposites Durability Workshop (CDW-5, October 7 to 20, 200, Kanazawa Institute o Technology Long-ter Lie Prediction o CFRP Structures Based on MMF/ATM Method by Yasushi Miyano and Masayuki Nakada
More informationDAMAGE SIMULATION OF CFRP LAMINATES UNDER HIGH VELOCITY PROJECTILE IMPACT
18 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS DAMAGE SIMULATION OF CFRP LAMINATES UNDER HIGH VELOCITY PROJECTILE IMPACT A. Yoshimura 1*, T. Okabe, M. Yamada 3, T. Ogasawara 1, Y. Tanabe 3 1 Advanced
More informationEFFECT OF ALTERNATE CHANGE IN STRESS RATIO ON FATIGUE STRENGTH OF WOVEN FABRIC CFRP LAMINATE AND LIFE PREDICTION USING THE ANISOMORPHIC CFL DIAGRAM
EFFECT OF ALTERNATE CHANGE IN STRESS RATIO ON FATIGUE STRENGTH OF WOVEN FABRIC CFRP LAMINATE AND LIFE PREDICTION USING THE ANISOMORPHIC CFL DIAGRAM M. Kawai a*, K. Yang a, S. Oh a a Department of Engineering
More informationAccelerated Testing Methodology for Long Term Durability of CFRP
IFREMER-ONR Workshop on Durability of Composites in a Marine Environment August 23 24, 22 IFREMER Centre, Nantes, France Accelerated esting Methodology for Long erm Durability of CFRP Masayuki Nakada*,
More informationMICROMECHANICAL FAILURE ANALYSIS OF UNIDIRECTIONAL FIBER-REINFORCED COMPOSITES UNDER IN-PLANE AND TRANSVERSE SHEAR
THE 19 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS MICROMECHANICAL FAILURE ANALYSIS OF UNIDIRECTIONAL FIBER-REINFORCED COMPOSITES UNDER IN-PLANE AND TRANSVERSE SHEAR Lei Yang*, Ying Yan, Zhiguo
More informationEffect of damage on performance of composite structures applications to static and fatigue strength predictions. Christos Kassapoglou
Effect of damage on performance of composite structures applications to static and fatigue strength predictions Christos Kassapoglou Outline static open hole BVID fatigue constant amplitude B-Basis curve
More informationA 3D Discrete Damage Modeling Methodology for Abaqus for Fatigue Damage Evaluation in Bolted Composite Joints
A 3D Discrete Damage Modeling Methodology for Abaqus for Fatigue Damage Evaluation in Bolted Composite Joints Eugene Fang 1, Ling Liu 1, Michael Stuebner 1, Jim Lua 1 1 Global Engineering and Materials,
More informationInterlaminar fracture characterization in composite materials by using acoustic emission
5th International Symposium on NDT in Aerospace, 13-15th November 2013, Singapore Interlaminar fracture characterization in composite materials by using acoustic emission Ian SILVERSIDES 1, Ahmed MASLOUHI
More informationA STUDY OF 0 -FIBRE MICROBUCKLING IN MULTIDIRECTIONAL COMPOSITE LAMINATES
A STUDY OF -FIBRE MICROBUCKLING IN MULTIDIRECTIONAL COMPOSITE LAMINATES P. Berbinau and C. Soutis Department o Aeronautics, Imperial College o Science, Technology & Medicine Prince Consort Rd, London SW7
More informationTensile behaviour of anti-symmetric CFRP composite
Available online at www.sciencedirect.com Procedia Engineering 1 (211) 1865 187 ICM11 Tensile behaviour of anti-symmetric CFRP composite K. J. Wong a,b, *, X. J. Gong a, S. Aivazzadeh a, M. N. Tamin b
More informationExample 1. Stress amplitude (MPa) 130 1x10 7 (no failure)
Example 1 For the ollowing R=-1 AISI 1090 steel test data, plot two S-N curves, one using loglinear coordinates and the other using log-log coordinates. a) Use linear regression to estimate the best it
More informationExperimentally Calibrating Cohesive Zone Models for Structural Automotive Adhesives
Experimentally Calibrating Cohesive Zone Models for Structural Automotive Adhesives Mark Oliver October 19, 2016 Adhesives and Sealants Council Fall Convention contact@veryst.com www.veryst.com Outline
More informationBIAXIAL STRENGTH INVESTIGATION OF CFRP COMPOSITE LAMINATES BY USING CRUCIFORM SPECIMENS
BIAXIAL STRENGTH INVESTIGATION OF CFRP COMPOSITE LAMINATES BY USING CRUCIFORM SPECIMENS H. Kumazawa and T. Takatoya Airframes and Structures Group, Japan Aerospace Exploration Agency 6-13-1, Ohsawa, Mitaka,
More informationSTRENGTH DEGRADATION MODEL FOR FATIGUE LIFE PREDICTION
16 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS STRENGTH DEGRADATION MODEL FOR FATIGUE LIFE PREDICTION Hiroshige Kikukawa: kikukawa@neptune.kanazawa-it.ac.jp Department of Aeronautics, Kanazawa Institute
More informationLife Prediction Under Multiaxial Fatigue
Lie Prediction Under Multiaxial Fatigue D. Ramesh and M.M. Mayuram Department o Mechanical Engineering Indian Institute o Technology, Madras Chennai-600 036 (India) e-mail: mayuram@iitm.ac.in ABSTRACT
More informationEffects of Resin and Fabric Structure
Fatigue of Wind Blade Laminates: Effects of Resin and Fabric Structure Details David Miller, Daniel D. Samborsky and John F. Mandell Montana State t University it MCARE 2012 Outline Overview of MSU Fatigue
More informationCHARACTERIZATION, ANALYSIS AND PREDICTION OF DELAMINATION IN COMPOSITES USING FRACTURE MECHANICS
Oral Reference Number: ICF100942OR CHARACTERIZATION, ANALYSIS AND PREDICTION OF DELAMINATION IN COMPOSITES USING FRACTURE MECHANICS T. Kevin O Brien U.S. Army Research Laboratory Vehicle Technology Directorate
More informationCOMPRESSIVE BEHAVIOR OF IMPACT DAMAGED COMPOSITE LAMINATES
16 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS COMPRESSIVE BEHAVIOR OF IMPACT DAMAGED COMPOSITE LAMINATES Hiroshi Suemasu*, Wataru Sasaki**, Yuuichiro Aoki***, Takashi Ishikawa**** *Department of
More informationBayesian Technique for Reducing Uncertainty in Fatigue Failure Model
9IDM- Bayesian Technique or Reducing Uncertainty in Fatigue Failure Model Sriram Pattabhiraman and Nam H. Kim University o Florida, Gainesville, FL, 36 Copyright 8 SAE International ABSTRACT In this paper,
More informationManufacturing Remaining Stresses in Truck Frame Rail's Fatigue Life Prediction
Manuacturing Remaining Stresses in Truck Frame Rail's Fatigue Lie Prediction Claudiomar C. Cunha & Carlos A. N. Dias MSX International & Department o Naval Engineering EPUSP/USP/Brazil Department o Mechanical
More informationNUMERICAL INVESTIGATION OF DELAMINATION IN L-SHAPED CROSS-PLY COMPOSITE BRACKET
NUMERICAL INVESTIGATION OF DELAMINATION IN L-SHAPED CROSS-PLY COMPOSITE BRACKET M.Gümüş a*, B.Gözlüklü a, D.Çöker a a Department of Aerospace Eng., METU, Ankara, Turkey *mert.gumus@metu.edu.tr Keywords:
More informationFRACTURE TOUGHNESS OF ADHESIVE BONDED COMPOSITE JOINTS UNDER MIXED MODE LOADING.
FRACTURE TOUGHNESS OF ADHESIVE BONDED COMPOSITE JOINTS UNDER MIXED MODE LOADING. X. J. Gong, F. Hernandez, G. Verchery. ISAT - Institut Supérieur de l Automobile et des Transports, LRMA - Laboratoire de
More informationChapter 6 Reliability-based design and code developments
Chapter 6 Reliability-based design and code developments 6. General Reliability technology has become a powerul tool or the design engineer and is widely employed in practice. Structural reliability analysis
More informationStress concentrations, fracture and fatigue
Stress concentrations, fracture and fatigue Piet Schreurs Department of Mechanical Engineering Eindhoven University of Technology http://www.mate.tue.nl/ piet December 1, 2016 Overview Stress concentrations
More informationDAMAGE MECHANICS MODEL FOR OFF-AXIS FATIGUE BEHAVIOR OF UNIDIRECTIONAL CARBON FIBER-REINFORCED COMPOSITES AT ROOM AND HIGH TEMPERATURES
DAMAGE MECHANICS MODEL FOR OFF-AXIS FATIGUE BEHAVIOR OF UNIDIRECTIONAL CARBON FIBER-REINFORCED COMPOSITES AT ROOM AND HIGH TEMPERATURES M. Kawai Institute of Engineering Mechanics University of Tsukuba,
More informationPrediction of The Ultimate Strength of Composite Laminates Under In-Plane Loading Using A Probabilistic Approach
Prediction of the Ultimate Strength of Composite Laminates Under In-Plane Loading Prediction of The Ultimate Strength of Composite Laminates Under In-Plane Loading Using A Probabilistic Approach Tae Jin
More informationCOMPARISON OF COHESIVE ZONE MODELS USED TO PREDICT DELAMINATION INITIATED FROM FREE-EDGES : VALIDATION AGAINST EXPERIMENTAL RESULTS
COMPARISON OF COHESIVE ZONE MODELS USED TO PREDICT DELAMINATION INITIATED FROM FREE-EDGES : VALIDATION AGAINST EXPERIMENTAL RESULTS A. Uguen 1, L. Zubillaga 2, A. Turon 3, N. Carrère 1 1 Laboratoire Brestois
More informationImpact and Crash Modeling of Composite Structures: A Challenge for Damage Mechanics
Impact and Crash Modeling of Composite Structures: A Challenge for Damage Mechanics Dr. A. Johnson DLR Dr. A. K. Pickett ESI GmbH EURO-PAM 99 Impact and Crash Modelling of Composite Structures: A Challenge
More informationIJSER 1. INTRODUCTION. M.Elhadary
1591 A new failure criterion for GRP composite materials subjected to in-phase and out-of-phase biaxial fatigue loading under different stress ratios M.Elhadary Abstract this studying the fatigue behavior
More informationDetermination of fiber/matrix interface debond growth parameters from cyclic loading of single fiber composites
Deterination o iber/atrix interace debond growth paraeters ro cyclic loading o single iber coposites Andrejs Pupurs 1,, Janis Varna 1, Povl Brøndsted 3, Stergios Goutianos 3 1 Luleå University o Technology,
More informationPrediction of Delamination Growth Behavior in a Carbon Fiber Composite Laminate Subjected to Constant Amplitude Compression-Compression Fatigue Loads
Prediction of Delamination Growth Behavior in a Carbon Fiber Composite Laminate Subjected to Constant Amplitude Compression-Compression Fatigue Loads J. Raju 1*, D.S. Sreedhar 2, & C.M. Manjunatha 1 1
More informationAXIALLY LOADED FRP CONFINED REINFORCED CONCRETE CROSS-SECTIONS
AXIALLY LOADED FRP CONFINED REINFORCED CONCRETE CROSS-SECTIONS Bernát Csuka Budapest University o Technology and Economics Department o Mechanics Materials and Structures Supervisor: László P. Kollár 1.
More informationAPPLICATION OF A CONDITIONAL EXPECTATION RESPONSE SURFACE APPROACH TO PROBABILISTIC FATIGUE
9 th ASCE Specialty Conerence on Probabilistic Mechanics and Structural Reliability APPLICATION OF A CONDITIONAL EXPECTATION RESPONSE SURFACE APPROACH TO PROBABILISTIC FATIGUE Abstract F.N. Momin, H.R.
More informationBond strength model for interfaces between nearsurface mounted (NSM) CFRP strips and concrete
University o Wollongong Research Online Faculty o Engineering and Inormation Sciences - Papers: Part A Faculty o Engineering and Inormation Sciences 2014 Bond strength model or interaces between nearsurace
More informationDetermination of Dynamic Fracture Toughness Using Strain Measurement
Key Engineering Materials Vols. 61-63 (4) pp. 313-318 online at http://www.scientific.net (4) Trans Tech Publications, Switzerland Online available since 4/4/15 Determination of Dynamic Fracture Toughness
More informationFRACTURE BEHAVIOR OF CFRP LAMINATE UNDER ARTIFICIAL LIGHTNING STRIKE
FRACTURE BEHAVIOR OF CFRP LAMINATE UNDER ARTIFICIAL LIGHTNING STRIKE Yoshiyasu Hirano 1, Singo Katsumata 2, Yutaka Iwahori 1, Hirooshi Hatta 1, and Akira Todoroki 3 1 Advanced Composite Technology Center,
More informationRUNWAY DEBRIS IMPACT ON GENERIC COMPOSITE TURBOFAN BLADE MULTISCALE PROGRESSIVE FAILURE ANALYSIS
RUNWAY DEBRIS IMPACT ON GENERIC COMPOSITE TURBOFAN BLADE MULTISCALE PROGRESSIVE FAILURE ANALYSIS Gong Huiling 1 Frank Abdi 2 Marc VillàMontero 2 Cody Godines 2 1 MVT Group Inc, Shanghai, China 2 Alpha
More informationApplication of Mathematica Software for Estimate the Fatigue Life Time Duration of Mechanical System
ANALELE UNIVERSITĂłII EFTIMIE MURGU REŞIłA ANUL XVII, NR. 2, 2010, ISSN 1453-7397 Petru Florin Minda, Ana Maria Budai Application o Mathematica Sotware or Estimate the Fatigue Lie Time Duration o Mechanical
More informationInitiation de fissure dans les milieux fragiles - Prise en compte des contraintes résiduelles
Initiation de fissure dans les milieux fragiles - Prise en compte des contraintes résiduelles D. Leguillon Institut Jean le Rond d Alembert CNRS/UPMC Paris, France Parvizi, Garrett and Bailey experiments
More informationFatigue verification of high loaded bolts of a rocket combustion chamber.
Fatigue veriication o high loaded bolts o a rocket combustion chamber. Marcus Lehmann 1 & Dieter Hummel 1 1 Airbus Deence and Space, Munich Zusammenassung Rocket engines withstand intense thermal and structural
More informationAnalytical Study on Low Compressive Strength of Composite Laminates with Impact Damage
Analytical Stuy on Low Compressive Strength of Composite Laminates with Impact Damage Hiroshi Suemasu, Makoto Ichiki, Grauate Stuent, an Yuichiro Aoki, JAXA UK-Japan Workshop, Bristol, March 4-7, 03 /7
More informationON AN ESTIMATION OF THE DAMPING PROPERTIES OF WOVEN FABRIC COMPOSITES
ON AN ESTIMATION OF THE DAMPING PROPERTIES OF WOVEN FABRIC COMPOSITES Masaru Zao 1, Tetsusei Kurashii 1, Yasumasa Naanishi 2 and Kin ya Matsumoto 2 1 Department o Management o Industry and Technology,
More information6.4 A cylindrical specimen of a titanium alloy having an elastic modulus of 107 GPa ( psi) and
6.4 A cylindrical specimen of a titanium alloy having an elastic modulus of 107 GPa (15.5 10 6 psi) and an original diameter of 3.8 mm (0.15 in.) will experience only elastic deformation when a tensile
More informationFASTENER PULL-THROUGH FAILURE IN GFRP LAMINATES
18 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS FASTENER PULL-THROUGH FAILURE IN GFRP LAMINATES G. Catalanotti 1*, P.P. Camanho 1, P. Ghys 2, A.T. Marques 1 1 DEMec, Faculdade de Engenharia, Universidade
More informationDESIGNING A FLEXIBLE BELLOWS COUPLING MADE FROM COMPOSITE MATERIALS USING NUMERICAL SIMULATIONS SVOČ FST 2018
DESIGNING A FLEXIBLE BELLOWS COUPLING MADE FROM COMPOSITE MATERIALS USING NUMERICAL SIMULATIONS SVOČ FST 2018 Ing. Frantisek Sedlacek, University of West Bohemia, Univerzitni 8, 306 14, Pilsen, Czech Republic
More informationPrüfmethoden zur Charakterisierung von Verbundwerkstoffen
Prüfmethoden zur Charakterisierung von Verbundwerkstoffen Gerald Pinter 1), Markus Wolfahrt 2) 1) Institut für Werkstoffkunde und Prüfung der Kunststoffe Montanuniversität Leoben, A 2) Polymer Competence
More informationIMPACT ON LAMINATED COMPOSITE PLATES: COMPARISON OF TEST AND SIMULATION RESULTS OBTAINED WITH LMS SAMTECH SAMCEF
V ECCOMAS Thematic Conference on the Mechanical Response of Composites COMPOSITES 015 S.R. Hallett and J.J.C. Remmers (Editors) IMPACT ON LAMINATED COMPOSITE PLATES: COMPARISON OF TEST AND SIMULATION RESULTS
More informationFracture Behavior. Section
Section 6 Fracture Behavior In January 1943 the one-day old Liberty Ship, SS Schenectady, had just completed successful sea trials and returned to harbor in calm cool weather when... "Without warning and
More informationMATERIALS FOR CIVIL AND CONSTRUCTION ENGINEERS
MATERIALS FOR CIVIL AND CONSTRUCTION ENGINEERS 3 rd Edition Michael S. Mamlouk Arizona State University John P. Zaniewski West Virginia University Solution Manual FOREWORD This solution manual includes
More informationA fatigue design methodology for GRP composites in offshore underwater applications
A fatigue design methodology for GRP composites in offshore underwater applications Dr P. A. FRIEZE P A F A Consulting Engineers Limited, Hampton, Middx, UK INTRODUCTION Norsk Hydro Troll C field - floating
More informationDurability of bonded aircraft structure. AMTAS Fall 2016 meeting October 27 th 2016 Seattle, WA
Durability of bonded aircraft structure AMTAS Fall 216 meeting October 27 th 216 Seattle, WA Durability of Bonded Aircraft Structure Motivation and Key Issues: Adhesive bonding is a key path towards reduced
More information9 Strength Theories of Lamina
9 trength Theories of Lamina 9- TRENGTH O ORTHOTROPIC LAMINA or isotropic materials the simplest method to predict failure is to compare the applied stresses to the strengths or some other allowable stresses.
More informationExamination in Damage Mechanics and Life Analysis (TMHL61) LiTH Part 1
Part 1 1. (1p) Define the Kronecker delta and explain its use. The Kronecker delta δ ij is defined as δ ij = 0 if i j 1 if i = j and it is used in tensor equations to include (δ ij = 1) or "sort out" (δ
More informationTensile Stress Acoustic Constants of Unidirectional Graphite/Epoxy Composites
Tensile Stress Acoustic Constants of Unidirectional Graphite/Epoxy Composites Journal of Reinforced Plastics and Composites, Vol. 9 (March, 1990) pp. 127-133 W. H. PROSSER NASA Langley Research Center
More informationAn Acoustic Emission Approach to Assess Remaining Useful Life of Aging Structures under Fatigue Loading
An Acoustic Emission Approach to Assess Remaining Useful Life of Aging Structures under Fatigue Loading Mohammad Modarres Presented at the 4th Multifunctional Materials for Defense Workshop 28 August-1
More informationN o n l i n e a r M u l t i - S c a l e M o d e l i n g o f A e r o s p a c e C o m p o s i t e s M a t e r i a l s & S t r u c t u r e s
N o n l i n e a r M u l t i - S c a l e M o d e l i n g o f A e r o s p a c e C o m p o s i t e s M a t e r i a l s & S t r u c t u r e s R o g e r A. A s s a k e r C E O, e - X s t r e a m e n g i n e
More informationCalculation of Energy Release Rate in Mode I Delamination of Angle Ply Laminated Composites
Copyright c 2007 ICCES ICCES, vol.1, no.2, pp.61-67, 2007 Calculation of Energy Release Rate in Mode I Delamination of Angle Ply Laminated Composites K. Gordnian 1, H. Hadavinia 1, G. Simpson 1 and A.
More informationModified Time-temperature Superposition Principle for Viscoelasticity of Thermosetting Resins
The 15 th Composites Durability Workshop (CDW-15), October 17 to 20, 2010, Kanazawa Institute of Technology Modified Time-temperature Superposition Principle for Viscoelasticity of Thermosetting Resins
More informationFailure Analysis of Unidirectional Composite Pinned- Joints
217 IJEDR Volume, Issue 4 ISSN: 2321-9939 Failure Analysis of Unidirectional Composite Pinned- Joints 1 Sai Ashok.M, 2 Mr. U. Koteswara Rao 1 M-tech Machine Design, 2 Associate Professor & Asst. COE 1
More informationSKIN-STRINGER DEBONDING AND DELAMINATION ANALYSIS IN COMPOSITE STIFFENED SHELLS
SKIN-STRINER DEBONDIN AND DELAMINATION ANALYSIS IN COMPOSITE STIFFENED SHELLS R. Rikards, K. Kalnins & O. Ozolinsh Institute of Materials and Structures, Riga Technical University, Riga 1658, Latvia ABSTRACT
More informationNUMERICAL MODELING OF GAS LEAKAGE THROUGH DAMAGED COMPOSITE LAMINATES
NUMERICAL MODELING OF GAS LEAKAGE THROUGH DAMAGED COMPOSITE LAMINATES Hisashi Kumazawa*, John Whitcomb** [Hisashi Kumazawa]:kumazawa.hisashi@jaxa.jp *Structure Technology Center, Japan Aerospace Exploration
More informationFatigue Life. The curve may be plotted as semilogarithmic
Fatigue Life The total number of cycles for which a specimen sustains before failure is called fatigue (cyclic) life, denoted by N. The graph by plotting values of S a and N is called S-N curve or Wöhler
More informationAssessment of Fatigue Damage Features in a Piping System Using Signal Processing Approach
PROCESSING (SIP8), Istanbul, Turkey, May 27-3, 28 Assessment o Fatigue Damage Features in a Piping System Using Signal Processing Approach 1 S. ABDULLAH, 2 M. LOMAN, 3 N. JAMALUDDIN, 4 A. ARIFIN, 5 Z.
More informationNonlinear Constant Fatigue Life Diagrams for CFRP Laminates
CompTest26, Porto Nonlinear Constant Fatigue Life Diagrams for CFRP Laminates M. Kawai and M. Koizumi Department of Engineering Mechanics and Energy Graduate School of Systems and Information Engineering
More informationMECHANICAL FAILURE OF A COMPOSITE HELICOPTER STRUCTURE UNDER STATIC LOADING
MECHANICAL FAILURE OF A COMPOSITE HELICOPTER STRUCTURE UNDER STATIC LOADING Steven Roy, Larry Lessard Dept. of Mechanical Engineering, McGill University, Montreal, Québec, Canada ABSTRACT The design and
More informationCHAPTER 6 MECHANICAL PROPERTIES OF METALS PROBLEM SOLUTIONS
CHAPTER 6 MECHANICAL PROPERTIES OF METALS PROBLEM SOLUTIONS Concepts of Stress and Strain 6.1 Using mechanics of materials principles (i.e., equations of mechanical equilibrium applied to a free-body diagram),
More informationAutodesk Helius PFA. Guidelines for Determining Finite Element Cohesive Material Parameters
Autodesk Helius PFA Guidelines for Determining Finite Element Cohesive Material Parameters Contents Introduction...1 Determining Cohesive Parameters for Finite Element Analysis...2 What Test Specimens
More informationFrontiers of Fracture Mechanics. Adhesion and Interfacial Fracture Contact Damage
Frontiers of Fracture Mechanics Adhesion and Interfacial Fracture Contact Damage Biology, Medicine & Dentistry The Next Frontiers For Mechanics One of the current challenges in materials & mechanics is
More informationComposite Damage Material Modeling for Crash Simulation: MAT54 & the Efforts of the CMH-17 Numerical Round Robin
Composite Damage Material Modeling for Crash Simulation: MAT54 & the Efforts of the CMH-17 Numerical Round Robin 2014 Technical Review Bonnie Wade (UW) Prof. Paolo Feraboli AMTAS (JAMS) Crashworthiness
More informationMaterials Science and Engineering A
Materials Science and Engineering A 528 (211) 48 485 Contents lists availale at ScienceDirect Materials Science and Engineering A journal homepage: www.elsevier.com/locate/msea Study o strength and its
More informationAn investigation of the mechanical behaviour of carbon epoxy cross ply cruciform specimens under biaxial loading
An investigation of the mechanical behaviour of carbon epoxy cross ply cruciform specimens under biaxial loading A. Makris, C. Ramault, D. Van Hemelrijck Department of Mechanics of Materials and Constructions,
More informationHIGH VELOCITY IMPACT ON TEXTILE REINFORCED COMPOSITES
16 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS HIGH VELOCITY IMPACT ON TEXTILE REINFORCED COMPOSITES Warnet L., Akkerman R., Ravensberg M. University of Twente, Faculty of Engineering Technology,
More information1. Introduction. 2. Testing strategy. Daniel HUELSBUSCH 1, Frank WALTHER 1
6th International Symposium on NDT in Aerospace, 12-14th November 2014, Madrid, Spain - www.ndt.net/app.aerondt2014 More Info at Open Access Database www.ndt.net/?id=16947 Damage detection and fatigue
More informationMASSACHUSETTS INSTITUTE OF TECHNOLOGY DEPARTMENT OF MATERIALS SCIENCE AND ENGINEERING CAMBRIDGE, MASSACHUSETTS 02139
MASSACHUSTTS INSTITUT OF TCHNOLOGY DPARTMNT OF MATRIALS SCINC AND NGINRING CAMBRIDG, MASSACHUSTTS 0239 322 MCHANICAL PROPRTIS OF MATRIALS PROBLM ST 4 SOLUTIONS Consider a 500 nm thick aluminum ilm on a
More informationEDEXCEL NATIONAL CERTIFICATE/DIPLOMA MECHANICAL PRINCIPLES AND APPLICATIONS NQF LEVEL 3 OUTCOME 1 - LOADING SYSTEMS TUTORIAL 3 LOADED COMPONENTS
EDEXCEL NATIONAL CERTIICATE/DIPLOMA MECHANICAL PRINCIPLES AND APPLICATIONS NQ LEVEL 3 OUTCOME 1 - LOADING SYSTEMS TUTORIAL 3 LOADED COMPONENTS 1. Be able to determine the effects of loading in static engineering
More informationSHEAR CAPACITY OF REINFORCED CONCRETE COLUMNS RETROFITTED WITH VERY FLEXIBLE FIBER REINFORCED POLYMER WITH VERY LOW YOUNG S MODULUS
SHEAR CAPACITY OF REINFORCED CONCRETE COLUMNS RETROFITTED WITH VERY FLEXILE FIER REINFORCED POLYMER WITH VERY LOW YOUNG S MODULUS Hu Shaoqing Supervisor: Susumu KONO ** MEE8165 ASTRACT FRP with low Young
More informationNon-conventional Glass fiber NCF composites with thermoset and thermoplastic matrices. F Talence, France Le Cheylard, France
20 th International Conference on Composite Materials Copenhagen, 19-24th July 2015 Non-conventional Glass fiber NCF composites with thermoset and thermoplastic matrices. Thierry Lorriot 1, Jalal El Yagoubi
More informationNotched Strength Estimation of Graphite/Epoxy Laminated Composite with Central Crack under Uniaxial Tensile Loading
International Journal o Composite Materials 5, 5(6): 77-8 DOI:.593/j.cmaterials.556.6 Notched Strength Estimation o Graphite/Epoxy Laminated Composite with Central Crack under Uniaxial Tensile Loading
More informationEFFECT OF THERMAL FATIGUE ON INTRALAMINAR CRACKING IN LAMINATES LOADED IN TENSION
EFFECT OF THERMAL FATIGUE ON INTRALAMINAR CRACKING IN LAMINATES LOADED IN TENSION J.Varna and R.Joffe Dept of Applied Physics and Mechanical Engineering Lulea University of Technology, SE 97187, Lulea,
More informationOpen-hole compressive strength prediction of CFRP composite laminates
Open-hole compressive strength prediction of CFRP composite laminates O. İnal 1, A. Ataş 2,* 1 Department of Mechanical Engineering, Balikesir University, Balikesir, 10145, Turkey, inal@balikesir.edu.tr
More informationSamantha Ramirez, MSE. Stress. The intensity of the internal force acting on a specific plane (area) passing through a point. F 2
Samantha Ramirez, MSE Stress The intensity of the internal force acting on a specific plane (area) passing through a point. Δ ΔA Δ z Δ 1 2 ΔA Δ x Δ y ΔA is an infinitesimal size area with a uniform force
More informationThis is an author-deposited version published in: Eprints ID: 2797
Open Archive Toulouse Archive Ouverte (OATAO) OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. This is an author-deposited
More information3960 PREPREG SYSTEM. Flexible Processing Prepreg can be suitably processed in either AFP or hand lay-up methodologies.
396 PREPREG SYSTEM Toray s nextgeneration #396 prepreg system demonstrates the next leap in performance of aerospace materials. Complementary pairing of the #396 resin system with stateoftheart T11G carbon
More informationPREDICTION OF OUT-OF-PLANE FAILURE MODES IN CFRP
PREDICTION OF OUT-OF-PLANE FAILURE MODES IN CFRP R. R. Pinto 1, P. P. Camanho 2 1 INEGI - Instituto de Engenharia Mecanica e Gestao Industrial, Rua Dr. Roberto Frias, 4200-465, Porto, Portugal 2 DEMec,
More informationTABLE OF CONTENTS. Mechanics of Composite Materials, Second Edition Autar K Kaw University of South Florida, Tampa, USA
Mechanics of Composite Materials, Second Edition Autar K Kaw University of South Florida, Tampa, USA TABLE OF CONTENTS 1. INTRODUCTION TO COMPOSITE MATERIALS 1.1 Introduction... 1.2 Classification... 1.2.1
More informationBasic Examination on Assessing Mechanical Properties of Concrete That Has Suffered Combined Deterioration from Fatigue and Frost Damage
5th International Conference on Durability of Concrete Structures Jun 30 Jul 1, 2016 Shenzhen University, Shenzhen, Guangdong Province, P.R.China Basic Examination on Assessing Mechanical Properties of
More informationCOMPRESSION TESTING OF LAMINATES OPTIMISED FOR DAMAGE TOLERANCE
OMPRESSION TESTING OF LAMINATES OPTIMISED FOR DAMAGE TOLERANE A. T. Rhead, R. Butler and N. Baker Department of Mechanical Engineering, University of Bath, Bath, UK R.Butler@bath.ac.uk SUMMARY Barely Visible
More informationUniversity of Bristol - Explore Bristol Research. Early version, also known as pre-print
Hallett, S. R., & Wisnom, M. R. (2006). Numerical investigation of progressive damage and the effect of layup in notched tensile tests. Journal of Composite Materials, 40 (14), 1229-1245. DOI: 10.1177/0021998305057432
More informationTENSILE FATIGUE BEHAVIOR OF SINGLE FIBRES AND FIBRE BUNDLES
TENSILE FATIGUE BEHAVIOR OF SINGLE FIBRES AND FIBRE BUNDLES C. Qian 1 *, R. P. L. Nijssen 1, D. D. Samborsky 2, C.Kassapoglou 3, Z. Gürdal 3, G. Q. Zhang 4 1 Knowledge Centre Wind turbine Materials and
More informationSpecimen Geometry and Material Property Uncertainty Model for Probabilistic Fatigue Life Predictions
Specimen Geometry and Material Property Uncertainty Model for Probabilistic Fatigue Life Predictions Prakash Chandra Gope*, Sandeep Bhatt**, and Mohit Pant** *Associate Professor, Mechanical Engineering
More informationDYNAMICS AND DAMAGE ASSESSMENT IN IMPACTED CROSS-PLY CFRP PLATE UTILIZING THE WAVEFORM SIMULATION OF LAMB WAVE ACOUSTIC EMISSION
DYNAMICS AND DAMAGE ASSESSMENT IN IMPACTED CROSS-PLY CFRP PLATE UTILIZING THE WAVEFORM SIMULATION OF LAMB WAVE ACOUSTIC EMISSION ABSTRACT Y. MIZUTAMI, H. NISHINO, M. TAKEMOTO and K. ONO* Aoyama Gakuin
More informationFRACTURE MECHANICS OF COMPOSITES WITH RESIDUAL STRESSES, TRACTION-LOADED CRACKS, AND IMPERFECT INTERFACES
Proc. 2 nd ESIS TC4 Conference on Polymers and Composites, in press, 1999 Author prepared reprint FRACTURE MECHANICS OF COMPOSITES WITH RESIDUAL STRESSES, TRACTION-LOADED CRACKS, AND IMPERFECT INTERFACES
More informationLab Exercise #5: Tension and Bending with Strain Gages
Lab Exercise #5: Tension and Bending with Strain Gages Pre-lab assignment: Yes No Goals: 1. To evaluate tension and bending stress models and Hooke s Law. a. σ = Mc/I and σ = P/A 2. To determine material
More informationCritical Load columns buckling critical load
Buckling of Columns Buckling of Columns Critical Load Some member may be subjected to compressive loadings, and if these members are long enough to cause the member to deflect laterally or sideway. To
More informationSize Effect on Strength of Bimaterial Joints: Computational Approach versus Analysis and Experiment
Proc. (CD), 12th Intern. Con. on Fracture (ICF-12) (held in Ottawa, Canada, July 2009), Robert Bell, ed., Carleton University, pp. 1 10. Size Eect on Strength o Bimaterial Joints: Computational Approach
More informationEstimating Damage Tolerance of Asphalt Binders Using the Linear Amplitude Sweep
Standard Method of Test for Estimating Damage Tolerance of Asphalt Binders Using the Linear Amplitude Sweep AASHTO Designation: TP 101-14 American Association of State Highway and Transportation Officials
More informationS. Srinivasan, Technip Offshore, Inc., Houston, TX
9 th ASCE Specialty Conerence on Probabilistic Mechanics and Structural Reliability PROBABILISTIC FAILURE PREDICTION OF FILAMENT-WOUND GLASS-FIBER Abstract REINFORCED COMPOSITE TUBES UNDER BIAXIAL LOADING
More informationDamage analysis of composite structures: a software editor point of view and illustration on industrial applications
1 SAMCEF Solver group, SAMTECH s.a., A Siemens Company 2 Aerospace & Mechanical Engineering Dpt, University of Liège Damage analysis of composite structures: a software editor point of view and illustration
More information