DESIGNING A FLEXIBLE BELLOWS COUPLING MADE FROM COMPOSITE MATERIALS USING NUMERICAL SIMULATIONS SVOČ FST 2018
|
|
- Ira Fields
- 5 years ago
- Views:
Transcription
1 DESIGNING A FLEXIBLE BELLOWS COUPLING MADE FROM COMPOSITE MATERIALS USING NUMERICAL SIMULATIONS SVOČ FST 2018 Ing. Frantisek Sedlacek, University of West Bohemia, Univerzitni 8, , Pilsen, Czech Republic ABSTRACT This paper deals with the design of a composite bellows coupling. The mechanical properties of the composite material were determined using experimental tests according to ASTM standards. A geometric optimization was done in connection with structural analysis to find the optimal design and layout of the laminate of the composite flexible bellows coupling. An advanced finite element model was used to verify the coupling using advanced intra-laminar and interlaminar failure criterions. The parameters for these numerical simulations were obtained using a series of experimental tests according to ASTM standards. KEYWORDS Flexible coupling, composite materials, numerical simulations, FEM, structural optimization, cohesive elements INTRODUCTION The main function of the coupling is to transfer torque from a master mover (e.g. electric or combustion motor, steam turbine) to a functional machine (e.g. gear, compressor, pump, generator) [1]. In most practical applications, the perfect alignment of couplings to machines, and/or shafts is impossible [2]. The conventional way of connecting is by using rigid couplings. However, if there are some misalignments, a rigid coupling can generate high reaction forces. These reaction forces may cause failure of bearings, induce noisy operation, increase vibrations or even cause breakage. Flexible couplings exist for these reasons. Elastomer flexible couplings are most widely used if there is a requirement for multiaxial compliance or transfer of loads. But their construction has many disadvantages and problems, such as very high weight, low durability (service life), high maintenance requirements, they can be used only at low speeds, rubber degradation, their stiffness is dependent on temperature, complicated design and they are expensive. The goal of this paper is to create a highly flexible coupling from composite materials which can transmit the required torque with the possibility of specific angular and axial deformation and all this with the desired stiffness. It must also have: low weight (ability to work at high rotational speeds), high eigenvalues, high durability, low maintenance requirements and a simple design. The basic function schema is shown in Fig. 1. Fig. 1 Schema of loadcases of flexible bellows coupling. However, composite material was not only used for reasons such as high strength and low weight (compared to conventional spring steel up to 80%), low friction, high eigenvalues, acid and weather (corrosion) resistance, high fatigue strength, and many other positive properties of composite materials. The main factor for its selection is its very high elastic deformation energy per unit of weight U (kj/kg). This parameter is the main factor when selecting the material for a spring, and it can be generally expressed as: U = 1 2 σ f 2 ρe [kj kg ]. (1) It means that the material with a lower modulus of elasticity E or density ρ has a relatively higher elastic deformation energy per unit of mass (EDEPM) within the same maximum allowed stress of the material σ f. Fig. 2 gives the EDEPM for common engineering materials. Carbon Fibre Reinforced Polymers (CFRP) have more than seven times higher EDEPM than standard spring steel. Only elastomers are better than CFRP, but they have a significant loss factor and many other issues mentioned above.
2 Material Elastic deformation energy per unit weight U (kj/kg) Rubber CFRP (Carbon Fibre Reinforced Polymer) Ti alloys Nylon GFRP (Glass Fibre Reinforced Polymer) Spring steel Wood Fig. 2 Schema and main values of elastic deformation energy per unit of weight of engineering materials [3]. The design methodology for the composite flexible bellows coupling (CFBC) was created based on specified goals and general requirements - see Fig. 3. It comprises four main stages; the first deals with creation of a generic CAD model and basic FEM model of the coupling. The second is intended to find the required mechanical properties of the coupling (the required stiffness in the main directions/angles). The third stage verifies the design proposal using advanced numerical simulation and experimental tests. The last stage deals with the final design and validation of the coupling. Fig. 3 Flowchart of design of composite flexible bellows coupling. BASIC DESIGN OF THE COUPLING First, it was necessary to choose the main shape of the coupling. This was very limited due to the restricted installation dimensions (especially the maximum width b = 80mm). Furthermore, the manufacturing technology and mounting options were taken into account. Several variations of the basic geometry of the CFBC were created. The most suitable design variant was the W-shaped cross-section, see Fig. 1. A generic 2D CAD model of the CFBC was created based on the main shape and FEM was applied to this model. The structural analysis was done in Siemens Simcenter NX 12 with non-linear multiphysics solver NX Nastran 12 SOL 401 (based on first-order shear deformation theory). A 2D mapped mesh with parabolic quad elements (CQUAD8) was used (see Fig. 4). The orthotropic physical properties of the layup of the composite were entered using the special NX Laminate Composites module. The solution was solved with six load subcases: the load from max. torque moment (M 0 = 12 knm), centrifugal force (n max = 4000 rev.min -1 ), max. required positive axial deformation (Δx a = 5.1 mm) and angular deformation (Δα 0 = 1.5 deg); and the load from max. torque moment, centrifugal force, maximum required negative axial deformation (Δx a = -5.1 mm) and angular deformation (Δα 0 = -1.5 deg), see Fig. 1.
3 Fig. 4 2D FEM model of CFBC. DETERMINATION OF MECHANICAL PROPERTIES OF COMPOSITE Before the numerical simulation itself, the correct mechanical and strength parameters of the laminate were determined. High strength 200gsm 2x2 twill carbon fabric prepreg gg200t (with 3k T700 toray fibres) was chosen for the coupling. The carbon fibre sheet was fabricated in laboratories at the University of West Bohemia. It was cured in an autoclave with an 8 hour cycle at 110 C. Eight different series of laminate specimens were made according to ASTM standards (a total of 118 specimens). Tensile testing the composite Steel fittings were glued to the carbon sheets because of the high strength of the specimens (to avoid slipping out of the jaws). The tensile properties of the laminate were determined according to ASTM standard D3039 to find the tensile modulus (E 1, E 2, E 3) and stress limits (X T, Y T, Z T ) of the laminate [4]. Experimental tensile tests were carried out by quasistatic load (2 mm/min) on the Zwick/Roell Z050 machine. Subsequently, failure modes of the specimens were evaluated (according to mode code, see Fig. 5) and the individual mechanical parameters were calculated using a sub-routine in Python. The final values are given in Tab. 1. Fig. 5 Experimental tensile measurement of the composite. Compressive test of the composite The compressive properties of the laminate were determined using experimental testing according to ASTM standard D3410 to find stress limits (X C, Y C, Z C ) of the prepreg in compression for all the main directions [5]. Experimental compressive tests were carried out by quasi-static load (1.5 mm/min) on a Zwick/Roell Z050 machine. Subsequently, failure modes of the specimens were evaluated (according to mode code, Chyba! Nenalezen zdroj odkazů.) and parameters were calculated with a subroutine in Python The final values are given in Tab. 1. Fig. 6 Experimental compressive measurement of the composite.
4 Objective function [N] In-plane shear test of the composite A standard test method for in-plane shear response of polymer matrix composite materials by tensile testing at ±45 was done according to ASTM standard D3518 [6]. Experimental tests were carried out using quasi-static load (2 mm/min) on the Zwick/Roell Z050 machine. Final parameters of the in-plane shear modulus (G 12, G 23, G 31) and shear stress limits (S 12, S 23, S 31) are given in Tab. 1. Mechanical properties Fig. 7 Experimental in-plane shear measurement of the composite. Strength properties ρ (kg/m 3 ) 1820 Laminate density X T (MPa) 693 Tensile strength (0 ) t (mm) Ply thickness Y T (MPa) 610 Tensile strength (90 ) E 1 (GPa) 55.8 Young s Modulus 0 Z T (MPa) 67 Tensile strength (N90 ) E 2 (GPa) 53.7 Young s Modulus 90 X C (MPa) 552 Compression strength 0 E 3 (GPa) 6.4 Young s Modulus N90 Y C (MPa) 558 Compression strength 90 G 12 (GPa) 3.12 In-plane Shear Modulus 12 Z C (MPa) 268 Compression strength N90 G 23 (GPa) 2.89 In-plane Shear Modulus 23 S 12 (MPa) In-Plane Shear Strength in 12 G 31 (GPa) 2.89 In-plane Shear Modulus 31 S 23 (MPa) 121 In-Plane Shear Strength in 23 ν 12 (-) 0.28 Poisson s ratio in plane 12 S 31 (MPa) 121 In-Plane Shear Strength in 31 k I (GPa/m) 10e3 Interface stiffness for Mode-I G IC (J/m 2 ) Fracture toughness for Mode-I k II (GPa/m) 14e3 Interface stiffness for Mode-II G IIC (J/m 2 ) 1408 Fracture toughness for Mode-II Tab. 1 Mechanical and strength properties of CFRP (gg200t prepreg). FINDING THE MOST SUITABLE GEOMETRY AND COMPOSITE LAYOUT OF THE CFBC The geometric optimization was combined with the structural analysis to find the best shape and layup of the CFBC that meets all the required mechanical properties of the coupling (stiffness in main directions/angles). The optimization was done using NX Optimizer The optimization algorithm implemented in NX Optimizer belongs to a class of methods called gradient methods [7], [8]. Finding the minimum weight of the coupling was chosen as the objective function of the optimization. The cross-section of the 3D model was divided into five main zones. The physical properties for individual plies (thickness of the plies and main angle of the fibres) were applied on these sections (Fig. 9). These forty-two parameters with four geometric parameters of the coupling were set as design variables of the geometric optimization Iteration of geometry otimization [-] Fig. 8 Change of objective function across iterations of geometry optimization (left) and change of the geometry of the coupling across iterations of the geometric optimization of the coupling (right). The maximum allowed stresses in all main normal (X T, Y T, Z T, X C, Y C, Z C ) and shear (S 12, S 23, S 31) directions were used as constrains of the optimization. The maximum rotation in the direction of the axis of the coupling (minimum desired torsional stiffness) was set as the last constrain of the geometry optimization. The progress of the objective function across iterations of the geometric optimization and change of the geometry of the CFBC are given in Fig. 8. A design weighing 2.53 kg was found with axial stiffness 410 kn/m, torsional stiffness 11 kn.m/deg and twisting stiffness 34.5 kn.m/deg. The final layup of the composite is given in Fig. 9.
5 Fig. 9 Final values of layup of the composite (from geometric optimization). VERIFICATION OF FINAL DESIGN USING ADVANCED NUMERICAL SIMULATION An advanced numerical model was created to verify the mechanical properties of the coupling and to determine the strength of the final design of the coupling from geometric optimization. An advanced FEM model was created from a basic 2D model using the NX Laminate Composites module. The 2D FEM model of the CFBC was filled into a 3D mesh with respect to the manufacturing technology for all plies, such as; cuts of the individual plies, distortions of the main directions of the fibres of the plies, resin drops and pockets and overlaps of the individual plies. A total of 168 plies were manually set using the special draping function based on the Fish-net algorithm, see Fig. 10. Fig. 10 Advanced FEM model of the coupling with details of the layup. Intra-laminar (strength properties in plies) and inter-laminar strength (strength properties between plies) was evaluated using a 3D FEM model, see Fig. 11. The inter-laminar strength of the laminate was determined because the coupling is highly flexible and works with large displacements. The numerical simulation was done using NX Nastran 12 SOL401 Multi-step Non-linear Multiphysics solver (100 steps). The flanges of the shafts and bolted connections were included with a full contact condition in the simulation. Fig. 11 Schema of Intra- and Inter-laminar failure of fibre composite.
6 DETERMINATION OF THE INTRA-LAMINAR STRENGTH The interactive Tsai-Wu failure criterion was used to determine the intra-laminar strength of the laminate [9]. The Tsai- Wu failure criterion can be written as: σ 1 2 ( 1 X T 1 X C) σ 1 + ( 1 Y T 1 Y C) σ 2 + X T X C + σ 2 Y T Y C + σ 12 (S L ) 2 + 2F 12 σ 1 σ 2 X T X C = 1, (2) Where F 12 is the coefficient of interaction and it can be wrriten as: F 12 = 2 1 2σ 2 {1 [XC X T + XT X C Y T Y C (YC Y T )] σ + (1 + XT X C Y T Y C ) σ2 }. (3) The individual ultimate stress parameters were determined using the experimental tests listed earlier and they are given in Tab. 1. DETERMINATION OF INTER-LAMINAR STRENGTH For highly flexible composite parts, it is recommended to determine the inter-laminar strength of the laminate too. A cohesive elements in the form of 2D layers between all the plies of the laminate were created (a total of 92 layers). Special cohesive parabolic elements were used with a cohesive damage interface approach according to Cachan, Allix and Ladevèze. It was necessary to find the fracture toughness (G IC, G IIC) and stiffness (k I, k II) of the interface for the first two modes of the cohesive failure (Mode-I is normal strength and Mode-II is the shear strength of the inter-laminar interface). Experimental tests for both modes of inter-laminar failure were carried out. Determination of Mode-I of the inter-laminar strength Special specimens for the double cantilever beam test (DCB test) were created from material gg200t according to ASTM standards D [11]. Experimental tensile DCB tests were carried out using a quasi-static load (2 mm/min) on the Zwick/Roell Z050 machine, see Fig Fig. 12 Experimental double cantilever beam test for finding parameters of Mode-I. The parameters of the fracture toughness (G IC) and stiffness (k I) for Mode-I were found using a special Python 2.73 subroutine in combination with a FEM model of the DCB in Abaqus 6.13 that allows fitting of the parameters. The fitting process was done with an accuracy of 4%, see Fig. 13 (red line in the chart). The final values are given in Tab. 1. Fig. 13 Fitting of fracture toughness and stiffness of interface for mode-i
7 Determination of Mode-II of the inter-laminar strength Special specimens for end-notched flexure (ENF) were fabricated from material gg200t according to ASTM standards D7905 [12]. Experimental three point bending ENF tests were carried out using a quasi-static load (0.5 mm/min) on the Zwick/Roell Z050 machine, see Fig. 14. Fig. 14 Experimental end-notched flexure test to find parameters of Mode-II. The parameters of the fracture toughness (G IIC) and stiffness (k II) for Mode-II were found in the same way as the DCB test. The fitting process was done with an accuracy of 3%, see Fig. 15 (red line in the chart). The final values are given in Tab. 1. Fig. 15 Fitting of fracture toughness and stiffness of interface for mode-ii. RESULTS OF NUMERICAL SIMULATION Fig. 16 shows the results of the displacement and the most critical normal and shear stress for the most critical loadcase (combination of: the load from max. torque moment, centrifugal force, maximum required positive axial deformation and angular deformation). Displacement (mm) Normal stress (MPa) direction 11 and 22 Shear stress (MPa) direction 12 and 23 Fig. 16 Results of the displacement and critical normal and shear stress for most critical loadcase. Fig. 17 shows the results of the intra- and inter-laminar strength of the CFBC for the same most critical loadcase. The results indicate that the design is satisfactory for both intra- and inter-laminar strength.
8 Failure index of intra-laminar strength (Tsai-Wu) Fig. 17 Results of the intra- and inter-laminar strength of CFBC. Failure index of inter-laminar strength (cohesive) CONCLUSION The optimal design of the CFBC was created using the proposed methodology (Fig. 3). The main shape and composite layup was found using geometric optimization and verified using advanced FEM numerical simulation. The intra- and inter-laminar strengths were determined based on the parameters from eight different experimental tests carried out on 118 specimens. The weight of the coupling (2.51 kg) was found to be in compliance with all the mechanical requirementsit was more than 70% lighter than a conventional steel/elastomer flexible coupling. Currently, I am working on the validation of the CFBC. A function sample of the CFBC has already been laminated. A divided positive mould was used for fabrication. The core of the mould was created using additive manufacturing technology (FDM 3D printer) from a heat-stable copolymer PA6 with short carbon fibres. The manufacturing process is shown in Fig. 18. In the future, the validation of the CFBC will be carried out using experimental testing (modal and multiaxial durability tests). Fig. 18 Laminating of function sample of CFBC. REFERENCES [1] C. M. Johnson, An introduction to flexible couplings, World Pumps, vol. 1996, no. Volume 1996, pp [2] Anon, Coupling & U-joints, Motion System Design, no. Sv. no. 12, pp [3] Materials Selection in Mechanical Design - 4th Edition. [Online]. Available: [Accessed: 23-Oct-2017]. [4] ASTM D3039 / D3039M-17, Standard Test Method for Tensile Properties of Polymer Matrix Composite Materials. West Conshohocken, PA, [5] ASTM D3410 / D3410M-16, Standard Test Method for Compressive Properties of Polymer Matrix Composite Materials with Unsupported Gage Section by Shear Loading. West Conshohocken, PA, [6] ASTM D3518 / D3518M-13, Standard Test Method for In-Plane Shear Response of Polymer Matrix Composite Materials by Tensile Test of a ±45 Laminate. West Conshohocken, PA, [7] Siemens PLM, NX Nastran Design Sensitivity and Optimization User s Guide. Siemens AG., [8] P. Goncharov, Engineering analysis with NX advanced simulation, vol Raleigh: Lulu Press. [9] W. Van Paepegem and J. Degrieck, Calculation of damage-dependent directional failure indices from the Tsai Wu static failure criterion, Composites Science and Technology, vol. 63, no. 2, pp , Feb [10] Calculation of damage-dependent directional failure indices from the Tsai - Wu failure criterion, ResearchGate. [Online]. Available: [11] A. ASTM, D , Standard test method for mode I interlaminar fracture toughness of unidirectional fiberreinforced polymer matrix composites. West Conshohocken, PA, [12] A. Standard, D7905/D7905M 14, Standard Test Method for Determination of the Mode II Interlaminar Fracture Toughness of Unidirectional Fiber-Reinforced Polymer Matrix Composites, 2014.
COMPARISON OF NUMERICAL SIMULATION AND EXPERIMENT OF A FLEXIBLE COMPOSITE CONNECTING ROD
10th International DAAAM Baltic Conference "INDUSTRIAL ENGINEERING - 12-13 May 2015, Tallinn, Estonia COMPARISON OF NUMERICAL SIMULATION AND EXPERIMENT OF A FLEXIBLE COMPOSITE CONNECTING ROD Sedláček,
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 informationComputational Analysis for Composites
Computational Analysis for Composites Professor Johann Sienz and Dr. Tony Murmu Swansea University July, 011 The topics covered include: OUTLINE Overview of composites and their applications Micromechanics
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 informationA RESEARCH ON NONLINEAR STABILITY AND FAILURE OF THIN- WALLED COMPOSITE COLUMNS WITH OPEN CROSS-SECTION
A RESEARCH ON NONLINEAR STABILITY AND FAILURE OF THIN- WALLED COMPOSITE COLUMNS WITH OPEN CROSS-SECTION H. Debski a*, J. Bienias b, P. Jakubczak b a Faculty of Mechanical Engineering, Department of Machine
More informationParameter Design of High Speed Coupling for 6 MW Wind Turbine Considering Torsional Vibration
Parameter Design of High Speed Coupling for 6 MW Wind Turbine Considering Torsional Vibration JongHun Kang 1, Junwoo Bae 2, Seungkeun Jeong 3, SooKeun Park 4 and Hyoung Woo Lee 1 # 1 Department of Mechatronics
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 informationA Study on the Tube of Integral Propeller Shaft for the Rear-wheel Drive Automobile Using Carbon Composite Fiber
A Study on the Tube of Integral Propeller Shaft for the Rear-wheel Drive Automobile Using Carbon Composite Fiber Kibong Han Mechatronics Department, Jungwon University, 85 Munmu-ro, Goesan-gun, South Korea.
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 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 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 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 informationINTERNATIONAL JOURNAL OF APPLIED ENGINEERING RESEARCH, DINDIGUL Volume 2, No 1, 2011
Interlaminar failure analysis of FRP cross ply laminate with elliptical cutout Venkateswara Rao.S 1, Sd. Abdul Kalam 1, Srilakshmi.S 1, Bala Krishna Murthy.V 2 1 Mechanical Engineering Department, P. V.
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 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 informationMulti Disciplinary Delamination Studies In Frp Composites Using 3d Finite Element Analysis Mohan Rentala
Multi Disciplinary Delamination Studies In Frp Composites Using 3d Finite Element Analysis Mohan Rentala Abstract: FRP laminated composites have been extensively used in Aerospace and allied industries
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 informationFinite element modelling of infinitely wide Angle-ply FRP. laminates
www.ijaser.com 2012 by the authors Licensee IJASER- Under Creative Commons License 3.0 editorial@ijaser.com Research article ISSN 2277 9442 Finite element modelling of infinitely wide Angle-ply FRP laminates
More informationModelling the nonlinear shear stress-strain response of glass fibrereinforced composites. Part II: Model development and finite element simulations
Modelling the nonlinear shear stress-strain response of glass fibrereinforced composites. Part II: Model development and finite element simulations W. Van Paepegem *, I. De Baere and J. Degrieck Ghent
More informationMINE ROOF SUPPORT DESIGN AND ANALYSIS. Document no : Revision no : 1.0
MINE ROOF SUPPORT DESIGN AND ANALYSIS Document no : 1806-2697-23 Revision no : 1.0 DOCUMENT TITLE : MINE ROOF SUPPORT DESIGN AND ANALYSIS DOCUMENT NUMBER : 1806-2697-23 ISSUE : Issue 1.0 DATE : 7 October
More informationModule III - Macro-mechanics of Lamina. Lecture 23. Macro-Mechanics of Lamina
Module III - Macro-mechanics of Lamina Lecture 23 Macro-Mechanics of Lamina For better understanding of the macromechanics of lamina, the knowledge of the material properties in essential. Therefore, the
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 informationTHE MUTUAL EFFECTS OF SHEAR AND TRANSVERSE DAMAGE IN POLYMERIC COMPOSITES
THE 19 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS THE MUTUAL EFFECTS OF SHEAR AND TRANSVERSE DAMAGE IN POLYMERIC COMPOSITES L.V. Smith 1 *, M. Salavatian 1 1 School of Mechanical and Materials
More informationNUMERICAL FEM ANALYSIS FOR THE PART OF COMPOSITE HELICOPTER ROTOR BLADE
Journal of KONES Powertrain and Transport, Vol. 19, No. 1 2012 NUMERICAL FEM ANALYSIS FOR THE PART OF COMPOSITE HELICOPTER ROTOR BLADE Hubert D bski Lublin University of Technology, Department of Machine
More informationMaterials: engineering, science, processing and design, 2nd edition Copyright (c)2010 Michael Ashby, Hugh Shercliff, David Cebon.
Modes of Loading (1) tension (a) (2) compression (b) (3) bending (c) (4) torsion (d) and combinations of them (e) Figure 4.2 1 Standard Solution to Elastic Problems Three common modes of loading: (a) tie
More informationEffect of Specimen Dimensions on Flexural Modulus in a 3-Point Bending Test
Effect of Specimen Dimensions on Flexural Modulus in a 3-Point Bending Test M. Praveen Kumar 1 and V. Balakrishna Murthy 2* 1 Mechanical Engineering Department, P.V.P. Siddhartha Institute of Technology,
More informationStress Analysis Lecture 3 ME 276 Spring Dr./ Ahmed Mohamed Nagib Elmekawy
Stress Analysis Lecture 3 ME 276 Spring 2017-2018 Dr./ Ahmed Mohamed Nagib Elmekawy Axial Stress 2 Beam under the action of two tensile forces 3 Beam under the action of two tensile forces 4 Shear Stress
More informationVALIDATION of CoDA SOFTWARE for COMPOSITES SYNTHESIS AND PRELIMINARY DESIGN (or GETTING COMPOSITES USED - PART 2 )
VALIDATION of CoDA SOFTWARE for COMPOSITES SYNTHESIS AND PRELIMINARY DESIGN (or GETTING COMPOSITES USED - PART 2 ) Graham D Sims and William R Broughton Composites Design Data and Methods, Centre for Materials
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 informationMODELING OF THE BEHAVIOR OF WOVEN LAMINATED COMPOSITES UNTIL RUPTURE
MODELING OF THE BEHAVIOR OF WOVEN LAMINATED COMPOSITES UNTIL RUPTURE Jean Paul Charles, Christian Hochard,3, Pierre Antoine Aubourg,3 Eurocopter, 375 Marignane cedex, France Unimeca, 6 rue J. Curie, 3453
More informationBEARING STRENGTH ASSESSMENT OF COMPOSITE MATERIAL THROUGH NUMERICAL MODELS
BEARING STRENGTH ASSESSMENT OF COMPOSITE MATERIAL THROUGH NUMERICAL MODELS Euler S. Dias*, Carlos A. Cimini Jr.* * Federal University of Minas Gerais, Dept. of Structural Engineering, Belo Horizonte -
More informationKINK BAND FORMATION OF FIBER REINFORCED POLYMER (FRP)
KINK BAND FORMATION OF FIBER REINFORCED POLYMER (FRP) 1 University of Science & Technology Beijing, China, niukm@ustb.edu.cn 2 Tsinghua University, Department of Engineering Mechanics, Beijing, China,
More informationD : SOLID MECHANICS. Q. 1 Q. 9 carry one mark each.
GTE 2016 Q. 1 Q. 9 carry one mark each. D : SOLID MECHNICS Q.1 single degree of freedom vibrating system has mass of 5 kg, stiffness of 500 N/m and damping coefficient of 100 N-s/m. To make the system
More informationMECHANICS OF MATERIALS. Prepared by Engr. John Paul Timola
MECHANICS OF MATERIALS Prepared by Engr. John Paul Timola Mechanics of materials branch of mechanics that studies the internal effects of stress and strain in a solid body. stress is associated with the
More informationMixed-Mode Fracture Toughness Determination USING NON-CONVENTIONAL TECHNIQUES
Mixed-Mode Fracture Toughness Determination USING NON-CONVENTIONAL TECHNIQUES IDMEC- Pólo FEUP DEMec - FEUP ESM Virginia Tech motivation fracture modes conventional tests [mode I] conventional tests [mode
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 informationProject MMS13 Task 5 Report No 3 (M6/D3)
Project MMS13 Task 5 Report No 3 (M6/D3) Material Data Requirements and Recommended Test Methods for the Predictive Modelling of Defect Criticality in Composite Material Systems M R L Gower and G D Sims
More informationDRAPING SIMULATION. Recent achievements and future trends. Dr. Sylvain Bel LGCIE University Lyon 1
DRAPING SIMULATION Recent achievements and future trends 1 Dr. Sylvain Bel LGCIE University Lyon 1 2 DRAPING SIMULATION Why? How? What? DRAPING SIMULATION WHY? Clamps Punch Fabric Die 1 2 Resin 3 4 Fig.
More informationSabah Shawkat Cabinet of Structural Engineering Walls carrying vertical loads should be designed as columns. Basically walls are designed in
Sabah Shawkat Cabinet of Structural Engineering 17 3.6 Shear walls Walls carrying vertical loads should be designed as columns. Basically walls are designed in the same manner as columns, but there are
More informationDYNAMIC DELAMINATION OF AERONAUTIC STRUCTURAL COMPOSITES BY USING COHESIVE FINITE ELEMENTS
DYNAMIC DELAMINATION OF AERONAUTIC STRUCTURAL COMPOSITES BY USING COHESIVE FINITE ELEMENTS M. Ilyas, F. Lachaud 1, Ch. Espinosa and M. Salaün Université de Toulouse, ISAE/DMSM, 1 avenue Edouard Belin,
More informationMechanical Engineering Ph.D. Preliminary Qualifying Examination Solid Mechanics February 25, 2002
student personal identification (ID) number on each sheet. Do not write your name on any sheet. #1. A homogeneous, isotropic, linear elastic bar has rectangular cross sectional area A, modulus of elasticity
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 informationPassive Damping Characteristics of Carbon Epoxy Composite Plates
Journal of Materials Science and Engineering A 6 (-) 35-4 doi:.765/6-63/6.-.5 D DAVID PUBLISHING Passive Damping Characteristics of Carbon Epoxy Composite Plates Dileep Kumar K * and V V Subba Rao Faculty
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 informationSSRG International Journal of Mechanical Engineering (SSRG-IJME) volume1 issue5 September 2014
Finite Element Modeling for Delamination Analysis of Double Cantilever Beam Specimen Mohammed Waseem H.S. 1, Kiran Kumar N. 2 1 Post Graduate Student, 2 Asst. Professor Dept. of Mechanical Engineering,
More informationADVANCES IN THE PROGRESSIVE DAMAGE ANALYSIS OF COMPOSITES
NAFEMS WORLD CONGRESS 13, SALZBURG, AUSTRIA ADVANCES IN THE PROGRESSIVE DAMAGE ANALYSIS OF M. Bruyneel, J.P. Delsemme, P. Jetteur (LMS Samtech, Belgium); A.C. Goupil (ISMANS, France). Dr. Ir. M. Bruyneel,
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 informationCHARACTERISATION OF FIBRE GLASS PANELS FOR NAVAL USE
ICEM12-12th International Conference on Experimental Mechanics 29 August - 2 September, 2004 Politecnico di Bari, Italy CHARACTERISATION OF FIBRE GLASS PANELS FOR NAVAL USE D. Lombardo a, G. Marannano
More informationEngineeringmanuals. Part2
Engineeringmanuals Part2 Engineering manuals for GEO5 programs Part 2 Chapter 1-12, refer to Engineering Manual Part 1 Chapter 13. Pile Foundations Introduction... 2 Chapter 14. Analysis of vertical load-bearing
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 informationFINITE ELEMENT AND EXPERIMENTAL STUDY OF NOVEL CONCEPT OF 3D FIBRE CELL STRUCTURE
FINITE ELEMENT AND EXPERIMENTAL STUDY OF NOVEL CONCEPT OF 3D FIBRE CELL STRUCTURE M. Růžička, V. Kulíšek 2, J. Had, O. Prejzek Department of Mechanics, Biomechanics and Mechatronics, Faculty of Mechanical
More informationUnified Quiz M4 May 7, 2008 M - PORTION
9:00-10: 00 (last four digits) 32-141 Unified Quiz M4 May 7, 2008 M - PORTION Put the last four digits of your MIT ID # on each page of the exam. Read all questions carefully. Do all work on that question
More informationQUESTION BANK Composite Materials
QUESTION BANK Composite Materials 1. Define composite material. 2. What is the need for composite material? 3. Mention important characterits of composite material 4. Give examples for fiber material 5.
More informationImplementation of fatigue model for unidirectional laminate based on finite element analysis: theory and practice
Focussed on Multiaxial Fatigue and Fracture Implementation of fatigue model for unidirectional laminate based on finite element analysis: theory and practice D. Carrella-Payan, B. Magneville, M. Hack,
More informationCalibration and Experimental Validation of LS-DYNA Composite Material Models by Multi Objective Optimization Techniques
9 th International LS-DYNA Users Conference Optimization Calibration and Experimental Validation of LS-DYNA Composite Material Models by Multi Objective Optimization Techniques Stefano Magistrali*, Marco
More informationA HIGHER-ORDER BEAM THEORY FOR COMPOSITE BOX BEAMS
A HIGHER-ORDER BEAM THEORY FOR COMPOSITE BOX BEAMS A. Kroker, W. Becker TU Darmstadt, Department of Mechanical Engineering, Chair of Structural Mechanics Hochschulstr. 1, D-64289 Darmstadt, Germany kroker@mechanik.tu-darmstadt.de,
More informationNUMERICAL AND EXPERIMENTAL ANALYSES OF MULTIPLE DELAMINATIONS IN CURVED COMPOSITE LAMINATES
THE 19 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS NUMERICAL AND EXPERIMENTAL ANALYSES OF MULTIPLE DELAMINATIONS IN CURVED COMPOSITE LAMINATES A. Baldi 1 *, A. Airoldi 1, P. Belotti 1, P. Bettini
More informationDEVELOPMENT OF THERMOELASTIC STRESS ANALYSIS AS A NON-DESTRUCTIVE EVALUATION TOOL
DEVELOPMENT OF THERMOELASTIC STRESS ANALYSIS AS A NON-DESTRUCTIVE EVALUATION TOOL S. Quinn*, R.K. Fruehmann and J.M. Dulieu-Barton School of Engineering Sciences University of Southampton Southampton SO17
More informationTHREE DIMENSIONAL STRESS ANALYSIS OF THE T BOLT JOINT
THREE DIMENSIONAL STRESS ANALYSIS OF THE T BOLT JOINT Víctor Martínez 1, Alfredo Güemes 2, Norbert Blanco 1, Josep Costa 1 1 Escola Politècnica Superior. Universitat de Girona. Girona, Spain (17071) 2
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 informationAnalysis and Optimization of a Hybrid Fan Blade
Analysis and Optimization of a Hybrid Fan Blade Permas Users Conference 27.04.06 28.04.06 Strassbourg DLR German Aerospace Center, Stuttgart Institute of Structures and Design J. Ehrmanntraut, F. Kocian,
More informationNumerical Evaluation of Fracture in Woven Composites by Using Properties of Unidirectional Type for modelling
J. Basic. Appl. Sci. Res., 2(12)13202-13209, 2012 2012, TextRoad Publication ISSN 2090-4304 Journal of Basic and Applied Scientific Research www.textroad.com Numerical Evaluation of Fracture in Woven Composites
More informationSOLUTION (17.3) Known: A simply supported steel shaft is connected to an electric motor with a flexible coupling.
SOLUTION (17.3) Known: A simply supported steel shaft is connected to an electric motor with a flexible coupling. Find: Determine the value of the critical speed of rotation for the shaft. Schematic and
More informationEXPERIMENTAL AND NUMERICAL STUDY OF THE ENERGY ABSORPTION CAPACITY OF PULTRUDED COMPOSITE TUBES
EXPERIMENTAL AND NUMERICAL STUDY OF THE ENERGY ABSORPTION CAPACITY OF PULTRUDED COMPOSITE TUBES D. Kakogiannis 1, D. Van Hemelrijck 1, J. Wastiels 1, S. Palanivelu 2, W. Van Paepegem 2, K. De Wolf 3, J.
More informationDEPARTMENT OF MECHANICAL ENIGINEERING, UNIVERSITY OF ENGINEERING & TECHNOLOGY LAHORE (KSK CAMPUS).
DEPARTMENT OF MECHANICAL ENIGINEERING, UNIVERSITY OF ENGINEERING & TECHNOLOGY LAHORE (KSK CAMPUS). Lab Director: Coordinating Staff: Mr. Muhammad Farooq (Lecturer) Mr. Liaquat Qureshi (Lab Supervisor)
More informationDynamic analysis of Composite Micro Air Vehicles
Dynamic analysis of Composite Micro Air Vehicles Shishir Kr. Sahu Professor and Head, Civil Engineering, National Institute of Technology, Rourkela, India E-mail: sksahu@nitrkl.ac.in ABSTRACT The present
More informationStatic and Time Dependent Failure of Fibre Reinforced Elastomeric Components. Salim Mirza Element Materials Technology Hitchin, UK
Static and Time Dependent Failure of Fibre Reinforced Elastomeric Components Salim Mirza Element Materials Technology Hitchin, UK Introduction Fibre reinforced elastomers are used in many applications,
More informationEffects of Core Softness and Bimodularity of Fibreglass Layers on Flexural Stiffness of Polymer Sandwich Structures
Effects of Core Softness and Bimodularity of Fibreglass Layers on Flexural Stiffness of Polymer Sandwich Structures Oldřich Šuba 1,*, Oldřich Šuba jr. 1, and Soňa Rusnáková 1 1 Tomas Bata University in
More informationSimulation of Dynamic Delamination and Mode I Energy Dissipation
Simulation of Dynamic Delamination and Mode I Energy Dissipation Muhammad Ilyas, Christine Espinosa 1, Frédéric Lachaud and Michel Salaün Université de Toulouse ISAE, DMSM, 1 Avenue Edouard Belin, 3154
More informationHigh Tech High Top Hat Technicians. An Introduction to Solid Mechanics. Is that supposed to bend there?
High Tech High Top Hat Technicians An Introduction to Solid Mechanics Or Is that supposed to bend there? Why don't we fall through the floor? The power of any Spring is in the same proportion with the
More information12/8/2009. Prof. A.K.M.B. Rashid Department of MME BUET, Dhaka
Prof. A.K.M.B. Rashid Department of MME BUET, Dhaka Introduction and classes of properties Case studies showing selection of the right material for the job Deformation of material under the action of a
More informationAssessment Methods of Mechanical Properties of Composite Materials
Mechanics and Mechanical Engineering Vol. 21, No. 4 (2017) 1005 1018 c Lodz University of Technology Assessment Methods of Mechanical Properties of Composite Materials Monika Kamocka Radoslaw J. Mania
More informationPROGRESSIVE DAMAGE ANALYSES OF SKIN/STRINGER DEBONDING. C. G. Dávila, P. P. Camanho, and M. F. de Moura
PROGRESSIVE DAMAGE ANALYSES OF SKIN/STRINGER DEBONDING C. G. Dávila, P. P. Camanho, and M. F. de Moura Abstract The debonding of skin/stringer constructions is analyzed using a step-by-step simulation
More informationPRELIMINARY PREDICTION OF SPECIMEN PROPERTIES CLT and 1 st order FEM analyses
OPTIMAT BLADES Page 1 of 24 PRELIMINARY PREDICTION OF SPECIMEN PROPERTIES CLT and 1 st order FEM analyses first issue Peter Joosse CHANGE RECORD Issue/revision date pages Summary of changes draft 24-10-02
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 informationApplication of fracture mechanics-based methodologies for failure predictions in composite structures
Application of fracture mechanics-based methodologies for failure predictions in composite structures Zoltan Mikulik a, B. Gangadhara Prusty a, Rodney S. Thomson b, Donald W. Kelly a,* a School of Mechanical
More informationMECHANICS OF MATERIALS
2009 The McGraw-Hill Companies, Inc. All rights reserved. Fifth SI Edition CHAPTER 3 MECHANICS OF MATERIALS Ferdinand P. Beer E. Russell Johnston, Jr. John T. DeWolf David F. Mazurek Torsion Lecture Notes:
More information2510 PREPREG SYSTEM. Industry Database FAA approved design allowable values (AGATE methodology), results in a low cost one-batch equivalency.
PREPREG SYSTEM The 251 prepreg system is specifically formulated for out-of-autoclave (OOA) processing of aerospace primary structures. This prepreg system has excellent all-around structural properties
More informationComparison of Ply-wise Stress-Strain results for graphite/epoxy laminated plate subjected to in-plane normal loads using CLT and ANSYS ACP PrepPost
Comparison of Ply-wise Stress-Strain results for graphite/epoxy laminated plate subjected to in-plane normal loads using CLT and ANSYS ACP PrepPost 1 Mihir A. Mehta, 2 Satyen D. Ramani 1 PG Student, Department
More informationISSN: ISO 9001:2008 Certified International Journal of Engineering Science and Innovative Technology (IJESIT) Volume 2, Issue 4, July 2013
Delamination Studies in Fibre-Reinforced Polymer Composites K.Kantha Rao, Dr P. Shailesh, K. Vijay Kumar 1 Associate Professor, Narasimha Reddy Engineering College Hyderabad. 2 Professor, St. Peter s Engineering
More informationCrashworthiness of composite structures: Experiment and Simulation
Crashworthiness of composite structures: Experiment and Simulation Francesco Deleo, Bonnie Wade and Prof. Paolo Feraboli (UW) Dr. Mostafa Rassaian (Boeing R&T) JAMS 2010 The Joint Advanced Materials and
More informationInfluence of the filament winding process variables on the mechanical behavior of a composite pressure vessel
Influence of the filament winding process variables on the mechanical behavior of a composite pressure vessel G. Vargas 1 & A. Miravete 2 1 Universidad Pontificia Bolivariana, Facultad de Ingeniería Mecánica,
More informationFlexural properties of polymers
A2 _EN BUDAPEST UNIVERSITY OF TECHNOLOGY AND ECONOMICS FACULTY OF MECHANICAL ENGINEERING DEPARTMENT OF POLYMER ENGINEERING Flexural properties of polymers BENDING TEST OF CHECK THE VALIDITY OF NOTE ON
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 informationfive Mechanics of Materials 1 ARCHITECTURAL STRUCTURES: FORM, BEHAVIOR, AND DESIGN DR. ANNE NICHOLS SUMMER 2017 lecture
ARCHITECTURAL STRUCTURES: FORM, BEHAVIOR, AND DESIGN DR. ANNE NICHOLS SUMMER 2017 lecture five mechanics www.carttalk.com of materials Mechanics of Materials 1 Mechanics of Materials MECHANICS MATERIALS
More informationLAMINATION THEORY FOR THE STRENGTH OF FIBER COMPOSITE MATERIALS
XXII. LAMINATION THEORY FOR THE STRENGTH OF FIBER COMPOSITE MATERIALS Introduction The lamination theory for the elastic stiffness of fiber composite materials is the backbone of the entire field, it holds
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 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 informationBending Load & Calibration Module
Bending Load & Calibration Module Objectives After completing this module, students shall be able to: 1) Conduct laboratory work to validate beam bending stress equations. 2) Develop an understanding of
More informationInternational Association of Certified Practicing Engineers
www.iacpe.com Knowledge, Certification, Networking Page: 1 101 Rev: 00 Rev 01- February 2016 IACPE No 19, Jalan Bilal Mahmood 80100 Johor Bahru Malaysia The International is providing the introduction
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 informationFinite Element Analysis Lecture 1. Dr./ Ahmed Nagib
Finite Element Analysis Lecture 1 Dr./ Ahmed Nagib April 30, 2016 Research and Development Mathematical Model Mathematical Model Mathematical Model Finite Element Analysis The linear equation of motion
More informationLoad Cell Design Using COMSOL Multiphysics
Load Cell Design Using COMSOL Multiphysics Andrei Marchidan, Tarah N. Sullivan and Joseph L. Palladino Department of Engineering, Trinity College, Hartford, CT 06106, USA joseph.palladino@trincoll.edu
More informationBenchmarking study of steel-composite structures in CAE crash applications. Master s thesis in Applied Mechanics MADELEINE ANDERSSON EMMA LARSSON
Benchmarking study of steel-composite structures in CAE crash applications Master s thesis in Applied Mechanics MADELEINE ANDERSSON EMMA LARSSON Department of Applied Mechanics CHALMERS UNIVERSITY OF TECHNOLOGY
More informationA SELF-INDICATING MODE I INTERLAMINAR TOUGHNESS TEST
A SELF-INDICATING MODE I INTERLAMINAR TOUGHNESS TEST P. Robinson The Composites Centre, Department of Aeronautics, Imperial College London South Kensington, London, SW7 2AZ, UK p.robinson@imperial.ac.uk
More informationTable of Contents. Preface...xvii. Part 1. Level
Preface...xvii Part 1. Level 1... 1 Chapter 1. The Basics of Linear Elastic Behavior... 3 1.1. Cohesion forces... 4 1.2. The notion of stress... 6 1.2.1. Definition... 6 1.2.2. Graphical representation...
More informationD : SOLID MECHANICS. Q. 1 Q. 9 carry one mark each. Q.1 Find the force (in kn) in the member BH of the truss shown.
D : SOLID MECHANICS Q. 1 Q. 9 carry one mark each. Q.1 Find the force (in kn) in the member BH of the truss shown. Q.2 Consider the forces of magnitude F acting on the sides of the regular hexagon having
More informationFlexible Mechanical Elements
lexible Mechanical Elements INTRODUCTION Belts, ropes, chains, and other similar elastic or flexible machine elements are used in conveying systems and in the transmission of power over comparatively long
More informationPassive Damping Characteristics of Carbon Epoxy Composite Plates
Journal of aterials Science and Engineering A 6 (1-2) (2016) 35-42 doi: 10.17265/2161-6213/2016.1-2.005 D DAVID PUBLISHIG Passive Damping Characteristics of Carbon Epoxy Composite Plates Dileep Kumar K
More informationAnalysis of Composite Pressure Vessels
Analysis of Composite Pressure Vessels Reza Mohammadzadeh Gheshlaghi 1 Mohammad Hassan Hojjati Hamid Reza Mohammadi Daniali 3 1 Engineering Research Centre, Tabriz, Iran,3 Department of Mechanical Engineering,
More information