Failure analysis of serial pinned joints in composite materials
|
|
- Hortense Payne
- 5 years ago
- Views:
Transcription
1 Indian Journal of Engineering & Materials Sciences Vol. 18, April 2011, pp Failure analysis of serial pinned joints in composite materials Alaattin Aktaş* Department of Mechanical Engineering, Uşak University, Uşak 64300, Turkey Received 23 July 2010; accepted 17 February 2011 In this paper, failure load and failure mode of woven glass epoxy composite plates with one and two serial pinned joints are analyzed experimentally and numerically. Two variables are investigated during analyses; the distance from the free edge of the plate to the diameter of the first-hole (E/D) ratio, and the width of the specimen to the diameter of the holes (W/D) ratios. Experiments are carried out according to the ASTM D Numerical study is performed by means of ANSYS finite element analysis program. Yamada Sun failure criterion is used for failure analyses. Mechanical properties of the composite material are obtained from the ASTM standards. The results showed that maximum failure load is obtained at E/D=4 and W/D=4. A good agreement is found between experimental results and numerical predictions. Keywords: Serial-pinned joint, Bearing strength, Failure mode One of the applications of pinned-joints is the construction of fiber reinforced composite structures. These joints are potential problem regions to the designers due to stress concentrations, and therefore, the strength of such a structure is dependent on the strength of its joints. This aspect of pinned-joints has attracted attention from many researchers Among them, Karakuzu et al. 2 investigated the effects of the distance between two holes-to-hole diameter ratio on the failure load and the failure modes in laminated woven-glass vinyl ester composite plates with two circular holes in serial. The failure analysis was performed numerically and experimentally. The LUSAS commercial finite element software was used for numerical analysis however; the failure mode was not predicted properly because, LUSAS program has not been improved for mechanical purpose. It has been improved for civil engineering problems. Aktas et al. 3 investigated the failure load and failure mode of glass-epoxy composite plates with one and two parallel pinned joint experimentally and numerically. The numerical study was performed by means of ANSYS finite element analysis program and good agreement was found between numerical and experimental study. Aktas and Dirikolu 4 studied the effect of stacking sequence of carbon epoxy composite laminates, with (0 /45 /-45 /90 ) S, and (90 /45 /-45 /0 ) S configuration, on pinned joint. For both configurations, the bearing strength reaches the maximum value at W/D=4 and E/D=4 geometric configuration. Sheng et al. 5 experimentally studied the * alaattin.aktas@usak.edu.tr pinned-joint for various stacking sequences of a T80011/ carbon-epoxy composite plate and also determined the maximum bearing strength and the failure mode. Okutan et al. 6 studied the bearing strength of pin loaded Kevlar-epoxy laminates experimentally. Shokrieh and Lessard 7 developed a three-dimensional non-linear finite element code to analyze the effects of material nonlinearity and the edge effects on the state of stress and failure prediction near the stress concentrations of a pinloaded graphite-epoxy laminated composite plate. Dano et al. 8 discussed influence of failure criteria and the inclusion of geometric and shear non-linearity. Ahn et al. 9 performed a nonlinear finite element analysis to consider the contact and friction between the pin and the laminate for unidirectional and woven composite laminated joints of an aircraft control rod. Pierron et al. 10 studied the behavior of woven glass fiber epoxy pin joints both numerically and experimentally, with particular attention given to the sensitivity of the model to different parameters such as clearance, friction, and material nonlinearity. This study is the continuity of the previous work of Aktas et al. 1 in which, the authors compared the single and parallel pin joints experimentally and numerically. However, in this study, the effects of E/D and W/D ratios on failure mode and failure load are investigated in the laminated woven glass fiber composite plate with one and two serial circular holes. The behavior of pin loaded composite plates was observed experimentally and numerically with various dimensions. The numerical study
2 AKTAS: FAILURE ANALYSIS OF SERIAL PINNED JOINTS IN COMPOSITE MATERIALS 103 was performed using ANSYS commercial software. Yamada-Sun failure criterion is used to obtain failure load and failure mode of the laminated plates. Problem Definition In this study, two types of pin joint plates are analyzed. One has single and the other has two serial holes as shown in Fig. 1a and 1b, respectively. The specimen with single hole of diameter (D) is located along the centerline of the plate (Fig. 1a). The center of the hole is located at distance (E) from one end. A uniform tensile load (P) is then applied to the plate, and this load is resisted by a rigid pin. The load is parallel to the plate and is symmetric with respect to the centerline. In the serial pin specimen, the distance between the two serial holes is taken 24 mm so that the failure mode gives the bearing mode 3. Since this mode gives the highest strength in pinnedjoint uses, the uniform tensile load (P) is then applied to the plate with the procedure of the single hole. In general, there are three basic pinned joint failure modes related to composites: These are net tension, shear-out, and bearing. Combination of these, i.e., mixed modes, may also appear as shown in Fig. 2. Net tension occurs catastrophically and presents the least strength. Designers are required to obtain the optimum E/D and W/D ratios to get the bearing mode, which shows the highest strength in pinned-joint uses. The behavior of the joint could be influenced by four groups of parameters 11 : (i) Material parameters: Fibre types and form, resin type, fibre orientation and laminate stacking sequence; (ii) Geometry parameters: Specimen width, W, or ratio of width to hole diameter, W/D, edge distance, E, or ratio of the edge distance to hole diameter E/D and specimen thickness (t); (iii) Fastener parameters: Fastener type, clamping area, hole size and fastener diameter; and (iv) Design parameters: Loading type, loading direction and failure criteria. Clearly, there are many variables involved in practical joints; therefore, complete characterization of joints is highly dependent on the hole geometry of the connection, including the edge distance, and the width. Experimental Procedure The fiber reinforced composite materials used in this study were manufactured from the 120 g/m 2 woven fabric, epoxy resin (Bisphenol ACY-225) and hardener (Anhydride HY-225). A hot lamination press was used for fabrication of composite plates. Laminated plates were retained at a constant pressure (250 kpa) and 130 C during 2 h for the curing process, and then the composite plate was cooled to room temperature at the same pressure. The nominal thickness and weight of the composite plates were obtained as 3.14 mm and 610 g/m 2, respectively. Specimen Preparation Woven glass-epoxy composite blanks, (0º) 4, are cut into rectangle shapes with a water-cooled diamondtipped rotary wheel for two types of testing. All cut edges were finished using a fine silicon carbide paper to remove any edge defects. The holes, typical in size of fasteners used in many airframe assemblies, were drilled using by a modified high-speed steel drilling tool with three sharp contact points to prevent fuzzy edges (Fig. 3). In this way, 6.5 mm diameter holes are Fig. 2 Three basic failure planes for pinned joints Fig. 1 Specimens dimensions Figure 3. Drill bits (a) standard, (b) modified
3 104 INDIAN J ENG. MATER. SCI., APRIL 2011 obtained on the specimens (Fig. 1). Specimens for each type were produced in the following manner: While keeping the E/D ratio as 4, the W/D ratio is varied as 2, 3, 4, and 5; and maintaining W/D as 4, E/D is changed as 2, 3, 4, and 5. Three specimens were prepared for each configuration. Material characterization In order to find the values of the longitudinal modulus, E 1, the Poisson s ratio (v 12 ), and the longitudinal tensile strength (X t ), a flat piece of woven plate, the principal axis of which coincides with the loading direction, was taken, and two strain gauges perpendicular to each other were stuck on. One of them was on principal and the other was on transverse direction. The specimen was loaded step by step up to rupture by means of a 50 kn loading capacity testing machine at a speed of 1.5 mm/min, and for all steps ε 1 and ε 2 were measured by an indicator. The same procedure was performed for the determination of transverse modulus (E 2 ), and the transverse tensile strength (Y t ). To define the respective longitudinal and transverse compressive strengths (X c ) and (Y c ), a flat piece of woven plate, the principal axis of which coincides with the loading direction was taken, and it was subjected to compressive loading up to failure. To obtain the shear modulus (G 12 ); a plate whose principal axis was on 45 was taken. Then, a strain gauge was stuck along the loading direction. The specimen was loaded step by step up to rupture and (G 12 ) was calculated by measurement of ε x, which is the strain in the tensile direction. To obtain the railshear strength (S), a series of specimens were tested. These tests were performed by placing the rail shear fixture into the testing machine and by applying compressive load. The rail-shear strength is obtained by dividing the ultimate failure load of the laminate by the sheared cross-section. The ASTM standards used for determination of the mechanical properties are given in Table 1, and the mechanical properties of the composite plate determined by the above method are given in Table 2. Testing procedures Table 1 Summarize of the ASTM standards The tests were conducted with reference to ASTM D953-D 2 at room temperature of ~20 C. One for single hole and two for serial holes through-hardening steels, 42CrMo4, hardened (by heating at 850ºC for 2 h and then quenched in oil at room temperature) and then polished pins were later inserted in holes nearly no clearance. Then, experiments were performed by Test type Determination of Specimengeometry ASTMStandard E Tensile test specimen, 1 (MPa) ASTM 12 ν Uniaxial direction X ç (MPa) Tensile test specimen, Transverse direction to fiber Shear modulus specimen Off-axis uniaxial loading E 2 (MPa) ν 21 Y ç (MPa) G 12 (MPa) ASTM [12] ASTM Shear test specimen Uniaxial direction S (MPa) Reference 14 Compressive test Uniaxial direction X b (MPa) ASTM Compressive test Transverse direction to fiber Y b (MPa) ASTM Table 2 Mechanical properties of the woven glass-epoxy composite plate E 1 =E 2 (GPa) G 12 (GPa) ν 12 X t =Y t (MPa) X c =Y c (MPa) S (MPa) R ot (mm) R oc (mm) Fiber [%]
4 AKTAS: FAILURE ANALYSIS OF SERIAL PINNED JOINTS IN COMPOSITE MATERIALS 105 means of custom fixtures on the 50 kn loading capacity universal machine with a speed of 1.5 mm/min. Characteristic lengths Characteristic length for tension (R ot ) In this study, the characteristic length for tension was determined by applying point stress criterion to the tensile specimen with a hole. This criterion has been suggested by Whitney and Nuismer 16. Figures 4a and 4b show the description of the point stress criterion and its specimen, respectively. In this criterion, failure has been said to occur when the tensile stress (σ y ) in the load direction is equal to unnotched laminate strength (σ 0 ) at some distance (R ot ) from the edge of the hole. R ot has been called characteristic length for tension 11 (Table 2). Characteristic length for compression (R oc ) In order to find the characteristic length for compression, (R oc ) bearing failure test was used (Fig. 4c). The specimen containing a machined half circle, 6.5 mm diameter, is at the center. The bearing failure test was applied by the hardened steel jig, 6.5 mm diameter. The bearing failure test was conducted at cross head speed of 1.5 mm/min. The dimension of the thickness (t) was chosen as 3.14 mm and (E) and (W) were 26 mm so that the failure mode gives the bearing mode. Since this mode gives the highest strength in pinned-joint uses, the failure load (P failure ) was measured by the bearing failure test. The point stress criterion was applied to the results obtained from the bearing failure test and the characteristic length for compression was obtained as shown in Fig. 4d. In this criterion, failure occurs when the compressive stress in the load direction equaled bearing strength (σ b ) at some distance from the arc edge. In this study, the compressive stress distribution at P failure was calculated by using finite element method (FEM) and R oc was obtained from those results and given in Table 2. Numerical Study Failure criterion In order to determine the failure loads and the failure modes, a failure criterion must be applied. In this investigation, the Yamada-Sun failure criterion is used. This criterion is quadratic theory. Involving the shear stress (τ 12 ) and the longitudinal stress (σ 1 ) along the fibers, and the following criterion for laminate failure is proposed. σ 1 2 τ ( ) + ( ) = e e 1 X S Failure e< 1 no failure... (1) Fig. 4 Description of point stress criterion
5 106 INDIAN J ENG. MATER. SCI., APRIL 2011 where, σ 1 is longitudinal stress along the fibers, X is longitudinal tensile strength of ply, τ 12 is shear stress along the fibers and S is the rail shear strength. The failure criterion (Eq. 1) only predicts whether the pin joint failed or not. It does not predict the failure mode. To obtain the failure mode the characteristic curve must be drawn. This curve is specified by Eq. (2). R c( θ) = D/ 2 + ROT + ( ROC - ROT )cosθ (2) Figure 5 shows the description of the characteristic curve. Failure occurs when e is equal to unity at any point on the characteristic curve. The calculation procedure described above also provides the location (angle θ fail showing in Fig. 5) at which e is equal to unity on the characteristic Fig. 5 Description of the characteristic curve for double serial holes curve. Knowledge of θ fail provides an estimate of the failure mode of failure, as follows 14, 0 f < θ < 15 : Bearing Failure 30 <θ f < 60 : Shear-out failure (3) 75 <θ f < 90 : Net-tension failure At intermediate values of θ fail, failure may be caused by combination of these modes. Finite element analysis Ansys TM finite element package has been used in the numerical analyses. Whether or not a joint fails under a given condition is determined by the finite element analysis as follows: (i) The geometry of the problem is modeled for single and serial holes using SHELL91 elements with the characteristic curve. The composite plates were modeled as a half model because of the symmetry of loading, geometry and material with respect to x-axis the displacements of the symmetry surface are zero in y direction (Fig. 5). (ii) In order to simulate the rigid pins, radial displacement constraints were used on the lefthand sides of the holes as shown in Fig. 6. The load was applied to the nodes of the laminate positioned at right hand side of the model. Fig. 6 Flow chart for failure load and failure mode procedure
6 AKTAS: FAILURE ANALYSIS OF SERIAL PINNED JOINTS IN COMPOSITE MATERIALS 107 (iii) The stresses (σ x, σ y and τ xy ) are calculated using the finite element method. (iv) If e equals or exceeds unity in any ply along the characteristic curve, the joint is decided to have failed. The procedure outlined above is used to numerically predict whether or not failure occurs under a given load (P). The calculated stresses are linearly proportional to the applied load. A relationship is employed to determine the maximum load (P max ), which can be imposed on the joint. For a given load (P) values of e are calculated on the characteristic curve for two cases as discussed above. The highest value of e (e 0 ) is determined, and the maximum load is calculated by the expression: P P max = (4) e 0 In order to find the failure mode, the criterion of Eq. (3) used. The procedure outlined above is shown as a chart in Fig. 7. However, in serial case, the failure loads are calculated for each hole numerically and these two loads (Let P 1 be the load available in the hole far from the free edge and P 2 be the load available in the other hole) are sum up, and then the load P 1 is divided to the sum of the loads, i.e. P P 1 = P + P 1 2 (5) Finally, failure load which occurs at each holes are calculated from Eq. (4) using the load obtained from Eq. (5) for serial pin case. The percentage of the loads which occurs at the hole far from the free edge of the specimen was given in Table 3. Results and Discussion Failure loads and failure modes of composite specimens with single and double serial holes which are subjected to reaction force by two rigid pins are investigated experimentally and numerically. In order to obtain the optimum geometry for two cases, the ratio of the edge distance to the pin diameter (E/D), Fig. 7 The effect of E/D ratio on failure load for single and serial pinned-joints
7 108 INDIAN J ENG. MATER. SCI., APRIL 2011 E/D=4 W/D=4 Table 3 The percentage of loads which occur at the hole far from the free edge of the specimens and the ratio of the specimen width to the pin diameter (W/D) have systematically been varied during analyses. Custom made fixtures on a testing machine and Ansys TM finite element package has respectively been used for pinned joint experiments and numerical solutions. Three tests were conducted for each type of specimen and average bearing load values were calculated. W/2 W/3 W/4 W/5 %88 %81 %69 %66 E/2 E/3 E/4 E/5 %69 %73 %69 %60 Failure load In serial case, the maximum failure load was calculated numerically from the procedure described in the finite element analysis section, and experimentally by multiplying the percentage of the hole far from the free edge given in Table 3 with the load obtained from the test. In this table, for example, in case of W/D=2 and E/D=4 (Table 3), while the hole far from the free edge of the specimen resists the 88% of the total applied load, on the other hand, the other resists 12%. The bearing loads with respect to E/D (W/D=4 is constant) for one and two serial pinned joints are shown in Fig. 8. When E/D is equal to 2 and 4, the failure loads takes its minimum and maximum value, respectively for two cases both experimentally and numerically however, the maximum and minimum values of the failure loads are close to each other. The results from both analyses show nearly the same trends. An interesting result is that the failure load for the serial hole is less than the single one. The reason for this may be that the most of load are carried by the hole far from the free edge of the specimen (Table 3). The bearing loads with respect to W/D (E/D=4 is constant) for single and serial pinned joints are shown in Fig. 9. When W/D is equal to 2 and 4, the failure loads takes its minimum and maximum value, respectively for two cases both experimentally and numerically. But the minimum and maximum values of loads are considerably far to each other because when W/D is equal to 2 the failure mode is net tension. Net tension occurs catastrophically and presents the least strength. The failure load of serial case is less than the single case as shown in Fig. 8. The reason is that the most of load are carried by the hole far from the free edge of specimen. In two Fig. 8 The effect of W/D ratio on failure load for single and serial pinned-joints Fig. 9 FEM and experimental results of failed specimens for serial pinned-joints figures the maximum failure loads are reached at E/D=4 and W/D=4. Failure mode In case of two holes in serial, only two types of photographs and FEM results of failure modes are given in Fig. 10. Since two types of these modes occur merely for the pins loaded in serial. One is net tension which shows least strength for W/D=2 (Fig. 10a), and the other is bearing mode, which shows the highest strength for W/D=4 (Fig. 10b). The other configurations of E/D and W/D give bearing mode. Failure occurs firstly in the pin hole far from the free edge of the specimens, because this pin hole is subjected to the highest stress (Table 3).
8 AKTAS: FAILURE ANALYSIS OF SERIAL PINNED JOINTS IN COMPOSITE MATERIALS 109 Figure 11 shows that when E/D and W/D is equal to 2 and 4, respectively, failure mode is net tension in the pin hole far from the free edge and shear out in the pin hole near the free edge of the specimen. Failure mode gives bearing mode in other configurations of E/D and W/D. In case of single hole, a photograph and FEM result are shown in Fig. 12a for the configuration of W/D=2 (E/D=4 is constant). In this figure, it is clear that failure mode is net tension. Another photograph and FEM result are shown in Fig. 12b for E/D=4 and W/D=4. In this configuration, the failure mode is bearing mode. An experimental and numerical result is shown in Fig. 13 for E/D=2 and W/D=4. It can be shown from the figure that the failure mode is mixed mode. It can be seen from figures that failure modes obtained from the experimental and numerical results are very close. Fig. 10 FEM and experimental results of failed specimens for serial pinned-joints (E/D=2 and W/D=4) Fig. 12 FEM and experimental results of failed specimens for single pinned-joints (E/D=2 and W/D=4) Fig. 11 FEM and experimental results of failed specimens for single pinned-joints Fig. 13 FEM and experimental results of failed specimens for single pinned-joints (E/D=2 and W/D=4)
9 110 INDIAN J ENG. MATER. SCI., APRIL 2011 Conclusions In the present paper, failure strength and failure mode of glass-epoxy composite plates with single and serial pinned joints has analyzed experimentally and numerically. Two variables were investigated during analyses; the distance from the free edge of plate to the diameter of the first hole (E/D) ratio (2,3,4,5), and the width of the specimen to the diameter of the holes (W/D) ratios (2,3,4,5). Experiments were carried out according to the ASTM D953-D 1. The numerical study was performed by means of ANSYS finite element analysis program. The following results are obtained from the numerical and experimental studies: In case of a serial hole (i) Minimum failure load is obtained W/D is equal to 2 when E/D=4 and W/D is equal to 2 when W/D=4. (ii) Maximum failure load is obtained at E/D=4 and W/D=4. (iii) Failure starts firstly at the hole far from the free edge since maximum failure load occurs at this hole. Therefore, when designers design their connections, they must take into account this failure load occurred at this hole. (iv) Failure modes give bearing mode at all geometrical configurations except, W/D=2 (E/D=4) and E/D=2 (W/D=4). In case of a single hole (i) Minimum failure load is obtained when W/D=2 (E/D=4) and E/D=2 (W/D=4). (ii) Maximum failure load is obtained when E/D and W/D is equal to 4. (iii) Failure modes give net tension and mixedmode when W/D=2 (E/D=4) and E/D=2 (W/D=4), respectively but other geometrical configurations give bearing mode. References 1 ASTM D 953-D, Standard test method for bearing strength of plastics, ASTM Designation, Karakuzu R, Çalışkan R, Aktas M & Icten B, Compos Struct, 82 (2008) Aktas A, Imrek H & Cunedioglu Y, Compos Struct, dio: /j. compstruct Aktas A & Dirikolu M H, Compos Struct, 62 (2003) Sheng H, Hung C & Chang F K, J Compos Mater, 30 (1996) Okutan B, Aslan Z & Karakuzu R, Compos Sci Technol, (2001) Shokrieh M M & Lessard L B, J Compos Mater, 30 (1996) Dano M L, Gendron G & Piccard A, Compos Struct, 50 (2000) Ahn H S, Kweon J H & Choi J H, J Reinforce Plastic Compos, 24(7) (2005) Pierron F, Cerisier F & Grediac M, J Compos Mater, 34 (12) (2000) Aktas A & Dirikolu M H, Compos Sci Technol, 64 (2004) ASTM D , Standard test method for tensile properties of fiber resin composites, American Society for Testing and Materials, ASTM D , Standard test method for in-plane shear response of polymer matrix composite materials by tensile test of a ±45 laminate, Aktas A & Karakuzu R, Mech Compos Mater Struct, 6 (1999) ASTM D , Standard test method for compressive properties of unidirectional or cross-ply fiber resin composites, American Society for Testing and Materials, Whitney J M & Nuismer R J, J Compos Mater, 8 (1974)
Failure 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 informationNUMERICAL MODELLING OF COMPOSITE PIN- JOINTS AND EXPERIMENTAL VALIDATION
NUMERICAL MODELLING OF COMPOSITE PIN- JOINTS AND EXPERIMENTAL VALIDATION Fabrice PIERRON*, François CERISIER*, and Michel GRÉDIAC** * SMS/ Département Mécanique et Matériaux, École Nationale Supérieure
More informationThe Accuracy of Characteristic Length Method on Failure Load Prediction of Composite Pinned Joints
, June 30 - July 2, 2010, London, U.K. The Accuracy of Characteristic Length Method on Failure Load Prediction of Composite Pinned Joints O. Aluko, and Q. Mazumder Abstract An analytical model was developed
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 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 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 informationPrediction of Elastic Constants on 3D Four-directional Braided
Prediction of Elastic Constants on 3D Four-directional Braided Composites Prediction of Elastic Constants on 3D Four-directional Braided Composites Liang Dao Zhou 1,2,* and Zhuo Zhuang 1 1 School of Aerospace,
More informationStrength of GRP-laminates with multiple fragment damages
Strength of GRP-laminates with multiple fragment damages S. Kazemahvazi, J. Kiele, D. Zenkert Kungliga Tekniska Högskolan, KTH 100 44 Stockholm, Sweden sohrabk@kth.se SUMMARY The strength of glass fibre
More informationProgressive Damage of GFRP Composite Plate Under Ballistic Impact: Experimental and Numerical Study
Progressive Damage of GFRP Composite Plate Under Ballistic Impact: Experimental and Numerical Study Progressive Damage of GFRP Composite Plate Under Ballistic Impact: Experimental and Numerical Study Md
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 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 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 informationACDC. User Manual. Ver. 1.0
ACDC User Manual Ver. 1.0 Centre Composite December 2016 ACDC, Ver. 1.0 User Manual Centre Composite, 2016 (software@composite.lv) Table of Contents Introduction... 1 System requirements... 1 Theoretical
More informationInfluence of fibre proportion and position on the machinability of GFRP composites- An FEA model
Indian Journal of Engineering & Materials Sciences Vol. 12, October 2005, pp. 443-450 Influence of fibre proportion and position on the machinability of GFRP composites- An FEA model D Abdul Budan* Department
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 information[5] Stress and Strain
[5] Stress and Strain Page 1 of 34 [5] Stress and Strain [5.1] Internal Stress of Solids [5.2] Design of Simple Connections (will not be covered in class) [5.3] Deformation and Strain [5.4] Hooke s Law
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 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 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 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 informationMicromechanical analysis of FRP hybrid composite lamina for in-plane transverse loading
Indian Journal of Engineering & Materials Sciences Vol. 15, October 2008, pp. 382-390 Micromechanical analysis of FRP hybrid composite lamina for in-plane transverse loading K Sivaji Babu a *, K Mohana
More informationCOMPARISON 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 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 informationNumerical investigation on the position of holes for reducing stress concentration in composite plates with bolted and riveted joints
THEORETICAL & APPLIED MECHANICS LETTERS 1, 041005 (2011) Numerical investigation on the position of holes for reducing stress concentration in composite plates with bolted and riveted joints M. R. Khoshravan,
More informationMechanical Properties of Materials
Mechanical Properties of Materials Strains Material Model Stresses Learning objectives Understand the qualitative and quantitative description of mechanical properties of materials. Learn the logic of
More informationNORMAL STRESS. The simplest form of stress is normal stress/direct stress, which is the stress perpendicular to the surface on which it acts.
NORMAL STRESS The simplest form of stress is normal stress/direct stress, which is the stress perpendicular to the surface on which it acts. σ = force/area = P/A where σ = the normal stress P = the centric
More informationTHE ROLE OF DELAMINATION IN NOTCHED AND UNNOTCHED TENSILE STRENGTH
THE ROLE OF DELAMINATION IN NOTCHED AND UNNOTCHED TENSILE STRENGTH M. R. Wisnom University of Bristol Advanced Composites Centre for Innovation and Science University Walk, Bristol BS8 1TR, UK M.Wisnom@bristol.ac.uk
More information4.MECHANICAL PROPERTIES OF MATERIALS
4.MECHANICAL PROPERTIES OF MATERIALS The diagram representing the relation between stress and strain in a given material is an important characteristic of the material. To obtain the stress-strain diagram
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 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 informationME 243. Mechanics of Solids
ME 243 Mechanics of Solids Lecture 2: Stress and Strain Ahmad Shahedi Shakil Lecturer, Dept. of Mechanical Engg, BUET E-mail: sshakil@me.buet.ac.bd, shakil6791@gmail.com Website: teacher.buet.ac.bd/sshakil
More informationINTRODUCTION TO STRAIN
SIMPLE STRAIN INTRODUCTION TO STRAIN In general terms, Strain is a geometric quantity that measures the deformation of a body. There are two types of strain: normal strain: characterizes dimensional changes,
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 informationSOME RESEARCH ON FINITE ELEMENT ANALYSIS OF COMPOSITE MATERIALS
Mechanical Testing and Diagnosis ISSN 2247 9635, 2012 (II), Volume 3, 79-85 SOME RESEARCH ON FINITE ELEMENT ANALYSIS OF COMPOSITE MATERIALS Valeriu DULGHERU, Viorel BOSTAN, Marin GUŢU Technical University
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 informationCHAPTER 3 THE EFFECTS OF FORCES ON MATERIALS
CHAPTER THE EFFECTS OF FORCES ON MATERIALS EXERCISE 1, Page 50 1. A rectangular bar having a cross-sectional area of 80 mm has a tensile force of 0 kn applied to it. Determine the stress in the bar. Stress
More informationFinite element analysis of drilled holes in uni-directional composite laminates using failure theories
American Journal of Science and Technology 2014; 1(3): 101-105 Published online May 30, 2014 (http://www.aascit.org/journal/ajst) Finite element analysis of drilled holes in uni-directional composite laminates
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 informationTuesday, February 11, Chapter 3. Load and Stress Analysis. Dr. Mohammad Suliman Abuhaiba, PE
1 Chapter 3 Load and Stress Analysis 2 Chapter Outline Equilibrium & Free-Body Diagrams Shear Force and Bending Moments in Beams Singularity Functions Stress Cartesian Stress Components Mohr s Circle for
More informationThe University of Melbourne Engineering Mechanics
The University of Melbourne 436-291 Engineering Mechanics Tutorial Four Poisson s Ratio and Axial Loading Part A (Introductory) 1. (Problem 9-22 from Hibbeler - Statics and Mechanics of Materials) A short
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 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 informationMECHANICS OF MATERIALS
Third E CHAPTER 2 Stress MECHANICS OF MATERIALS Ferdinand P. Beer E. Russell Johnston, Jr. John T. DeWolf Lecture Notes: J. Walt Oler Texas Tech University and Strain Axial Loading Contents Stress & Strain:
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 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 informationEXPLICIT DYNAMIC SIMULATION OF DROP-WEIGHT LOW VELOCITY IMPACT ON CARBON FIBROUS COMPOSITE PANELS
EXPLICIT DYNAMIC SIMULATION OF DROP-WEIGHT LOW VELOCITY IMPACT ON CARBON FIBROUS COMPOSITE PANELS Umar Farooq and Karl Gregory School of Built Environment and Department of Engineering, University of Bolton,
More informationEvaluation of in-plane orthotropic elastic constants of paper and paperboard
Evaluation of in-plane orthotropic elastic constants of paper and paperboard T. Yokoyama and K. Nakai Department of Mechanical Engineering, Okayama University of Science - Ridai-cho, Okayama 7-5, Japan
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 informationD.B.Kawadkar 1, Dr.D.V.Bhope, 2 S.D. Khamankar 3
Evaluation of Stress Concentration in Plate with Cutout and its Experimental Verification D.B.Kawadkar, Dr.D.V.Bhope, 2 S.D. Khamankar 3 Student, IV Semester, M.Tech (CAD/CAM) Mechanical Engineering Department,
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 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 informationUniversity of Sheffield The development of finite elements for 3D structural analysis in fire
The development of finite elements for 3D structural analysis in fire Chaoming Yu, I. W. Burgess, Z. Huang, R. J. Plank Department of Civil and Structural Engineering StiFF 05/09/2006 3D composite structures
More informationRELATIONSHIP BETWEEN RADIAL COMPRESSIVE MODULUS OF ELASTICITY AND SHEAR MODULUS OF WOOD Jen Y. Liu Research Engineer
RELATIONSHIP BETWEEN RADIAL COMPRESSIVE MODULUS OF ELASTICITY AND SHEAR MODULUS OF WOOD Jen Y. Liu Research Engineer and Robert J. Ross Supervisory Research Engineer USDA Forest Service Forest Products
More informationBurst pressure estimation of reworked nozzle weld on spherical domes
Indian Journal of Engineering & Materials Science Vol. 21, February 2014, pp. 88-92 Burst pressure estimation of reworked nozzle weld on spherical domes G Jegan Lal a, Jayesh P a & K Thyagarajan b a Cryo
More informationStrength Prediction Of Composite Laminate
Strength Prediction Of Composite te Prof. Yogananda. A 1, Mr. R. Vijayakumar 2 Assistant Professor, Department of Mechanical Engineering, East West Institute of Technology, Bangalore. Research Scholar,
More informationAmerican Society for Testing and Materials (ASTM) Standards. Mechanical Testing of Composites and their Constituents
Mechanical Testing of Composites and their Constituents American Society for Testing and Materials (ASTM) Standards Tests done to determine intrinsic material properties such as modulus and strength for
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 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 informationCapability Assessment of Finite Element Software in Predicting the Last Ply Failure of Composite Laminates
Available online at www.sciencedirect.com Procedia Engineering 41 (2012 ) 1647 1653 International Symposium on Robotics and Intelligent Sensors 2012 (IRIS 2012) Capability Assessment of Finite Element
More informationMICROMECHANICAL ANALYSIS OF FRP COMPOSITES SUBJECTED TO LONGITUDINAL LOADING
MICROMECHANICAL ANALYSIS OF FRP COMPOSITES SUBJECTED TO LONGITUDINAL LOADING N. Krishna Vihari 1, P. Phani Prasanthi 1, V. Bala Krishna Murthy 2* and A. Srihari Prasad 3 1 Mech. Engg. Dept., P. V. P. Siddhartha
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 informationIMPACT STRENGTH AND RESPONSE BEHAVIOR OF CFRP GUARDER BELT FOR SIDE COLLISION OF AUTOMOBILES
IMPACT STRENGTH AND RESPONSE BEHAVIOR OF CFRP GUARDER BELT FOR SIDE COLLISION OF AUTOMOBILES AOKI Y.*, BEN G.**, KIM H. S.* *College of Science & Technology, Nihon University **College of Industrial Technology,
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 informationDerivation of the stress concentrations at holes in orthotropic plates using thermoelastic stress analysis
Derivation of the stress concentrations at holes in orthotropic plates using thermoelastic stress analysis S. Quinn, S. Sambasivam and J.M. Dulieu-Barton School of Engineering Sciences, University of Southampton,
More informationDETERMINING THE STRESS PATTERN IN THE HH RAILROAD TIES DUE TO DYNAMIC LOADS 1
PERIODICA POLYTECHNICA SER. CIV. ENG. VOL. 46, NO. 1, PP. 125 148 (2002) DETERMINING THE STRESS PATTERN IN THE HH RAILROAD TIES DUE TO DYNAMIC LOADS 1 Nándor LIEGNER Department of Highway and Railway Engineering
More informationDetermination of the Shear Buckling Load of a Large Polymer Composite I-Section Using Strain and Displacement Sensors
Sensors 2012, 12, 16024-16036; doi:10.3390/s121216024 Article OPEN ACCESS sensors ISSN 1424-8220 www.mdpi.com/journal/sensors Determination of the Shear Buckling Load of a Large Polymer Composite I-Section
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 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 informationGeometric and Material Property Effects on the Strength of Rubber-Toughened Adhesive Joints
Geometric and Material Property Effects on the Strength of Rubber-Toughened Adhesive Joints Altering the geometry of a bonded joint will invariably cause changes to occur in the stress and strain distribution
More informationEXPERIMENTAL INVESTIGATION OF HIGH SPEED DRILLING OF GLASS FIBER REINFORCED PLASTIC (GFRP) COMPOSITE LAMINATES MADE UP OF DIFFERENT POLYMER MATRICES
International Journal of Mechanical and Production Engineering Research and Development (IJMPERD) ISSN (P): 2249-6890; ISSN (E): 2249-8001 Vol. 7, Issue 6, Dec 2017, 351-358 TJPRC Pvt. Ltd EXPERIMENTAL
More informationUNIVERSITY OF SASKATCHEWAN ME MECHANICS OF MATERIALS I FINAL EXAM DECEMBER 13, 2008 Professor A. Dolovich
UNIVERSITY OF SASKATCHEWAN ME 313.3 MECHANICS OF MATERIALS I FINAL EXAM DECEMBER 13, 2008 Professor A. Dolovich A CLOSED BOOK EXAMINATION TIME: 3 HOURS For Marker s Use Only LAST NAME (printed): FIRST
More informationComposite models 30 and 131: Ply types 0 and 8 calibration
Model calibration Composite Bi-Phase models 30 and 3 for elastic, damage and failure PAM-CRASH material model 30 is for solid and 3 for multi-layered shell elements. Within these models different ply types
More informationEMA 3702 Mechanics & Materials Science (Mechanics of Materials) Chapter 2 Stress & Strain - Axial Loading
MA 3702 Mechanics & Materials Science (Mechanics of Materials) Chapter 2 Stress & Strain - Axial Loading MA 3702 Mechanics & Materials Science Zhe Cheng (2018) 2 Stress & Strain - Axial Loading Statics
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 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 informationFinite Element Analyses of Low Velocity Impact on Thin Composite Disks
International Journal of Composite Materials 2013, 3(6B): 59-70 DOI: 10.5923/s.cmaterials.201310.07 Finite Element Analyses of Low Velocity Impact on Thin Composite Disks Marcelo L. Ribeiro 1, Ricardo
More informationCoupling of plasticity and damage in glass fibre reinforced polymer composites
EPJ Web of Conferences 6, 48 1) DOI: 1.151/epjconf/1648 c Owned by the authors, published by EDP Sciences, 1 Coupling of plasticity and damage in glass fibre reinforced polymer composites R. Kvale Joki
More informationN = Shear stress / Shear strain
UNIT - I 1. What is meant by factor of safety? [A/M-15] It is the ratio between ultimate stress to the working stress. Factor of safety = Ultimate stress Permissible stress 2. Define Resilience. [A/M-15]
More informationthe failure strengths and failure modes of composite laminates containing
464 Failure Strength of Nonlinearly Elastic Composite Laminates Containing a Pin Loaded Hole FU-KUO CHANG AND RICHARD A. SCOTT Department of Mechanical Engineering and Applied Mechanics The University
More informationInfluence of residual stresses in the structural behavior of. tubular columns and arches. Nuno Rocha Cima Gomes
October 2014 Influence of residual stresses in the structural behavior of Abstract tubular columns and arches Nuno Rocha Cima Gomes Instituto Superior Técnico, Universidade de Lisboa, Portugal Contact:
More informationThe numerical simulation research of an Ultra-Light Photovoltaic Cell multilayer composite structure
5th International Conference on Civil, Architectural and Hydraulic Engineering (ICCAHE 2016) The numerical simulation research of an Ultra-Light Photovoltaic Cell multilayer composite structure Kangwen
More informationMechanical Behavior of Circular Composite Springs with Extended Flat Contact Surfaces
Mechanical Behavior of Circular Composite Springs with Extended Flat Contact Surfaces Ping-Cheung Tse epartment of Mechanical Engineering, The Hong Kong Polytechnic University, Hunghom, Kowloon, Hong Kong
More informationMechanical and Thermal Properties of Coir Fiber Reinforced Epoxy Composites Using a Micromechanical Approach
Mechanical and Thermal Properties of Coir Fiber Reinforced Epoxy Composites Using a Micromechanical Approach Sandhyarani Biswas Department of Mechanical Engineering, N.I.T Rourkela, INDIA Abstract: Now-a-days,
More informationDesign of a fastener based on negative Poisson's ratio foam adapted from
1 Design of a fastener based on negative Poisson's ratio foam adapted from Choi, J. B. and Lakes, R. S., "Design of a fastener based on negative Poisson's ratio foam", Cellular Polymers, 10, 205-212 (1991).
More informationHygrothermal stresses in laminates
Hygrothermal stresses in laminates Changing environment conditions (temperature and moisture) have an important effect on the properties which are matrix dominated. Change in temperaturet and moisture
More informationDirect and Shear Stress
Direct and Shear Stress 1 Direct & Shear Stress When a body is pulled by a tensile force or crushed by a compressive force, the loading is said to be direct. Direct stresses are also found to arise when
More informationFrequency Response of Composite Laminates at Various Boundary Conditions
International Journal of Engineering Science Invention (IJESI) ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 www.ijesi.org ǁ PP.11-15 Frequency Response of Composite Laminates at Various Boundary Conditions
More informationEFFECT OF LAMINATION ANGLE AND THICKNESS ON ANALYSIS OF COMPOSITE PLATE UNDER THERMO MECHANICAL LOADING
Journal of MECHANICAL ENGINEERING Strojnícky časopis, VOL 67 (217), NO 1, 5-22 EFFECT OF LAMINATION ANGLE AND THICKNESS ON ANALYSIS OF COMPOSITE PLATE UNDER THERMO MECHANICAL LOADING Arnab Choudhury 1,
More informationPlane Strain Test for Metal Sheet Characterization
Plane Strain Test for Metal Sheet Characterization Paulo Flores 1, Felix Bonnet 2 and Anne-Marie Habraken 3 1 DIM, University of Concepción, Edmundo Larenas 270, Concepción, Chile 2 ENS - Cachan, Avenue
More informationCOMBINED IN-PLANE AND THROUGH-THE-THICKNESS ANALYSIS FOR FAILURE PREDICTION OF BOLTED COMPOSITE JOINTS
COMBINED IN-PLANE AND THROUGH-THE-THICKNESS ANALYSIS FOR FAILURE PREDICTION OF BOLTED COMPOSITE JOINTS V. Kradinov, * E. Madenci The University of Arizona, Tucson, Arizona, 8575 D. R. Ambur NASA Langley
More informationAdvanced Structural Analysis EGF Section Properties and Bending
Advanced Structural Analysis EGF316 3. Section Properties and Bending 3.1 Loads in beams When we analyse beams, we need to consider various types of loads acting on them, for example, axial forces, shear
More informationName :. Roll No. :... Invigilator s Signature :.. CS/B.TECH (CE-NEW)/SEM-3/CE-301/ SOLID MECHANICS
Name :. Roll No. :..... Invigilator s Signature :.. 2011 SOLID MECHANICS Time Allotted : 3 Hours Full Marks : 70 The figures in the margin indicate full marks. Candidates are required to give their answers
More informationASPECTS CONCERNING TO THE MECHANICAL PROPERTIES OF THE GLASS / FLAX / EPOXY COMPOSITE MATERIAL
5 th International Conference Advanced Composite Materials Engineering COMAT 2014 16-17 October 2014, Braşov, Romania ASPECTS CONCERNING TO THE MECHANICAL PROPERTIES OF THE GLASS / FLAX / EPOXY COMPOSITE
More informationMULTISCALE AND MULTILEVEL ANALYSIS OF COMPOSITE STRUCTURES WITH BOLTED JOINTS
MULTISCALE AND MULTILEVEL ANALYSIS OF COMPOSITE STRUCTURES WITH BOLTED JOINTS F.-X. Irisarri, J.-F. Maire* and N. Carrere ONERA, 9 av. de la Division Leclerc, 930 Châtillon, France francois-xavier.irisarri@onera.fr,
More informationTheory at a Glance (for IES, GATE, PSU)
1. Stress and Strain Theory at a Glance (for IES, GATE, PSU) 1.1 Stress () When a material is subjected to an external force, a resisting force is set up within the component. The internal resistance force
More informationMECE 3321 MECHANICS OF SOLIDS CHAPTER 3
MECE 3321 MECHANICS OF SOLIDS CHAPTER 3 Samantha Ramirez TENSION AND COMPRESSION TESTS Tension and compression tests are used primarily to determine the relationship between σ avg and ε avg in any material.
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 informationTensile Properties of Thermoplastic-Laminated Composites Based on a Polypropylene Matrix Reinforced with Continuous Twaron Fibers
Tensile Properties of Thermoplastic-Laminated Composites Based on a Polypropylene Matrix Reinforced with Continuous Twaron Fibers J. L. MENA-TUN, P. I. GONZALEZ-CHI Centro de Investigación Científica de
More informationRELIABILITY ANALYSIS IN BOLTED COMPOSITE JOINTS WITH SHIMMING MATERIAL
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES RELIABILITY ANALYSIS IN BOLTED COMPOSITE JOINTS WITH SHIMMING MATERIAL P. Caracciolo, G. Kuhlmann AIRBUS-Germany e-mail: paola.caracciolo@airbus.com
More informationPREDICTION OF FAILURE BEHAVIOUR OF COMPOSITE LATTICE STRUCTURE UNDER COMPRESSIVE LOAD
PREDICTION OF FAILURE BEHAVIOUR OF COMPOSITE LATTICE STRUCTURE UNDER COMPRESSIVE LOAD Min-Hyeok Jeon. 1, Min-Song Kang 1, Mun-Guk Kim 1, Eun-Su Go 1, In-Gul Kim. 1, and Sang-Woo Lee 2 1 Aerospace Engineering,
More information