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1 6 th International Conference Computational Mechanics and Virtual Engineering COMEC October 15, Braşov, Romania COMPUER AIDED DESIGN IN CASE OF HE LAMINAED COMPOSIE MAERIALS Camelia Cerbu ransilvania University of Brasov, ROMANIA, Abstract: he wor firstly shows the analytical calculus model used to compute the distribution of the strains and stresses over the thicness in case of the laminated composite plates subjected to bending. hen, it is briefly described the main steps (calculus procedures) of the Matlab program that is used in design of the laminated composite plate in order to compute the stresses and to draw the distributions of the both strains and stresses. herefore, rectangular plates subjected to the uniformly distributed force, with different boundary conditions (all sides simply supported, two sides simple supported while the others sides are free end) may be designed by using this program. he program also reports: the stiffness matrix corresponding to the plate element of the laminated composite plate that is computed; the safety coefficients are also computed by using one of the failure theories (maximum stress criterion; sai-hill s criterion, sai-wu s criterion). Keywords: composite, Matlab program, bending, stresses, strains, safety coefficients 1. INRODUCION he Matlab program used within this wor is based on both the classical theory of the laminated composite plate [1-] and the constitutive equation of the element of the laminated composite plate with linear variation of the temperature over the thicness [4]. Firstly, the theory is briefly described and then, the main steps of the calculus methodology, used in Matlab program is presented by using the logical scheme. Finally some particular cases are considered and the results obtained by using the Matlab program are comparatively analyed.. WORK MEHODS.1. Briefly theoretical aspects It is considered the general case of a laminated composite plate element having n layers. he coordinates corresponding to the layer are: 1 and are the distances between the median plate surface and the upper or the bottom level of the layer ; is the distance between the median plate surface and the median surface of the layer. It is also considered that the temperature linearly varies over the thicness of the laminated composite plate: a b, (1) where the coefficients a and b are computed by using the following relations: 1 a ; b 1, () h where 1 is the final temperature to the uppermost surface of the plate corresponding to the coordinate - final temperature at the bottom surface of the plate corresponding to the coordinate n - initial temperature of the plate. 5

2 From the scientific literature in the field of the mechanics of the composite materials, it is already nown the constitutive equation corresponding to the laminated composite plate element with linearly variation of the temperature over the thicness [,, 5]: where: Nx N y Nxy M x M y M xy A B B D x y xy x y xy A B a B D b, () N Q ; A Q ; N Aij ij 1 ij ij N 1 N B 1 ; ij Q 1 ; ij Bij Q 1 ij (4) 1 1 N 1 N D 1 ; ij Q ij 1. ij D Q 1 ij 1 In the relation (), A is called rigidity matrix in plane because it lins the vector of strains x y xy developed within the median surface of the plate and the vector of forces N x N y Nxy developed at the level of the same surface; D x y xy he term Q ij and the vector of moments M M M - bending rigidity matrix because it lins the vector of the curvatures from relations (4) is the component of the rigidity matrix Q with respect to the global coordinate system xoy. he matrix Q x y xy ; D - bending-tensile coupling matrix. corresponding to the layer depends on the both the orientation angle of the reinforcement fibers and the rigidity matrix Q of that layer with respect to the local coordinate system 1 (material coordinate system) whose 1 axis is parallel to the fiber direction while the axis is perpendicular on the fiber direction. a. b. Figure 1: he cases of loading analyed: a. he I st case of loading; b. he II nd case of loading In case of the rectangular plate made of laminated composite material that is simply supported along the edges having the dimension b while the others two edges are free (fig. 1, a), the strain component x is non-ero []: u w A11 B 11 x, x x A 11D11 B 11 and the normal stress x developed at the level of layer is computed with the following relation [,, 5]: (5) 6

3 x Q x 11. (6) he relationship between the thermal coefficients corresponding to the two coordinate systems (global and local) is the following []: where x m y n 1 mn xy m cos ; n sin n m mn mn 1 mn m n 1 1, ; is the orientation angle of the reinforcement fibers. SAR (7) 1. Data input (dimensions of the plate; elastic characteristics and strength characteristics of all layers with respect to the the coordinate system aligned with fibre direction; external distributed pressure applied to the upper surface of the plate; temperature: = initial temperature; 1 =final temperature at the lower surface of the plate; = final temperature at the upper surface of the plate).. Calculus of the stiffness matrix Q lamina with respect to the coordinate system of the. Calculus of the stiffness matrix Q of the lamina, with respect to the global coordinate system for each layer of the plate 4. Calculus of the stiffness matrix of the thin laminated composite plate 1 Simply supported on the two edges while the others two are free Boundary Conditions Simply supporte on its edges 5. Calculus model for cilindrical bending 5. Calculus model for the case of the plate simply supported along its edges Maximum vertical displacement max the curvature vector at sections where wmax occurs w at of the midle of the plate; strain vector and 6. Calculus of the stress vector with respect to the global coordinate system for each layer of the composite plate 7. Calculus of the stress vector with respect to the local coordinate system for each layer of the composite plate 8. Calculus of the safety factors of all layers by using the failure theories: maximum stress criterion, sai-wu failure theory and sai-hill failure theory 9. Output of the results (maximum vertical displacement wmax the midle of the plate; safety factors computed with three failure theories; x, y, xy developed at critical cross-section) at of 1. Graphically plotting of the distributions of the stresses x, y, xy END Figure : Logical scheme of the application programme used to compute the thin laminated plate made of composite material 7

4 Assuming that the temperature change varies linearly on the thicness of the plate, the application programme considers two cases of boundary conditions: case 1 of loading, rectangular plate is simply supported along the edges having the dimension b while the others two edges are free (fig. 1, a). case of loading, plate is simply supported along all edges (fig. 1, b)... Application program It was created an application program by using Matlab soft, based on the analytical calculus model. his application programe may be easily used to compute a thin laminated plate made of composite materials subjected to an uniformly distributed pressure p while the temperature linearly varies on the thicness of the plate. o easily understanding of the methodology used by the application program, the logical scheme of the Matlab program is shown in the figure. he calculus relations are from the classical theory of the thin laminated plates made of composite material [1-] with linearly temperature change on the thicness [, 5]. Finally, the application programe graphically draws the distribution of the stresses over the thicness of the laminated at the level of the critical cross-section. It also computes maximum deflection w max at the midpoint of the plate and the safety coefficient c of the laminated composite plate. Moreover, the program give us the information about the number of the layer that firstly failures. he program computes the safety coefficient c by using the three failure theories: maximum normal stress theory, sai-wu s failure theory or sai-hill s theory. he last two failure theories are dedicated for composite strength calculus... Particular cases analyed Herein, it is studied the mechanically behavior of a laminated composite plate [/9/] having the dimensions a 8 mm, b 4 mm (fig. ) while the total thicness of the plate is h 6 mm. All layers have the same thicness. Each lamina is made of epoxy resin unidirectional reinforced with continuous E-glass fibres. he characteristics of the lamina are: modulus of elasticity 5 E MPa in the fiber direction; modulus of elasticity E 51 MPa in the direction perpendicular on fibers; transversal modulus of elasticity G1 51 MPa in reinforcing plane 1; tensile strength 1t 1 MPa in fiber direction; compressive strength 1c 1 MPa in fiber direction; tensile and compressive limit stresses t 5 MPa and c 1 MPa in the direction of fibers and in the direction perpendicular on fibers; thermal expansion coefficients grd and grd in the direction of fibers and in the direction perpendicular on fibers, respectively. he composite laminated plate is subjected to an uniformly distributed pressure p 1 N mm that is applied perpendicular to the plate. he initial temperature of the composite laminated plate is C. he final temperatures at the upper and lower surfaces of the late are 1 6 C and 1 C due to a heat flow. Figure : he composite laminated plate analyed. RESULS By running persistently of the application program it may obtain the distributions of the both x, y normal stresses shown in the figures 4-8 and the results presented in the able 1 concerning: maximum deflection w max ; safety coefficient c ; number of the ply that firstly failures. 8

5 a. b. Figure 4: Results obtained by using application program in the II nd case of loading. ( = C ; 1 = 6 C; = 1 C) at the level of the critical cross-section: a. Distribution of x normal stresses; b. Distribution of y normal stresses Figure 5: Distribution of the x normal stresses over the critical cross-section, obtained by using application program in the I st case of loading ( = C; 1 = 6 C; = 1 C) Figure 6: Distribution of the x normal stresses over the critical cross-section, obtained by using application program in the I st case of loading with = 1 = = C Figure 7: Distribution of the x normal stresses over the critical cross-section, obtained by using application program in the I st case of loading with = C ; 1 = - C; = C) a. b. Figure 8: Results obtained by using application program in the II nd case of loading ( = 1 = = C) at the level of the critical cross-section: a. Distribution of x normal stresses; b. Distribution of y normal stresses 9

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