Consider a single lamina of unidirectional kevlar-epoxy with a
fiber orientation angle of 55 degress . You may use a computer or
do the calculations by hand but must show your work. Use the lamina
properties provided in Lesson 3, Slide 19 in SI units. The lamina
is loaded with stresses {x,
y,
xy} = {125, -10,
20} MPa. a. Sketch a complete and useful figure for this problem,
including all relevant coordinate systems. b. Calculate the strains
in the x-y coordinate system caused by the applied
stresses.
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Consider a single lamina of unidirectional kevlar-epoxy with a
fiber orientation angle of 55 degress ....
Consider a unidirectional Kevlar/Epoxy lamina. The stiffness in the fiber direction must be at least 70...
Consider a unidirectional Kevlar/Epoxy lamina. The stiffness in the fiber direction must be at least 70 GPa, and the stiffness perpendicular to the fibers must be at least 10 GPa. The modulus of the Kevlar fibers is 124 GPa, and Poisson ratio is 0.35. The modulus of the Epoxy is 3.5 GPa and Poisson ratio is 0.33. You may use the 4 design equations from Lesson 6, Slide 17. a) Write 2 simple equations that define the 2 requirements you...
Composite Structures Tutorial 7 (week 8) 7.1 Find the five strength parameters of a unidirectional glass/epoxy lamina with 40% fiber volume fraction. Use the properties of glass and ep...
Composite Structures Tutorial 7 (week 8) 7.1 Find the five strength parameters of a unidirectional glass/epoxy lamina with 40% fiber volume fraction. Use the properties of glass and epoxy from Table 3.1 and Table 3.2. Assume the fibers have circular cross-section and are in a square array packing. 1-52.0-$01674870 225 47 Find 208 Mechanics of Composite Materials, Second Edi Convert PO or Excel Orl Select PDF I TABLE 3.1 Typical Properties of Fibers (SI System of Units) Units Graphite Glass...
2. For a graphite/epoxy unidirectional lamina (un-oriented lamina), find the following: ,--3 MPa 1) Compliance matrix...
2. For a graphite/epoxy unidirectional lamina (un-oriented lamina), find the following: ,--3 MPa 1) Compliance matrix 2) Stiffness matrix 3) Resultant strain under the applied stresses 12-4 MP 2 MPa τ12 Typical Mechanical Properties of a Unidirectional Lamina (SI System of Units) Glass Boron/ Graphitel epoxy epoxy Property Symbol Units epoxy Fiber volume fraction Longitudinal elastic modulus E Transverse elastic modulus E, Major Poisson's ratio Shear modulus Ultimate longitudinal tensile (σ1he 0.45 0.70 10.30 7.17 GPa GPa 38.6 8.27 18.50...
3. A [0/90]s graphite/epoxy laminate is subjected to a tensile normal load of 1N/m in the x- dire...
3. A [0/90]s graphite/epoxy laminate is subjected to a tensile normal load of 1N/m in the x- direction (the direction parallel to the fibers in the 0° ply). Assume the thickness of each ply is 5 mm and use properties of unidirectional graphite/epoxy lamina from the table. a) Calculate the resultant strains of the laminate b) Calculate the global stresses in the laminate c) Calculate the principal stresses (stresses in material directions) of the top layer. Typical Mechanical Properties of...
6.1 A simply supported laminated composite beam (Figure 6.6) made of glass/epoxy is 75 mm long an...
6.1 A simply supported laminated composite beam (Figure
6.6) made of glass/epoxy is 75 mm long and has the layup of
[±30]2s. A uniform load is applied on the beam that is 5 mm in
width. Assume each ply is 0.125 mm thick and the properties of
glass/epoxy are from Table 2.1.
1. What is the maximum deflection of the
beam?
2. Find the local stresses at the top of the
laminate.
q- 100 N/m 0.075 m FIGURE 6.6 Uniformly...
8.17 A [0/90] crossply antisymmetric carbon/epoxy lam- inate is cooled down during curing from 18...
We were unable to transcribe this image8.17 A [0/90] crossply antisymmetric carbon/epoxy lam- inate is cooled down during curing from 180 oC (356 °F) to 30 °C (86 °F) (Fig. 8.18). Compute the curvatures K, and k, for the lamina properties E 140 GPa (20.3 Msi) E2-10 GPa ( 1 .45 Msi) G12-6 GPa (0.87 Msi) V12 = 0.34 02 30 x 10-/C (16.7 x 10- F) β,-0.55 t = 1 mm (0.040 in) (layer thickness)
8.17 A [0/90] crossply...
Consider a unidirectional Kevlar/Epoxy lamina. The stiffness in the fiber direction must be at least 70 GPa, and the stiffness perpendicular to the fibers must be at least 10 GPa. The modulus of the Kevlar fibers is 124 GPa, and Poisson ratio is 0.35. The modulus of the Epoxy is 3.5 GPa and Poisson ratio is 0.33. You may use the 4 design equations from Lesson 6, Slide 17. a) Write 2 simple equations that define the 2 requirements you...
Composite Structures Tutorial 7 (week 8) 7.1 Find the five strength parameters of a unidirectional glass/epoxy lamina with 40% fiber volume fraction. Use the properties of glass and epoxy from Table 3.1 and Table 3.2. Assume the fibers have circular cross-section and are in a square array packing. 1-52.0-$01674870 225 47 Find 208 Mechanics of Composite Materials, Second Edi Convert PO or Excel Orl Select PDF I TABLE 3.1 Typical Properties of Fibers (SI System of Units) Units Graphite Glass...
2. For a graphite/epoxy unidirectional lamina (un-oriented lamina), find the following: ,--3 MPa 1) Compliance matrix 2) Stiffness matrix 3) Resultant strain under the applied stresses 12-4 MP 2 MPa τ12 Typical Mechanical Properties of a Unidirectional Lamina (SI System of Units) Glass Boron/ Graphitel epoxy epoxy Property Symbol Units epoxy Fiber volume fraction Longitudinal elastic modulus E Transverse elastic modulus E, Major Poisson's ratio Shear modulus Ultimate longitudinal tensile (σ1he 0.45 0.70 10.30 7.17 GPa GPa 38.6 8.27 18.50...
3. A [0/90]s graphite/epoxy laminate is subjected to a tensile normal load of 1N/m in the x- direction (the direction parallel to the fibers in the 0° ply). Assume the thickness of each ply is 5 mm and use properties of unidirectional graphite/epoxy lamina from the table. a) Calculate the resultant strains of the laminate b) Calculate the global stresses in the laminate c) Calculate the principal stresses (stresses in material directions) of the top layer. Typical Mechanical Properties of...
6.1 A simply supported laminated composite beam (Figure
6.6) made of glass/epoxy is 75 mm long and has the layup of
[±30]2s. A uniform load is applied on the beam that is 5 mm in
width. Assume each ply is 0.125 mm thick and the properties of
glass/epoxy are from Table 2.1.
1. What is the maximum deflection of the
beam?
2. Find the local stresses at the top of the
laminate.
q- 100 N/m 0.075 m FIGURE 6.6 Uniformly...
We were unable to transcribe this image8.17 A [0/90] crossply antisymmetric carbon/epoxy lam- inate is cooled down during curing from 180 oC (356 °F) to 30 °C (86 °F) (Fig. 8.18). Compute the curvatures K, and k, for the lamina properties E 140 GPa (20.3 Msi) E2-10 GPa ( 1 .45 Msi) G12-6 GPa (0.87 Msi) V12 = 0.34 02 30 x 10-/C (16.7 x 10- F) β,-0.55 t = 1 mm (0.040 in) (layer thickness)
8.17 A [0/90] crossply...
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