Down Autocad 2004 Crack Full WORK
Down Autocad 2004 Crack Full WORK
Down Autocad 2004 Crack Full
the damage of the laminates, which is due to the matrix cracking and delamination, are mainly observed in the back side of the laminates. the damage of the laminates is more severe in the carbon fiber and epoxy resin layers than in the glass fiber and epoxy resin layers. the damage of the glass fiber layer is due to the crack propagation in the layer, while the damage of the carbon fiber layer is due to the fiber failure. the damage of the epoxy resin layer is due to the matrix cracking. the damage of the glass/carbon fiber-reinforced laminates is the result of the damage of the glass and carbon fiber layers in the laminates.
the graph showing impact force indicates clearly that the addition of the carbon fiber layer in the midplane in specimen gc1 enhances impact resistance even after the failure of the glass fiber layer on the impacted side. the impact force increases quickly and drops down to the lowest value for specimen g, whereas the impact force does not drop down drastically for the specimen gc1 with the carbon fiber layer in the midplane. the energy absorbed during impact is found to be greater in case of specimen gc1 compared with that of specimen g. furthermore, the laminate with carbon fiber in the midplane absorbed more energy than the fully glass laminate in the later stage of impact. this can be attributed to the fact that the carbon fiber layers can absorb the impact more effectively in specimen gc1 than the fully glass fiber layers in specimen g.
the time histories of impact force and energy absorbed by the laminates are shown in figure 6 a and b, respectively. as can be seen, the impact force of specimen gc2 increased and dropped slowly to the lowest value, whereas in specimen cg1, the impact force increased and then dropped suddenly after reaching the maximum value, indicating the failure of the carbon fiber layer in the skin. as the carbon fiber layer failed initially, the force dropped down and reached the value close to gc2. the impact force of specimen gcg is similar to that of specimen cg1 up to the maximum value, but the specimen gcg maintained the force of resistance due to the carbon fiber layers in the middle. energy absorbed is almost similar for all the laminates, with the lowest value of energy absorbed by the specimen gc2. the rate of energy absorbtion is greater for the specimen cg1 at the initial stages, although it dropped down after the carbon fiber failed. in comparison, the laminate gcg absorbed more energy, increasing steadily at the later stages of the impact.
a total of 72 hybrid composite specimens were fabricated and divided into four groups, and the testing was conducted on three separate days. each group included 12 specimens tested on the ultms and 3pb. the four groups were (1) low glass/carbon ratio, 0.1 (w/c ratio), 0.2; (2) high glass/carbon ratio, 0.3; (3) low laminate thickness, 5 mm; and (4) high laminate thickness, 7 mm. the impact load, force and displacement, impact energy, and penetration were measured using the instrumented drop-weight impact tester. the micro-cracks observed at the delamination failure areas of the fractured specimens were recorded using x-ray computed tomography (ct) image system. after the tests, the specimens were cut in half along the delamination direction. the delamination area on each half was measured and compared using the software. the results of the ultms and 3-point bend test are shown in table 3. the table shows that the average value of the tensile yield strengths are 17.1, 23.6, and 22.3 mpa for the low, medium, and high glass/carbon ratios, respectively, and are lower than the values of the tensile yield strengths of 29.4, 32.7, and 36.8 mpa for the low, medium, and high glass/carbon ratios, respectively. the average value of the tensile modulus is 34.4, 35.1, and 40.1 gpa for the low, medium, and high glass/carbon ratios, respectively, and are lower than the tensile modulus of 57.1, 54.9, and 53.6 gpa for the low, medium, and high glass/carbon ratios, respectively. the average value of the compressive yield strengths are 19.6, 23.3, and 23.1 mpa for the low, medium, and high glass/carbon ratios, respectively, and are lower than the compressive yield strengths of 34.1, 41.7, and 42.9 mpa for the low, medium, and high glass/carbon ratios, respectively. the average value of the compressive modulus is 33.6, 32.1, and 34.3 gpa for the low, medium, and high glass/carbon ratios, respectively, and are lower than the compressive modulus of 55.3, 53.
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