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The dimensions of a steel (AISI 4340) I-beam are w = 125 mm, t = 15 mm, and h = 200 mm. Assume that t and h are to be fixed. a) Calculate the moment of inertia (I) for the steel beam. b) Now, using IM6/3501-6 carbon/epoxy composite, find the width for the composite beam so that it also has an equivalent bending stiffness to that of the steel beam. Compare the weight-per-unit length of these three beams. Which is more structurally efficient? c) If this I-beam is being used as a support in a volume and weight-limited structure, what would be the effects of using the different materials on self-weight, geometry, and structural efficiency? TABLE 1.1 Mechanical properties of metals at room temperature in aircraft structures Property E Material GPa (msi) MPa (ksi) MPa (ksi) Aluminum 2024-T3 72 (10.5) 0.33 449 (65) 324 (47) 7075-T6 71 (10.3) 0.33 538 (78) 490 (71) Titanium Ti-6Al-4V 110 (16.0) 0.31 925 (134) 869 (126) Steel AISI 4340 200 (29.0) 0.32 1790 (260) 1483 (212) 300 M 0.32 1860 (270) 1520 (220) = tensile ultimate stress; tensile yield stress. g/cm3 (lb/in3) 2.78 (0.10) 2.78 (0.10) 4.46 (0.16) 7.8 (0.28) 7.8 (0.28) TABLE 1.3 Longitudinal mechanical properties of fiber composites Property E Material Type GPa (msi) GPa (ksi) T300/5208 140.0 (20) 1.50 (210) IM6/3501-6 177.0 (25.7) 2.86 (414) AS4/3501-6 140.0 (20) 2.10 (300) Boron/aluminum B/AI 2024 210.0 (30) 1.50 (210) Glass/epoxy S2 Glass/epoxy 43.0 (6.2) 1.70 (245) Aramid/epoxy Kev 49/epoxy 70.0 (10) 1.40 (200) P g/cm3 1.55 1.55 1.55 2.65 1.80 1.40

          The dimensions of a steel (AISI 4340) I-beam are w = 125 mm, t = 15 mm, and h = 200 mm. Assume that t and h are to be fixed.

a) Calculate the moment of inertia (I) for the steel beam.

b) Now, using IM6/3501-6 carbon/epoxy composite, find the width for the composite beam so that it also has an equivalent bending stiffness to that of the steel beam. Compare the weight-per-unit length of these three beams. Which is more structurally efficient?

c) If this I-beam is being used as a support in a volume and weight-limited structure, what would be the effects of using the different materials on self-weight, geometry, and structural efficiency?

TABLE 1.1 Mechanical properties of metals at room temperature in aircraft structures

Property E Material GPa (msi) MPa (ksi) MPa (ksi) Aluminum 2024-T3 72 (10.5) 0.33 449 (65) 324 (47) 7075-T6 71 (10.3) 0.33 538 (78) 490 (71) Titanium Ti-6Al-4V 110 (16.0) 0.31 925 (134) 869 (126) Steel AISI 4340 200 (29.0) 0.32 1790 (260) 1483 (212) 300 M 0.32 1860 (270) 1520 (220) = tensile ultimate stress; tensile yield stress.

g/cm3 (lb/in3)

2.78 (0.10) 2.78 (0.10)

4.46 (0.16)

7.8 (0.28) 7.8 (0.28)

TABLE 1.3 Longitudinal mechanical properties of fiber composites

Property E Material Type GPa (msi) GPa (ksi) T300/5208 140.0 (20) 1.50 (210) IM6/3501-6 177.0 (25.7) 2.86 (414) AS4/3501-6 140.0 (20) 2.10 (300) Boron/aluminum B/AI 2024 210.0 (30) 1.50 (210) Glass/epoxy S2 Glass/epoxy 43.0 (6.2) 1.70 (245) Aramid/epoxy Kev 49/epoxy 70.0 (10) 1.40 (200)

P g/cm3 1.55 1.55 1.55 2.65 1.80 1.40

the dimensions of a steel aisi4340 i beam are w 125mm t 15mm and h 200 mm assume that t and h are to be fixed that of the steel beam bnow using im63501 6 carbonepoxy composite find the width 30212

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