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Materials for a Business Jet

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For aluminum 2124, used T351 condition/temper. Kevlar K49 used for density, shear strength and modulus, and yield strength. For density and ultimate tensile strength, used Dupont Kevlar 49 Aramid fiber. For CFRP, data is for Type P-VSB-32 (Union Carbide) carbon fibers.Aluminum alloy 7475 has lower impurity limits than 7075. Aluminum 7475 is used for aircraft structures because of its good fracture toughness. As noted in table 2, fracture toughness is greater in the 2xxx series aluminum alloys than in the 7xxx series aluminum alloys. Fracture toughness for all of the aluminum alloys is approximately 36 MPa m.There is a different thermal/heat treatment for each of the aluminum alloys. Aluminum 2124 responds to heat treatment by developing good toughness and strength. Machinability is optimum with the T 851 precipitation heat treated condition. The heat treatment is as follows: the alloy is "solution annealed at 920 F followed by water quench. Precipitation hardening is done at 375 F for 12 hours and air cooling - this produces the T 851 temper." (Metal Suppliers, 2006).Aluminum alloy 2124 has been selected for the main use of our aircraft. The reasons for this are: although aluminum 2124 has a lower strength and lower hardness than 7475, the fracture toughness is higher in aluminum 2124. This will contribute to a lower maintenance cost for aluminum 2124, all other things held equal.Other mechanical properties of aluminum 2124 and aluminum 7475 are virtually the same. The shear strength and shear modulus of aluminum alloys 2124 and 7475 are very similar. Their densities are almost exactly the same, as well as their moduli of elasticities.The composite selected for our aircraft is Kevlar. The reason for using Kevlar is its high ultimate tensile strength, which is almost twice as high as CFRPs. Kevlar is the lightest material that was studied here; according to table 2, Kevlar has the lowest density. Kevlar also has a relatively low cost; according to the research done for table 1, Kevlar was found to be cheaper than the aluminum alloys.The locations of the materials in our aircraft design are as follows: the aluminum alloy 2124 will be used for the fuselage skin; and Kevlar will be used for the empennage and for the ailerons, elevators and rudder of our aircraft design. Composite materials such as Kevlar can be used in these aircraft areas in order to save weight. This is similar to the Boeing Business Jet 2 (BBJ
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preview essay on Materials for a Business Jet
  • Pages: 5 (1250 words)
  • Document Type: Essay
  • Subject: Physics
  • Level: Undergraduate
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