Discuss the use of magnesium as an aircraft material

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Chapter 14 / Exercise 14.111
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4.Discuss the use of magnesium as an aircraft material and its heat treatment. How does this relate to structural factors and aviation safety? Magnesium is often used as a material to build an aircraft structure due to its light weight in nature. Magnesium is the lightest structural metal alloyed with a high strength to weight ratio. Magnesium alloysare usually heat treated to improve its mechanical properties for the use of the aircraft structure. Solution heat treatment improves the strength of magnesium and results in maximum toughness and shock resistance. This can increase the strength of the material used for the structure of the aircraft and hence, enhance its safety structurally.
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Statistics for Management and Economics + XLSTAT Bind-in
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Chapter 14 / Exercise 14.111
Statistics for Management and Economics + XLSTAT Bind-in
Keller
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5.Discuss the use of titanium as an aircraft material and its heat treatment. How does this relate to structural factors and aviation safety? Titanium is also a common material used as an aircraft construction material. Titanium is 40% lighter than steel and 60% heavier than aluminum, but it is highly corrosion resistant. Titanium’s corrosion resistance characteristics allow it to be used frequently in the structure of the aircraft. Heat treatment of titanium allows it to achieve various characteristics that can improve its material safety rating for aircraft use. Heat treatment of titanium allows it to alleviate stresses that were set up during cold forming or machining. Heat treating titanium can also enhance its maximum ductility before cold working procedures take place. Furthermore, heat treatment of titanium allows it to improve its strength and toughness. An example of this in aviation would be in the construction of aircraft that frequently break the sound barrier. Given the amount of force and stress upon a supersonic aircraft such as the SR-71 of which titanium makes up 81% of the structure, the use of the material ensure the aircraft doesn’t break apart after experiencing only three flights under such enormous stress.Dole, C. (1989).Fundamentals of aircraft material factors(2nd ed.). Englewood, CO: Jeppesen.ASSIGNMENT #3: Chapter 11 Questions 1.Discuss the advantages and disadvantages of composites. There are various advantages of composites in terms of using it for the structure of the aircraft. First of all, composites have a high strength to weight ratio and also a high stiffness to weight ration. Next,composites have the ability to tailor structures to meet loading and environmental requirements. Composites does not have the issue of metal fatigue, however some fatigue behaviors still exist in composites. Lastly, composites may be molded into complex shapes in one part. On the other hand, there are also disadvantages that come along with using composites for the structure of the aircraft. First, raw materials for composites are very expensive. Second, it can be very labor intensive when using composite materials. Third, special training and skills are required for both manufacturing and repairing composites. Fourth, high temperatures and vacuum capabilities are required for field repair. Fifth, there are more health and safety concerns to be addressed when using composites.

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