Optimal Material Selection Aircraft Components is a B.Tech project topic for Aerospace / Aeronautical Engineering. It gives students a clear starting point for research, implementation planning, and documentation.
Optimal Material Selection Aircraft Components Project Details
| Abstract |
One of the primary concerns for aerospace engineering is choosing the proper materials for construction since this affects the structures performance, safety, longevity, and fuel efficiency. The parts of an aircraft must endure extreme service conditions, like massive mechanical loads and fluctuations in temperature and pressure. Therefore, materials must be chosen so that mass, stiffness, ductility, and resistance to elevated temperatures are considered for the appropriate balance. In this paper, the author presents a solution to the material selection problem of aircraft components by analyzing five options for different types of materials: aluminum, Aluminum 7075-T6, maraging steel, steel, and titanium. The author will use one of the decision-making systems, namely
the COPRAS (Complex Proportional Assessment) method, in order to evaluate the aforementioned engineering alternatives within the scope of the required density, elastic modulus, ductility, and temperature limitations. The author combines the materials properties with a multilevel assessment system to find the best material for the aerospace industry. The author concludes that while standard aluminum received the worst result, Aluminum 7075-T6 got the best score due to its favorable combination of lightweight, high mechanical strength, and operational performance.
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| Reference Paper |
Optimal Material Selection for Aircraft Components using The COPRAS Method |
| Domain |
Aerospace / Aeronautical Engineering |
| Sub-Domain |
Composite Materials |
| PDF Download |
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