A 1 - AIRCRAFT STRUCTURES PROJECT PHASE IV EAS 4200C...

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AIRCRAFT STRUCTURES PROJECT PHASE IV EAS 4200C Roberto Barraza IFID 0087-1745 12/15/2010
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1. A 1.5 in long through thickness crack has been discovered on the bottom surface of the wing close to the fuselage as shown in the figure below. The crack makes a 45 angle with the y-axis of the wing (along the span). Determine the stress intensity factor KI for Mode I loading. If the fracture toughness of the alloy used is = 24 MPa, would you recommend grounding the airplane? From phase III of the project, we know that the shear stress at the root for both cases is: 1248.5 psi, -15729 psi 1846.9 psi, -17620 psi Thus, we can calculate the stress intensity factor as follows: -15717.2 -17120.2 Converting the fracture toughness to English units, we get 21841.1. Thus both cases (average and elliptical) are within safe limits and the airplane is safe to flight. 2. Calculate the Mode II stress intensity factor and use the interaction equation to refine your answer to Part 1. The fracture toughness is the same for Mode I and II.
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-15717.2 -17120.2
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