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Response to applied loads
ASSESSMENT OF COMPOSITE MATERIAL DAMAGE

Aviation Structural Mechanic (H&S) 3&2 - How airplanes are built and how to maintain them
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See figure 14-23. Drawings specify ply stacking angles and the sequence of the lay-up. A standard laminate orientation code is used to ensure standardization in the industry. The orientation code denotes the angle, in degrees, between the fibers and the “X” axis of the part. The “X” axis is usually spanwise of the part, or in the direction of applied loads. See figure 14-24. The laminate ply orientation or stacking sequence is denoted in brackets, with the angle of each ply separated by a slash (/); for example, [+45/–45/+45/-45]. Laminae are listed in sequence from the first lamina to the last. The brackets or parenthesis indicate the beginning and the end of a code. The plus (+) and minus (–) angles are relative to the “X” axis. Plus (+) signs are to the left of 0, and minus (–) signs are to the right of 0. Adjacent laminae of equal angles but opposite signs are identified as ±, (±45 = +45,  –45). The directional strengths and stiffness of the laminate can be altered by changing the ply orientation. CATEGORIES OF COMPOSITE MATERIAL DAMAGE Figure 14-23.—Laminae stacking. Advanced composite materials continue to be increasingly popular with designers of new aircraft. It is estimated that new airframes will be 75 percent to Figure 14-24.—Standard ply orientation clock. 14-22







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