FIELD: aircraft.
SUBSTANCE: invention relates to aircraft and concerns the wings of composite laminated panels. Composite laminated panel comprises a first plurality of plies of reinforcing fibers oriented at an average angle α, and a second plurality of reinforcing fibers oriented at angles ±β relative to the main load direction. Moreover, α is 0 degrees relative to the main load direction, and β is between 15 and 35 degrees.
EFFECT: weight reduction of the wing skin is achieved without damaging the flexural strength, bending stiffness and failure resistance.
14 cl, 9 dwg
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