FIELD: transport.
SUBSTANCE: invention relates to structure of composite with holes, particularly, to aircraft wing and fuselage. This structure extending in wing direction comprises multiple holes and is composed of plastic reinforced with fibre and to be subjected to compressive and/or extending load in lengthwise direction. Stiffness at lengthwise expansion/compression in peripheral edge area around the hole is smaller than that at compression is lengthwise direction in the other area around peripheral edge area. Every hole makes an access hole made in aircraft wing lower surface outer skin. Besides, lengthwise direction can be lengthwise direction of aircraft. Note here that every hole makes the illuminator opening made in aircraft fuselage outer skin.
EFFECT: ruled out strain concentration at peripheral edges of openings, decreased weight.
8 cl, 10 dwg
