CONSTRUCTION FROM COMPOSITE MATERIAL, MAIN WING AND FUSELAGE OF THE AIRCRAFT CONTAINING THE SPECIFIED DESIGN

摘要

1. A composite material structure, comprising: a structural member with holes made of a composite material that is a fiber reinforced plastic, said structural member extending in one direction and equipped with an opening, an adjacent structural member made of a composite material that represents a fiber-reinforced plastic, the adjacent structural element extending in the indicated one direction and connected to the side portion of the decree a structural component with holes, and the tensile load and / or compressive load act in the specified one direction, while the rigidity of the specified structural element with holes in tension and / or compression in the specified one direction is lower than the stiffness of the adjacent structural element in tension and / or compression in the indicated direction, and the lower skin of the main wing of the aircraft is made of many composite materials having an interface extending in longitudinal ohm direction of the main wing, with one of said composite material having an access opening formed in the lower main wing skin, serves as a structural element with holes, and other composite materials have the function of adjacent structural elementov.2. The composite construction according to claim 1, in which the structural element with holes is made of composite material, the main components of which are fibers oriented at an angle from +/- 30 ° to +/- 60 °,