METHOD FOR THE ORBITAL ASSEMBLY OF AIRCRAFT SECTIONS MADE OF COMPOSITE MATERIAL

摘要

The invention relates to a method for assembling two structural elements, at least one of the two being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of said element to adapt to the shape and perimeter of the junction interface is improved by providing longitudinal grooves distributed on the circumference of the junction interface. The grooves are of a sufficient length to provide the junction interface with the flexibility to accommodate, through the relative radial movement of each portion located between two grooves, the differences in shape and perimeter among the junction interfaces of the two structural elements.