| 摘要 |
<p>In a process to manufacture an aircraft fuselage stringer in composite material, a form core has a hollow profile with longitudinally segmented folding sides. The form core is converted as required from open to closed (A) presentation for carbon fiber layup. On completion of the fiber and resin layup process, the material and form core are subject to heat and pressure for the duration of the curing process. The form core sides have interlocking profiles defining the external shape of the closed unit. The closed unit is retained in the closed presentation e.g. by welding. The form core is a plastic extrusion. Further claimed are a commensurate form core and an aircraft fuselage stringer made of composite material. The closed form core is covered by a flexible sleeve (16) and peel foil, followed by the carbon fiber and resin layup. The layup is cured by external application of heat and pressure. The form core corners are fitted with metal or plastic gussets (13) to prevent the creation of sharp bends in the fiber layup. The lay-up process uses e.g. hand preparation, prepreg layup, injection press layup, or vacuum infusion. The form core folded cross-section is omega, trapezoidal, triangular ring-shaped and/or corrugated. Further claimed are a commensurate form core and an aircraft fuselage stringer.</p> |
