| 摘要 |
<p>#CMT# #/CMT# In a process to manufacture an aircraft fuselage skin stringers in composite material (1), a core form (4) is prepared by placing a parallel group of flexible tubes (7) on a backing plate, thereby creating a form core (4). The form core exposed area is then covered by a carbon fiber and resin layup, where it is then cured by a combination of heat and pressure. #CMT# : #/CMT# The grouped parallel tubes are held in position by ties, and covered by a flexible sleeve (16) and peel foil. During the external application of heat and pressure for curing, the flexible tubes (7) are connected to a pressure source, and are pressurized internally. After completion of the curing process, the tubes are evacuated and shrink to facilitate their removal from the stringer. The form core corners are fitted with 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. After fabrication and curing of the skin panel with integral stringers, the form core steel wire is extracted. Further claimed are a commensurate form core and an aircraft fuselage skin panel. #CMT#USE : #/CMT# Process to manufacture omega-shaped aircraft fuselage stringer. #CMT#ADVANTAGE : #/CMT# The combined skin panel and stringers are lighter and of lower cost than prior art. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a cross sectional view of a suitable form core and carbon fiber layup. 2 : Base plate 3 : carbon fiber 4 : form core 7 : hollow body 9 : core sleeve 13 : gussets 15 : intermediate space 16 : flexible sleeve.</p> |
