Verfahren zur Herstellung eines Faserverbundbauteils für die Luft- und Raumfahrt

摘要

#CMT# #/CMT# In a process to manufacture a carbon fiber fuselage stringer (1) of essentially omega cross-section, a form core (4) with a narrow melting range is placed within a form tool (8) and heated to the commensurate cross-sectional shape. Following solidification and removal from the form, the form core is then encased in a first peel layer and a second carbon fiber (1) layer under the staged application of appropriate temperatures and pressures. #CMT# : #/CMT# When the stringer has reached the appropriate shape, hoses are connected to each end of the stringer and the stringer is heated to beyond the core melting point. The form core melts and is extracted by a combination of positive and negative pressure, and gravity. #CMT#USE : #/CMT# For aviation and space industry (claimed). Carbon fiber stringer to strengthen carbon fiber fuselage skin. #CMT#ADVANTAGE : #/CMT# The carbon fiber stringer is lighter than prior art. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a cross sectional view of a form core. 4 : Form core 6 : trapezoidal cross section 7 : core material 8 : form tool 9 : core sleeve 10 : outer face 11 : inner face.