| 摘要 |
<p>#CMT# #/CMT# The method involves stacking a set of plies (24, 26) on a deformable mandrel (22), where a curved profile comprises the plies having fibers oriented at preset degrees relative to longitudinal direction. The mandrel and the plies are wound on a bending tool along a rotation axis. The plies sandwiched between the mandrel and the bending tool, are bent in a single-phase. The plies are heated during bending in a deformation zone at temperature on the order of 70 degrees Celsius. The bent plies are polymerized. #CMT#USE : #/CMT# Method for manufacturing a composite material curved profile in the form of an aircraft fuselage frame, from a rectilinear preform of pre-impregnated fiber plies. #CMT#ADVANTAGE : #/CMT# The plies sandwiched between the mandrel and the bending tool, are bent in the single-phase, so that costs and implementation time can be reduced while avoiding a step-by-step process, thus limiting rejects due to absence of wrinkling or bridging in an area of radii of curvature, and hence making the profile with cores having large dimensions. The method enables providing better control of aging of resin as the deformed portion is subjected to rise in temperature. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a sectional perspective view of a stacking of plies on a rectilinear deformable mandrel, where sectioned part represents orientation of fibers of the stacked plies. 12 : Core 14 : Wings 20 : Rectilinear preform 22 : Deformable mandrel 24, 26, 28, 40 : Plies.</p> |
