/ REINFORCED LAY-UP STRUCTURE AND METHOD OF CARBON EPOXY PREPREG ON JOINING SECTION BETWEEN CFRP HIGH TORSION PROPELLER FILAMENT WINDING SHAFT AND METALLIC FLANGE

摘要

The present invention relates to a structure and a method for reinforced laminating a fabric type carbon/epoxy prepreg on a connecting part between a propeller filament winding shaft and a metal flange. The purpose of the present invention is to provide the structure and the method for reinforced laminating the fabric type carbon/epoxy prepreg on the connecting part between the propeller filament winding shaft and the metal flange, the structure and the method which are not concerned about breakage of a notch due to fiber damage caused by torsional strength when performing a process of processing holes for assembly pins in the propeller filament winding shaft and a metal power transmission flange portion. According to the present invention, the structure includes: a carbon/epoxy filament which is primarily wound on the connecting part between the propeller filament winding shaft and the metal flange; the fabric type carbon/epoxy prepreg which is primarily reinforced laminated on the carbon/epoxy filament; the carbon/epoxy filament which is again secondly wound on the fabric type carbon/epoxy prepreg; the fabric type carbon/epoxy prepreg which is again secondly reinforced laminated on the carbon/epoxy filament; and the carbon/epoxy filament which is finally thirdly wound on the fabric type carbon/epoxy prepreg to form the surface of a laminate.