Reinforcement beam as well as method and fiber laminate for manufacturing the reinforcement beam

Abstract

Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

1 . A curved reinforcement beam comprising
 a synthetic material that is reinforced by at least one fiber laminate,   wherein the fiber laminate comprises at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction in a base portion of the reinforcement beam that is mainly subjected to shear forces and/or transverse forces,   wherein in a peripheral area of the fiber laminate, at least one further layer with a third fiber direction is arranged in an outer portion of the reinforcement beam that is mainly subjected to tensile forces and/or compression forces, and a base portion of the fiber laminate is capable of being draped,   wherein the base portion and the peripheral section of the fiber laminate define an angle of approximately 90 degrees, to form a reinforcement beam with an L-shaped cross section.   
     
     
         2 . The curved reinforcement beam according to  claim 1 , wherein the layers are each formed with a plurality of fibers that are arranged substantially in parallel and equidistantly to each other. 
     
     
         3 . The curved reinforcement beam according to  claim 1 , wherein the first fiber direction is in a range of +20 degrees to +70 degrees. 
     
     
         4 . The curved reinforcement beam according to  claim 1 , wherein the second fiber direction is in a range of −70.degrees to −20.degrees. 
     
     
         5 . The curved reinforcement beam according to  claim 1 , wherein the third fiber direction is substantially 0 degrees. 
     
     
         6 . The curved reinforcement beam according to  claim 1 , wherein the reinforcement beam is bent at least twice by approximately 90 degrees in the area of the base portion, to form a curved reinforcement beam having a Z-shaped or a C-shaped cross section. 
     
     
         7 . The curved reinforcement beam according to  claim 1 , wherein the fiber laminate is formed with a plurality of fibers. 
     
     
         8 . The curved reinforcement beam according to  claim 7 , wherein the fiber laminate is formed with a multi-axial fiber laminate comprising at least one of carbon fibers, glass fibers and aramid fibers. 
     
     
         9 . The curved reinforcement beam according to  claim 1 , wherein the synthetic material is a curable synthetic material. 
     
     
         10 . The curved reinforcement beam according to  claim 9 , wherein the synthetic material is at least one of an epoxy resin, a polyester resin and a BMI resin. 
     
     
         11 . The curved reinforcement beam according to  claim 9 , wherein the curved reinforcement beam is a curved ring frame segment for fuselage cells of aircraft.