Sandwich Structure Having Arrestment Feature and Method of Making the Same

Abstract

A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

1 - 16 . (canceled) 
     
     
         17 . A method of making a composite sandwich structure, comprising:
 producing a core by forming joints between a plurality of core segments;   sandwiching the core between first and second facesheets, including joining the core to each of the facesheets; and,   forming an arrestment feature between the core and at least one of the facesheets along each of the joints.   
     
     
         18 . The method of  claim 17 , wherein forming an arrestment feature includes placing a composite wrap on each of the core segments along each of the joints. 
     
     
         19 . The method of  claim 17 , wherein placing the composite wrap on each of the core segments along each of the joints includes forming the wrap over at least portions of each of three sides of each of the core segments. 
     
     
         20 . The method of  claim 19 , wherein forming an arrestment feature includes placing a composite strap between the composite wrap and the at least one of the facesheets. 
     
     
         21 . The method of  claim 19 , wherein forming an arrestment feature includes applying a layer of adhesive between the wraps on adjacent facesheets of the core segments. 
     
     
         22 . (canceled) 
     
     
         23 . A method of making a composite sandwich structure for an aircraft, comprising:
 providing a plurality of core segments;   wrapping three sides of each of the core segments along the edges of the core segments with a fiber reinforced composite resin wrap;   assembling the wrapped core segments into a core, including forming joints between the core segments by arranging the core segments in edge-to-edge relationship and abutting the wraps on adjacent ones of the core segments;   introducing a layer of adhesive between the wraps along each of the joints;   forming a plurality of composite tear straps;   placing one of the tear straps over the wraps along each of the joints;   assembling the structure including sandwiching the core, the wraps and the tear straps between first and second facesheets; and,   curing the assembled structure.   
     
     
         24 . (canceled) 
     
     
         25 . The method of  claim 19 , wherein the composite wrap comprises a fiber reinforced resin material.