Patent ID: 7968169
Filing Date: 2011-06-28
Classification: B29C,B29D,B29K,B29L,B64C,Y02T,Y10T

Abstract:
1. A structural component usable in an aircraft comprising: a body formed from a plurality of composite plies, each composite ply having unidirectional fibers, the body having a longitudinal axis and a cross section perpendicular to the longitudinal axis, the cross section varying along at least a portion of the longitudinal axis to provide the body with at least one uniform contour profile portion and at least one compound contour profile portion; a first side flange of the body having a substantially linear portion along the axial length; a second side flange of the body having a substantially linear portion and a non-linear portion along the axial length forming the compound contour profile; a web of the body, the web positioned between the first side flange and the second side flange; wherein the first side flange is positioned opposite the second side flange and wherein the first side flange and second side flange are disposed substantially normal to the web; and the plurality of composite plies including composite plies having unidirectional fibers oriented substantially parallel to the longitudinal axis, the composite plies having unidirectional fibers oriented substantially parallel to the longitudinal axis comprising first and second composite ply portions, the first composite ply portion forming the uniform contour profile portion and the second composite ply portion forming the compound contour profile portion.