Patent ID: 7861969
Filing Date: 2011-01-04
Classification: B29C,B29L,B64C,Y02T,Y10T

Abstract:
1. A stiffened skin panel of an aircraft comprising: a composite aircraft skin panel; and a composite stringer consolidated with the aircraft skin panel, the stringer comprising a first stringer side and a second stringer side, wherein the first stringer side extends from a stringer top through a first stringer leg and a second stringer side extends from the stringer top through a second stringer leg, the first stringer side and second stringer side each extending in a continuous curve from the stringer top through a respective stringer leg, and wherein the curve of each stringer side is characterized by at least one inflection point such that the curve of each stringer side is further characterized by at least a first convex section and at least a first concave section.