Patent ID: 8163219
Filing Date: 2012-04-24
Classification: B29C,B29D,B29L,Y10T

Abstract:
1. A method for molding a helicopter rotor blade wherein said rotor blade includes a spar that extends parallel to the longitudinal axis of said rotor blade, said longitudinal axis extending from the root of said rotor blade to the tip of said rotor blade, said spar having interior surfaces that defines a spar cavity that also extends longitudinally from the root of said rotor blade to the tip of said rotor blade, said spar interior surfaces including a leading edge surface that comprises an upper leading edge portion and a lower leading edge portion, a trailing edge surface that comprises an upper trailing edge portion and a lower trailing edge portion, an upper surface that extends between said leading edge upper portion and said trailing edge upper portion and a lower surface that extends between said leading edge lower portion and said trailing edge lower portion, said method comprising the steps of: A) providing a mandrel that comprises: B) applying uncured composite material to the exterior surface of said mandrel to form an uncured spar; C) collapsing said collapsible support structure; D) removing said mandrel from said spar cavity; and E) curing said uncured spar.