Flexible mandrel for highly contoured composite stringer

Details Flexible mandrel for highly contoured composite stringer Flexible mandrel for highly contoured composite stringer

2011-03-08

2011-03-08

Tolin, Michael A (Department: 1745)

Adhesive bonding and miscellaneous chemical manufacture

Methods

Surface bonding and/or assembly therefor

C156S285000

Reexamination Certificate

active

07901531

ABSTRACT:
An aircraft stringer lay-up assembly is provided comprising a contoured curing block and a first mandrel element positioned thereon. The first mandrel assembly includes a first bar assembly having a plurality of rigidity reducing first slots formed along a first mandrel length. The plurality of rigidity reducing first slots protruding partially through a first mandrel depth of the first mandrel element to allow the first bar assembly to conform to the contoured curing block. A composite ply assembly is laid up onto the first mandrel element and cured while conformed to said contoured curing block such that a contoured composite stringer element is generated.

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“Manufacture of Advanced Carbon Fiber Reinforced Advanced Composite Structure With Toughened Epoxy Systems, + 350 F Cure”, Boeing Process Specification BAC 5578, Oct. 1, 1985, The Boeing Company, U.S.

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