Despite the limited formability of Fibre Metal Laminates (FMLs), most structural components for a stiffened wing or fuselage structure can be manufactured. In general the applicable manufacturing processes are a combination of conventional processes used for sheet metal parts and laminating principles used for composites. The formability of Glare is related to the different failure modes that may occur. These failure modes are related to the constituents of the laminates and the layup of the laminates. Despite the limited formability, the manufacture of stringers does not pose a problem, as has been demonstrated by extensive research. On the other hand, in-plane deformations of Glare laminates and the related forming processes, such as stretch forming, are affected by the limited failure strains of Glare.
KeywordsFailure Mode Metal Layer Failure Strain Monolithic Material Transverse Shear Stress
Unable to display preview. Download preview PDF.
- E. Atzema, Formability of sheet metal and sandwich laminates, Master Thesis, University of Twente, 1994.Google Scholar
- N.J. Pagano ed., Interlaminar response of composite materials, Elsevier, 1989.Google Scholar
- E. Kroon, Manufacturing Glare stringers, status report, report B2V-00-05, Delft University of Technology, Delft, January 2000.Google Scholar
- E. Kroon, Brake form concept for Glare 2A laminates, report TD-R-00-008, Structural Laminates Industries, Delft, September 2000.Google Scholar