Certification of composite primary structures for use in commercial aerospace transports requires demonstration of structural integrity in the presence of through penetration damage. A novel structural design concept is described that facilitates satisfaction of this structural integrity requirement with near zero weight penalty. The concept involves the use of tear straps of very high orthotropy (at least 60% fiber in a single orientation) that halt catastrophic progression of discrete source damage by forcing a failure mode change. To predict this failure mode change, an analytical methodology was developed based on separate examination of shear and normal strain failure indices at the damage tip. Initial failure loads in modes that are normal strain dominated are predicted using the point strain failure criterion. The methodology is validated through testing of five tear strap laminates subject to uniaxial tension.
Stiffness tailoring of tension loaded composite panels to contain crack-like damage
2000
9 Seiten, 15 Quellen
Conference paper
English
Stiffness Tailoring of Tension-Loaded Composite Panels to Contain Damage
British Library Conference Proceedings | 2000
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