In this paper, structural advantages relating to the fatigue-insensitive, tear-resistant behavior of fiber/metal laminates are discussed in the context of future aircraft design needs. High-altitude aircraft (41,000 feet plus) will have special fuselage design requirements because a rapid decompression could be lethal to passengers. The likelihood of such an incident would be significantly reduced by the use of fatigue-resistant materials.
A rational damage tolerance philosophy is proposed for fiber/metal laminate structures in order to ensure ultimate load capability throughout the design life with reduced inspection requirements compared to monolithic materials. Attributes of the proposed method are compared to conventional fatigue and damage tolerance approaches.
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