Abstract
Abstract The safety factor is widely used in aircraft design. Theoretically, design by using structural system reliability is much more reasonable than that based on the safety factor. However, because of the lack of the statistical data from the strength of materials used and the applied loads, design concepts based on the safety factor will still dominate for a period. The present safety factor for metallic aircraft structures is generally 1.5, but no final conclusions have yet been reached for the safety factor for composite structures. Several methods for determining the safety factor for composite structures are discussed in the paper. A technique based on structural system reliability is presented. This safety factor is influenced not only by the scatter of strength and exceptionally large loads but also the failure modes of the composite laminates. The paper also discusses the safety factor which provides the same reliability for composite structures as the 1.5 safety factor for the metallic structures. The value of the safety factor for aircraft structural design when using composite laminates is recommended.
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