The Structural Reliability of Airframes

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Report Number: AFML TR 64-401
Author(s): Payne, A. O., Freudenthal, A. M.
Corporate Author(s): Columbia University
Laboratory: AF Materials Laboratory
Date of Publication: 1964-12
Pages: 95
Contract: AF 33(616)-7042
DoD Project: 7351 - Metallic Materials
DoD Task: 735106 - Behavior of Metals
Identifier: AD0615654

The theory of reliability estimation developed in previous reports (WADD TR61-53, ML-TDR-64-300) has been applied to three types of aircraft, a civilian transport, a heavy bomber and a fighter designed by current procedures, for which operational records, multiple structural tests and records of service experience are available. Failure rates for critical ultimate load conditions have been evaluated on the basis of data obtained from various sources and compared with service experience. Lives associated with equal risk of ultimate load failure and fatigue failure (or initial structural fatigue damage) have also been computed. The obtained numerical values which reflect current design practices can serve as the basis for a rational comparative reliability analysis of new designs involving new materials and different design criteria and missions psectra and profiles.

Provenance: Bombardier/Aero

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