The purpose of this study was to develop rational failsafe/safe-life interface criteria for the design of helicopter structural components. Present specifications containing design criteria were reviewed and deficient areas defined. Rational design criteria were developed and are titled 'Damage-Tolerant Design Criteria'. Damage-tolerant design concepts are presented for various helicopter structural components. They include redundant structure, controlled fracture structure and failure indicating systems. The Hughes OH-6A main rotor blade was selected as the structural component to establish the effects on life-cycle costs in designing to different structural criteria and using different damage-tolerant design concepts.
Failsafe/Safe-Life Interface Criteria
1975
96 pages
Report
Keine Angabe
Englisch
Kraftfahrwesen | 1979
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