A fracture mechanics based life prediction procedure has been developed for hypersonic airframes subjected to thermomechanical load profiles. The analysis, which models crack growth behavior in metals, was incorporated into a computer routine named DAMAGE (Damage Analysis of Metals subjected to AGressive Environments). The accuracy of the procedure was determined by predicting the crack growth under thermomechanical load histories typical of advanced fighters and aerospace vehicles, then comparing those predictions with test results. Predictions made with the DAMAGE routine were within 20 percent of the test lives for 67 % of the combined thermomechanical load history tests performed. Limitations in the ability of this procedure to predict the test results were used to formulate recommendations for further modeling efforts and research. The work discussed in this paper was performed by McDonnel Aircraft Company under WRDC Contract F33615-86-C-3208, 'Damage Tolerance Analysis for Manned Hypervelocity Vehicles'. The period of performance was September 1986 through September 1989.
Thermomechanical fatigue analyses for monolithic materials
Thermomechanische Materialermüdungsuntersuchung monolithischer Materialien für Überschallflugzeuge
1990
15 Seiten, 21 Bilder, 12 Quellen
Aufsatz (Konferenz)
Englisch
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