The half-cycle crack growth theory was incorporated into the Ko closed-form aging theory to improve accuracy in the predictions of operational flight life of failure-critical aerostructural components. A new crack growth computer program was written for reading the maximum and minimum loads of each half-cycle from the random loading spectra for crack growth calculations and generation of in-flight crack growth curves. The unified theories were then applied to calculate the number of flights (operational life) permitted for B-52B pylon hooks and Pegasus adapter pylon hooks to carry the Hyper-X launching vehicle that air launches the X-43 Hyper-X research vehicle. A crack growth curve for each hook was generated for visual observation of the crack growth behavior during the entire air-launching or captive flight. It was found that taxiing and the takeoff run induced a major portion of the total crack growth per flight. The operational life theory presented can be applied to estimate the service life of any failure-critical structural components.
Incorporation of Half-Cycle Theory Into Ko Aging Theory for Aerostructural Flight-Life Predictions
2007
88 pages
Report
Keine Angabe
Englisch
Aircraft , Crack propagation , Aircraft structures , B-52 aircraft , Life(Durability) , Bristol-siddeley bs 53 engine , Air launching , Pylons , Stress distribution , Flight tests , Loads(Forces) , Flow charts , Failure analysis , Finite element method , Computer programs , Half-cycle theory , Ko aging theory , Aerostructural flight-life predictions
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