The safe fatigue life of helicopter transmission components made if in service load data together with transmission fatigue data, represented as the number of cycles of failure as a function of tooth load, were estimated. Instrumentation was developed to provide in flight estimation and indication of the proportion of safe fatigue life expended for critical gears in single or twin engine helicopter transmission systems. Basic transmission load data in the form of totalized times spent in a number of contiguous torque bands are continually updated and stored during flight. The basic load data together with values of life expenditure for critical gears for the current flight are printed out after flight. This technique opens the way towards fatigue life monitoring of individual transmissions. The special demands of the life estimating system and in particular the very significant effects of errors in mean torque estimation are assessed.
in-Flight Estimation and Indication of Cumulative Fatigue Damage to Helicopter Gears
1984
113 pages
Report
Keine Angabe
Englisch
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