The Australian Defence Force (ADF) operates rotary and fixed-wing aircraft in a different manner from the way that the aircraft manufacturers envisaged. That is, the usage spectra of the ADF aircraft are different from the usage spectra assumed by the aircraft manufacturer during design. The effects of perturbing the amount of time spent in flight conditions on both component fatigue damage and life-cycle costs are investigated in this report. An 'amplification factor' is developed, which allows the effect of varying the amount of time spent in different flight conditions on both damage and cost to be determined. These amplification factors give both qualitative ('importance' ordering) and quantitative (sensitivity) information regarding all flight conditions. The resulting procedure is both easy to implement and use, and allows the operator to determine the effects of different spectra on both damage and cost. The outlined procedures will lead to cost savings and safety improvement for the ADF for both rotary and fixed-wing aircraft.
Usage Spectrum Perturbation Effects on Helicopter Component Fatigue Damage and Life-Cycle Costs
2000
40 pages
Report
No indication
English
Aircraft , Logistics Military Facilities & Supplies , Helicopters , Life cycle costs , Fatigue(Mechanics) , Fixed wing aircraft , Flight testing , Manufacturing , Military aircraft , Damage , Amplification , Australia , Rotary wing aircraft , Aircraft design , Usage spectrum perturbation effects , Foreign reports , Adf(Australian defence force) , S-70a-9m aircraft , Black hawk helicopter
Component Fatigue Life Reliability with Usage Monitor
British Library Conference Proceedings | 2007
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Online Contents | 2008
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NTIS | 1981
Helicopter transmission fatigue life estimation
AIAA | 1988
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