6 Previous work: Rotor Diagnostics using Fuselage Measurements Azzam & Andrew (1992, 1995) Ganguli, Chopra & Haas (1995-98) Passive generation of fixed frame loads Measurements relative blade position fuselage vibration Measurements in hover and forward flight Limitations: Limited detectability of small faults Neural net required to classify faults Forward flight condition measurements required Azzam & Andrew (1992, 1995) Ganguli, Chopra & Haas (1995-98) Passive generation of fixed frame loads Measurements relative blade position fuselage vibration Measurements in hover and forward flight Limitations: Limited detectability of small faults Neural net required to classify faults Forward flight condition measurements required Dissimilar blade model Seed fault Simulate response Measure tip displacement hub loads (vibs) Next flight condition Next fault Fault profile at each flight condition Train Neural Net
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