A helicopter rotor‐system damage detection methodology is formulated for an articulated rotor in hover, and in forward flight. Damages modeled are moisture absorption, loss of trim mass, misadjusted pitch‐link, damaged trailing‐edge flap, damaged pitch‐control
system and inoperative lag damper. These damages are represented by changes in mass, stiffness, damping and aerodynamic properties of the rotor blade. A rotor aeroelastic analysis based on finite element discretization in space and time, and capable of modeling dissimilar blades, is used to
simulate the undamaged and the damaged rotor. Changes in rotor system behavior are identified for the selected faults and tables of rotor system diagnostics are compiled. Rotor faults detectable from blade tip response include moisture absorption, misadjusted pitch‐link, damaged trailing‐edge
flap and damaged pitch‐control system. Rotor faults detectable from vibratory hub forces include moisture absorption, loss of trim mass, damaged pitch‐control system and damaged lag damper. Finally, rotor faults detectable from vibratory hub moments include misadjusted pitch‐link,
damaged trailing‐edge nap and damaged pitch‐control system.
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Document Type: Research Article
Center for Rotorcraft Education and Research, Department of Aerospace Engineering, University of Maryland, College Park, MD
Publication date: 1996-10-01
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