PREDICTION OF ROTOR INSTABILITY AT HIGH FORWARD SPEEDS. VOLUME 1. STEADY FLIGHT DIFFERENTIAL EQUATIONS OF MOTION FOR A FLEXIBLE HELICOPTER BLADE WITH CHORDWISE MASS UNBALANCE
UNITED TECHNOLOGIES CORP STRATFORD CT SIKORSKY AIRCRAFT DIV
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The differential equations of motion for a linearly twisted rotor blade having chordwise mass unbalance and operating under steady flight conditions are derived. The motions include flapping and lagging for the articulated blade, as well as flatwise, edgewise, and torsional deformations for the articulated and nonarticulated blades. The fully coupled aerodynamic forcing functions are based on quasi-steady theory. The differential equations of motion are expanded in terms of the uncoupled vibratory modes of the blade in order to facilitate their numerical solution on a digital computer.
- Fluid Mechanics