Damperless Helicopter Rotor Blade

The basic objective of this study is to achieve, for a realistics basic set of soft inplane, hingeless rotot configuration parameters, those relationships between and the practical ranges for blade aeroplastic couplings that achieve optimal inherent stability without the use of lead-lag dampers, while satisfying other equirements needed for practical application. This objective would be achieved first, by configurating an analysis system comprised of an air resonance analysis, an analysis for calculating elastic couplings, a constrained optimization program and a subprogram for calculating constraints and a suitably defined cost function and, second, by actually making the objective calculations.