A Parametric Study of Real Time Mathematical Modeling Incorporating Dynamic Wake and Elastic Blades

In this paper, a finite-state dynamic wake theory is combined with blade element model for rotor modeling in helicopter real time flight simulation. A parametric study of the effects of incorporating dynamic wake and elastic blades to a real time rotorcraft mathematical model is discussed. The representation of the wake dynamics is a closed-form, first-order, ordinary differential equation in time. In this application, the induced flow modeling up to a second harmonic variation is implemented. Results for rigid and elastic blade models, while varying induced flow degree of freedom are presented. Correlation of the results with flight test data is provided to assess the inflow dynamics and rotor blade dynamics modeling effects.