J. Serafini, F. Cardito, G. Bernardini, M. Gennaretti

DOI Number: N/A

Conference number: IFASD-2017-179

The effect of dynamic inflow modeling on helicopter aeromechanic simulation for stability, response and control purposes is investigated. Two different linear time-invariant in-flow models, extracted from high-fidelity aerodynamic simulations, are presented and applied. One provides the wake inflow as a function of rotor kinematic variables, while the second one gives the wake inflow dynamics forced by rotor loads. In both cases, first the involved transfer functions are identified through time-marching aerodynamic simulations, and then a rational-matrix formula is applied for their finite-state approximation. The resulting state-space dynamic inflow models are applied to helicopter response and stability analyses, showing that the aeromechanic transfer functions and poles predicted by kinematic-based and loads-based models are somewhat different, with those related to the loads-based inflow depending on the kinematic perturbation considered to synthesize the model. Both simulations present discrepancies with respect to those obtained by the widely-used Pitt-Peters dynamic inflow model.

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In Categories: 1.Events, IFASD 2017, Reduced Order Modeling
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