Finite State Inflow Model Augmented with Viscous Vortex Particle Method for Advanced Rotorcraft Configurations

Most existing finite state inflow models that are widely used in flight dynamics simulation are limited to only modeling single main rotor helicopters. Modern advanced rotorcraft configurations usually involve multiple main rotors (e.g., co-axial, tilt-rotor, etc.), ducted fans, auxiliary wings, etc.. Advances in rotor inflow modeling are needed to extend the current modeling capability to provide effective support for the design and development of advanced rotorcraft configurations. An innovative approach is proposed to develop an accurate formulation of a finite state rotor inflow solution for advanced rotorcraft configurations that is well suited for flight dynamics and control applications. The innovative methodology and implementation algorithms will be thoroughly described and tested. The feasibility of the proposed solution will be demonstrated and validated with examples in both the time and frequency domains.