Finite State Induced Inflow Model Extracted from Viscous Vortex Particle Method for Advanced Rotorcraft Configurations

Existing finite state inflow models used in flight dynamics simulation and analysis are mostly limited to only modeling single main rotor helicopters. Modern advanced rotorcraft configurations usually involve multiple main rotors (e.g., co-axial), ducted fans, wings, etc.. Advances in rotor inflow dynamics modeling are needed in order to extend the current modeling capability to provide an effective support for the design and development of advanced rotorcraft configurations. An innovative formulation and approach is proposed to develop an advanced finite state rotor inflow solution well suited for future vertical lift aircraft flight dynamics and control applications. In Phase I, the feasibility of the proposed solution has been demonstrated and validated with examples in both the time and frequency domains. The proposed Phase II will significantly extend the scope for a full development of the unified state-space inflow model as demonstrated in Phase I. This includes the enhancement of the model formulation and the corresponding model parameter extraction method. The Phase II effort will also include the integration of the inflow model with a full flight rotorcraft simulation program to carry out a full range of flight dynamics and control analysis with extensive model testing and validations.