The influence of vortex ring state (VRS) on rotorcraft flight
dynamics is investigated, specifically the vertical velocity drop
of helicopters and the roll-off of tiltrotors encountering VRS. The
available wind tunnel and flight test data for rotors in vortex
ring state are reviewed. Test data for axial flow, non-axial flow,
two rotors, unsteadiness, and vortex ring state boundaries are
described and discussed. Based on the available measured data, a
VRS model is developed. The VRS model is a parametric extension of
momentum theory for calculation of the mean inflow of a rotor,
hence suitable for simple calculations and real-time simulations.
This inflow model is primarily defined in terms of the stability
boundary of the aircraft motion. Calculations of helicopter
response during VRS encounter were performed, and good correlation
is shown with the vertical velocity drop measured in flight tests.
Calculations of tiltrotor response during VRS encounter were
performed, showing the roll-off behavior characteristic of
tiltrotors. Hence it is possible, using a model of the mean inflow
of an isolated rotor, to explain the basic behavior of both
helicopters and tiltrotors in vortex ring state.
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