Real-time simulation system of the effects of rotor-wake generated aerodynamic loads of a hover-capable aircraft on the aircraft itself, and method thereof

摘要

A real-time simulation system of the aerodynamic loads generated by the wake of a rotor of a hover-capable aircraft on the aircraft itself is described, said system comprising: a cockpit seat; a simulated control device able to receive a simulated command to simulate a flight condition of the aircraft; a plurality of simulation devices able to generate a simulated representation of the flight condition; and a processing unit configured to receive a first signal associated with the command given via the control device and to generate a second control signal for the plurality of simulation devices associated with the simulated aerodynamic loads. The processing unit cyclically generates a vortex ring, associates one or more control points with the vortex ring, computes the velocity induced on the control points, moves and updates the vortex ring, and generates the second signal on the basis of the velocities induced on the control points.

主权项

1. A real-time simulation system of the effect of aerodynamic loads generated by the wake of a rotor of a hover-capable aircraft on the aircraft itself, comprising:
a cockpit seat for a pilot; at least one simulated control device of said aircraft, which is able to receive a simulated command from said pilot to simulate a flight condition of said aircraft; a plurality of simulation devices able to generate a simulated representation of said flight condition and perceptible from the cockpit seat; a processing unit configured to receive a first signal associated with said command given via said control device in input and to generate and output a second control signal for said plurality of simulation devices associated with said simulated aerodynamic loads; characterized in that said processing unit is further configured to execute a cycle comprising the steps of:
a) generating, with a given period and in a simulated flow field, a vortex ring with a radius associated with the value of the disc circumference of said rotor and with a velocity circulation proportional to the thrust of said rotor set by said pilot via said control device;b) associating one or more control points to said vortex ring;c) computing one or more velocities induced on said control points by the vortex ring present in said simulated flow field and an asymptotic speed (Vasin) of the air with respect to said aircraft;d) moving said vortex ring according to said velocities induced on said control points;e) updating said vortex ring after said movement step;f) computing the velocity induced on at least one point of interest of said aircraft on the basis of the velocities induced on said control points of said vortex ring present in the simulated flow field and said asymptotic speed (Vasin); andg) generating said second control signal on the basis of said velocities induced on said point of interest of said aircraft.