Autorotation flight control system

A computer implemented method for guiding a pilot of a rotorcraft in simulated autorotation from a current state of simulated flight having a constrained optimal trajectory for autorotation to landing comprising the steps of:

• (a) determining the current state of the rotorcraft;
• (b) executing a guidance algorithm to compute the current constrained optimal trajectory of the rotorcraft for autorotation to landing;
• (c) executing the guidance algorithm to compute inputs for rotorcraft collective and pitch controls required to achieve the current optimal trajectory;
• (d) providing a visual guidance display including:
• (i) a symbol for the rotorcraft indicating the current pitch of the rotorcraft;
• (ii) a symbol representative of collective control position required to achieve the current optimal trajectory;
• (iii) a symbol representative of the current collective control position;
• (iv) a symbol representative of the pitch control required to achieve the current optimal trajectory;
• and
• (v) a symbol representative of the current pitch control;
• (d) providing the pilot visual cues where to currently position the collective control and the pitch control to follow the current optimal trajectory;
• (e) providing the pilot a visual preview of when and where to position the collective control and the pitch control at future times to follow the current optimal trajectory;
• (f) repeating steps (b) through (e) until landing occurs.

A helicopter guidance system for landing a simulated airborne helicopter following a partial or total helicopter engine power failure comprising:

• (a) state input signals representative of a current state of the helicopter;
• (b) control input signals representative of a current set of controls for the helicopter;
• (c) a helicopter guidance algorithm;
• (d) a computer adapted to;
• (i) receive the state input signals;
• (ii) receive the control signals;
• (iii) execute the guidance algorithm to compute an optimal current trajectory for a simulated landing of the helicopter;
• (iv) execute the guidance algorithm to compute current trajectory output signals representative of the optimal current trajectory;
• (v) execute the guidance algorithm to compute a set of current controls positioning required for the simulated airborne helicopter to achieve the optimal current trajectory;
• and
• (vi) execute the guidance algorithm to compute controls positioning output signals representative of the controls positioning required to achieve the optimal current trajectory;
• and
• (e) a visual guidance display including:
• (i) a symbol for the helicopter;
• (ii) indicators of the state of the helicopter;
• (iii) indicators of the controls positioning of the helicopter;
• (iv) indicators of control inputs required to achieve the optimal current trajectory;
• (v) visual cues for positioning of controls necessary to achieve the optimal current trajectory;
• and
• (vi) indicators of future positioning of controls required to achieve the optimal current trajectory.