Patent ID: 7976310

Claim:
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; (e) providing the pilot visual cues where to currently position the collective control and the pitch control to follow the current optimal trajectory; (f) 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; (g) repeating steps (b) through (e) until landing occurs.