초록 ▼

The present invention provides computer implemented methodology that permits the safe landing and recovery of rotorcraft following engine failure. With this invention successful autorotations may be performed from well within the unsafe operating area of the height-velocity profile of a helicopter b

The present invention provides computer implemented methodology that permits the safe landing and recovery of rotorcraft following engine failure. With this invention successful autorotations may be performed from well within the unsafe operating area of the height-velocity profile of a helicopter by employing the fast and robust real-time trajectory optimization algorithm that commands control motion through an intuitive pilot display, or directly in the case of autonomous rotorcraft. The algorithm generates optimal trajectories and control commands via the direct-collocation optimization method, solved using a nonlinear programming problem solver. The control inputs computed are collective pitch and aircraft pitch, which are easily tracked and manipulated by the pilot or converted to control actuator commands for automated operation during autorotation in the case of an autonomous rotorcraft. The formulation of the optimal control problem has been carefully tailored so the solutions resemble those of an expert pilot, accounting for the performance limitations of the rotorcraft and safety concerns.

대표청구항 ▼

What is claimed is: 1. 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;

What is claimed is: 1. 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.