WO2006076647B1

WO2006076647B1 - Autorotation flight control system

Info

Publication number: WO2006076647B1
Application number: PCT/US2006/001347
Authority: WO
Inventors: Edward N Bachelder; Dong-Chan Lee; Bimal Aponso
Original assignee: Systems Technology Inc; Edward N Bachelder; Dong-Chan Lee; Bimal Aponso
Priority date: 2005-01-14
Filing date: 2006-01-13
Publication date: 2007-08-16
Also published as: WO2006076647A2; WO2006076647A3

Abstract

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.

Claims

AMENDED CLAIMS received by the International Bureau on 11 October 2006 (11.10.2006)

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; (d) providing the pilot visual cues where to currently position the collective control and the pitch control to follow the current optimal trajectory;

80 (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.

2. 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

81 (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.

3. The helicopter guidance system of claim 1 in which the symbol for the helicopter is a representation of a side view of the helicopter and of the head and of the tail of the helicopter.

4. The helicopter guidance system of claim 1 in which the indicators of the state of the helicopter are anchored to the symbol for the helicopter.

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5. The helicopter guidance system of claim 1 in which the symbol for the helicopter is adapted to pitch with the pitch of the helicopter during landing.

6. The helicopter guidance system of claim 1 further including a series of horizontal lines representative of an altimeter readout as one of the indicators of the state of the helicopter.

7. The helicopter guidance system of claim 1 further including a rotary pointer and numerical display as indicators of the helicopter's rotor speed.

8. The helicopter guidance system of claim 2 further including a variable length vector extending from the symbol of the helicopter head as one of the indicators of the helicopter's forward speed.

9. The helicopter guidance system of claim 2 further including a variable length vector extending from the helicopter tail as one of the indicators of the helicopter's vertical speed.

10. The helicopter guidance system of claim 1 further including a collective range setting indicator scale and a collective indicator as indicators of the position of the collective relative to 0% and to 100% collective positions.

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11. The helicopter guidance system of claim 10 further including a rotor blade stall limit indicator corresponding to the helicopter's rotor blade stall limit.

12. The helicopter guidance system of claim 1 further including a time line representative of collective guidance commands for collective position over time as one of the indicators of control inputs required to achieve the optimal current trajectory.

13. The helicopter guidance system of claim 1 further including a time line representative of pitch guidance commands for pitch position over time as one of the indicators of control inputs required to achieve the optimal current trajectory.

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