| CPC B64C 29/0033 (2013.01) [B64C 13/18 (2013.01); B64C 13/22 (2013.01)] | 19 Claims |
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1. A method for automatic rotor tilt control comprising:
gathering or receiving, as inputs:
airspeed of an aircraft or a commanded airspeed for the aircraft;
acceleration of the aircraft or a commanded acceleration for the aircraft;
pitch attitude of the aircraft and pilot pitch bias commands for the aircraft; and
an aircraft rotor tilt angle;
calculating, from one or more of the airspeed of the aircraft, the commanded airspeed for the aircraft, the acceleration of the aircraft, the commanded acceleration for the aircraft, the pitch attitude of the aircraft and the pilot pitch bias commands for the aircraft, a commanded rotor tilt angle for the aircraft;
calculating, from the aircraft rotor tilt angle and the commanded rotor tilt angle, a rotor tilt angle error for the aircraft;
calculating, from the rotor tilt angle error, a rotor tilt rate command for the aircraft; and
at least one of:
determining if the commanded rotor tilt angle is within a threshold of a predetermined discrete tilt angle during unaccelerated flight, and commanding the rotor tilt angle to the predetermined discrete tilt angle in response to the commanded rotor tilt angle being within the threshold of the predetermined discrete tilt angle during unaccelerated flight; and
determining if the commanded rotor tilt angle error and/or tilt rate command is below a threshold, and inserting a deadband in the commanded rotor tilt angle error and/or tilt rate, to zero out tilt rate command in response to the commanded rotor tilt angle error and/or tilt rate command being below the threshold.
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