Patent ID: 9377784
Filing Date: 2016-06-28
CPC Classification: B64C,G01C,G01P,G05D

Claim Text:
1. A method for controlling a nacelle angle of a tilt rotor assembly of a tilt rotor aircraft, comprising the following operations: converting a commanded groundspeed into a commanded airspeed by taking into account a pressure altitude of a tilt rotor aircraft and ambient air temperature; inputting said commanded airspeed to a speed versus nacelle angle schedule to obtain a nacelle angle that produces a favorable pitch attitude at a given airspeed in un-accelerated level flight of the tilt rotor aircraft; receiving or locally inferring, if not available, an inertial descent rate command from a flight management system or pre-planned maneuver for commanding an inertial descent rate of the tilt rotor aircraft; computing an adjusted nacelle angle command as a function of said inertial descent rate command; and controlling a conversion actuator of the tilt rotor aircraft in accordance with said adjusted nacelle angle command.