Pitch control system
AssigneeSikorsky Aircraft Corporation
InventorsKevin L. Bredenbeck, Bryan S. Cotton, Mark K. Wilson
Life of this patent
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Abstract
A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position.
Claims5
A method of adjusting a pitch of a plurality of propeller blades comprising:
- measuring an airspeed and rotor revolutions per minute;
- determining in response to the airspeed, rotor revolutions per minute, and at least one discrete logical value, whether to operate a control system for adjusting the pitch of the plurality of propeller blades in a slew mode or a track mode;
- wherein the at least one discrete logical value is selected from the pitch control system command, an increase/decrease thrust command, latched switch fail, latched loop close switch, and dump valve activated;
- issuing a command to one or more actuators coupled to the propeller blades;
- and
- changing the pitch of the one or more propeller blades via the one or more actuators.
Dependencies are inferred from the claim text.