Anti-backlash flight control actuator system
A rotor blade pitch actuator has a first and second motor configured to control the rotor blade pitch. An actuator control system is configured to drive the first and second motor such that backlash is either eliminated from the system or minimized to an acceptable level.
1. An aircraft rotor blade pitch actuator operationally coupled to a rotor blade of an aircraft rotor, the aircraft rotor blade pitch actuator comprising:
a first motor configured to drive a first pinion gear;
a second motor configured to drive a second pinion gear;
a ring gear; and
an actuator control system comprising at least one processor configured to execute software instructions to cause the actuator control system to command the first motor to drive the first pinion gear in a first direction against the ring gear to change a blade pitch angle of the rotor blade while commanding the second motor to drive the second pinion gear in a second direction against the ring gear to reduce backlash.
2. The aircraft rotor blade pitch actuator of claim 1 , wherein the actuator control system uses a signal from a rotary position sensor to compute a signal to change the blade pitch angle a commanded amount and maintain sufficient force against the ring gear to minimize backlash.
3. The aircraft rotor blade pitch actuator of claim 1 , wherein the rotor blade pitch actuator is configured for use on a tilt-rotor aircraft.
4. The aircraft rotor blade pitch actuator of claim 1 , wherein the aircraft rotor is configured for individual blade control.
5. The aircraft rotor blade pitch actuator of claim 1 , wherein the first motor comprises a brushless DC motor.
6. The aircraft rotor blade pitch actuator of claim 1 , wherein the ring gear is heat treated.
7. The aircraft rotor blade pitch actuator of claim 1 , further comprising a slip ring configured to provide power and control signals to the first motor and the second motor.
8. The aircraft rotor blade pitch actuator of claim 1 , wherein the first pinion gear and the second pinion gear comprise at least one of: a spur gear, a helical gear, a miter gear, a worm gear, a screw gear, a rack and pinion gear, or a beveled gear.
9. The aircraft rotor blade pitch actuator of claim 1 , wherein the ring gear comprises at least one of: a spur gear, a helical gear, a miter gear, a worm gear, a screw gear, a rack and pinion gear, or a beveled gear.
10. The aircraft rotor blade pitch actuator of claim 1 , wherein the actuator control system is further configured to, in the event of a failure of the first motor or the first pinion gear, command the second motor to drive the second pinion gear against the ring gear to change the blade pitch angle.
11. A method for controlling a blade pitch angle of a rotor blade, comprising:
receiving, from an aircraft controller, a command to change the blade pitch angle;
receiving, from at least one sensor, a first position of a first motor and a second position of a second motor;
determining a first command for the first motor and a second command for the second motor based on the received first position and the received second position;
commanding the first motor by the first command to drive a first pinion gear in a first direction against a ring gear to change the blade pitch angle; and
commanding the second motor by the second command to drive a second pinion gear in a second direction against the ring gear to maintain an opposing force to reduce backlash.
12. The method of claim 11 , further comprising:
after commanding the first and second motors, receiving, from the at least one sensor, a third position of the first motor and a fourth position of the second motor.
13. The method of claim 11 , wherein the aircraft controller is further configured to, in the event of a failure of the first motor or the first pinion gear, command the second motor to drive the second pinion gear against the ring gear to change the blade pitch angle.