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US 12,441,465 B2Granted
Anti-backlash flight control actuator system
AssigneeArcher Aviation Inc.
InventorBernard Ahyow
Life of this patent
Estimating the term…
Abstract
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.
Claims13
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 more elements
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.
3 more elements
Dependencies are inferred from the claim text.