Actuator for airplane, method of driving actuator for airplane, and actuator system for airplane
AssigneeNabtesco Corporation
InventorTsutomu Yasui
Life of this patent
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Abstract
An actuator includes an inverter, a stator, a movable part, a controller, an injector, a current detector, and an estimator. The inverter is driven by a power generated by the axial force of an engine, etc. The stator includes an armature coil driven by the inverter. The movable part applies a driving force to at least one of a rudder surface of a tailplane of the airplane, etc. The controller controls the inverter in accordance with a signal from a maneuvering system. The injector injects a high-frequency signal into the coil. The current detector detects a coil current. The estimator estimates a position of the movable part.
Claims10
An actuator for an airplane comprising:
- an inverter that is driven by a power of the airplane;
- a stator including an armature coil energized and driven by the inverter;
- a movable part that applies a driving force to at least one of a rudder surface of a tailplane of the airplane, a movable surface of a main wing, a landing gear that supports wheels for landing, and a liquid pump through magnetic interaction with the stator;
- a controller that controls an operation of the inverter in accordance with a command signal from a maneuvering system of the airplane;
- an injector that injects a high-frequency signal into the coil, the high-frequency signal having a waveform of one of a sinusoidal wave, a trapezoidal wave, a triangular wave, and a staircase wave that varies stepwise between three or more levels;
- a current detector that detects a coil current flowing through the coil;
- and
- an estimator that estimates a position of the movable part based on a component of the coil current detected by the current detector, the component being related to the high-frequency signal.
A method of driving an actuator for an airplane, comprising:
- given an actuator for an airplane including an inverter that is driven by a power of the airplane, a stator including an armature coil energized and driven by the inverter, a movable part that applies a driving force to at least one of a rudder surface of a tailplane of the airplane, a movable surface of a main wing, a landing gear that supports wheels for landing, and a liquid pump through magnetic interaction with the stator, and a controller that controls an operation of the inverter in accordance with a command signal from a maneuvering system of the airplane, injecting a high-frequency signal into the coil, the high-frequency signal having a waveform of one of a sinusoidal wave, a trapezoidal wave, a triangular wave, and a staircase wave that varies stepwise between three or more levels;
- controlling the operation of the inverter in accordance with a command signal from a maneuvering system;
- detecting a coil current flowing through the coil;
- and
- estimating a position of the movable part based on a component of the coil current detected in the detecting, the component being related to the high-frequency signal.
Dependencies are inferred from the claim text.