초록 ▼

An actuator receives an input torque command and rotates an aeronautical surface within a prescribed range of motion. An output shaft is rigidly secured to the aeronautical surface, such that axial rotation of the output shaft results in displacement of the aeronautical surface. A drive motor contro

An actuator receives an input torque command and rotates an aeronautical surface within a prescribed range of motion. An output shaft is rigidly secured to the aeronautical surface, such that axial rotation of the output shaft results in displacement of the aeronautical surface. A drive motor controls rotation of the output shaft by applying a motive force thereto. A drive circuit controls the drive motor, to thereby control axial rotation of the output shaft, in response to keep input torque command. A torque sensor is operatively coupled to the drive shaft. The torque sensor measures output shaft rotational torque and provides an electronic representation of the output shaft rotational torque to the drive circuit. The drive circuit receives the electronic representation as a torque command feedback signal, and derives a torque error command as the difference between the input torque command and the output shaft rotational torque. When the aeronautical surface is within the range of motion, the drive circuit rotates the output shaft to compensate for the torque error command. When the aeronautical surface is not within the range of motion, the drive circuit rotates the output shaft to compensate for the torque error command only if the rotation moves the aeronautical surface closer to within the range of motion. This system may be applied of missiles or other aircraft. A separate actuator can be applied to each missile fin.

대표청구항 ▼

A method for controlling motion of an aeronautical device using at least one aeronautical surface that provides lift within a prescribed range of motion, an input torque command provided by a guidance system, an electronic drive circuit, a motor controlled by the drive circuit, an output shaft that

A method for controlling motion of an aeronautical device using at least one aeronautical surface that provides lift within a prescribed range of motion, an input torque command provided by a guidance system, an electronic drive circuit, a motor controlled by the drive circuit, an output shaft that rotates the aeronautical surface, and a torque sensor that senses torque in the output shaft, the method comprising: establishing a range of motion for said aeronautical surface; sensing rotational torque of the output shaft using the torque sensor and generating an electronic representation of that rotational torque; receiving both the electronic representation from the torque sensor and the input torque command, and computing a difference between the electronic representation and the input torque command to obtain a torque error command; generating a motor drive signal with the drive circuit in response to the torque error command; and using the motor to rotate the output shaft to compensate for the torque error command, at all times that the aeronautical surface is within said range of motion; and rotating the output shaft to compensate for the torque error command only if the rotation displaces the aeronautical surface closer to the range of motion, when the aeronautical surface is not within said range of motion.