Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1995-01-10
1997-01-14
Carone, Michael J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
244 328, F42B 1064
Patent
active
055931090
ABSTRACT:
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.
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Carone Michael J.
Lucas Western Inc.
Montgomery Christopher K.
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