Actuator system and method
US5593109A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jan 10, 1995 |
| Grant date | Jan 14, 1997 |
| Priority date | — |
| Expiry date | Jan 10, 2015 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF42B10/64
- WIPO fieldControl
- WIPO sectorInstruments
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 shaf…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.