| 摘要 |
Disclosed are a torque sensing method and apparatus for a control wing of a guide type munition, in which a control wing 100 is fixed to a first jig, and a wing surface of a control wing is clamped and fixed by using a second jig to measure a driving torque of the control wing by using a torque meter 23 coaxially connected to a rotation shaft of the second jig. An oscillograph for displaying a voltage signal generated by a twist due to a difference between a first rotation motion and a second rotation motion in real-time and a digital indicator 17 for converting the voltage signal into a torque value to display the converted torque valve are connected to the torque meter 23 through a wire, and the digital indicator 17 operates to sense a peak value of the torque value, thereby displaying the sensed peak value as a fixed value. The rotation motion of the torque meter 23 is converted into a reciprocation motion by a crank 30 and a connecting rod 31, and the reciprocation motion is converted into a third rotation motion including an oscillation motion and then is transmitted into the fly wheel 40. The ply wheel has inertial resistance with respect to the oscillation to apply various resistant forces to the control wing. In this process, since an external force similar to a force in an actual flying situation is applied, a motor driving controller may transmit realistic driving torque and rotation rate information to a wing motor on the basis of the applied external force. The present invention may practically measure the driving torque of the control wing in various kinds of guide type munitions. The results measured through the above-described processes may largely help optimization in design of the guide type munition as well as selection of a required specification and a reduction gear ratio. [Reference numerals] (AA) Wing module/reduction gear; (BB) Wing root |
