| 摘要 |
<p>The architecture has an electric power distribution unit (710) with an electric power calibrating unit that is in the shape of a controlled inverter (711), where the inverter serves to calibrate the electric power provided from a power bus (PW1) of an aircraft. The power distribution unit has a changeover switch (712) to selectively direct the calibrated power towards one of left and right electromechanical actuators (401, 402).</p> |
