| 摘要 |
<p>The present invention relates to a method for controlling a polyphase synchronous machine (3), implemented to control the attitude of a spacecraft, said machine comprising at least one rotor, one stator, and a plurality N of phases (RA, RB, RC) electrically powered to generate a predetermined torque, said control method comprising a step of electrically powering the synchronous machine (3) based on a six-step control mode, wherein the phases (RA, RB, RC) are activated in pairs. The method comprises, during the powering step, for each rotor position (Φ), the steps of: obtaining the intensities of the currents traveling within the two active phases and in the phase that has just been deactivated; estimating a torque (C*) based on values of the intensities of the phase currents obtained; controlling the estimated torque (C*) according to a predefined torque set-point (Ccons).</p> |
