| 摘要 |
The invention relates to a system for dissipating (10) regenerated electric energy produced by an electric actuator (1) of an aircraft, the dissipating system (10) including: a resistor (R); two switching arms (12, 13), each switching arm (12, 13) being connected in series with the resistor (R), the two switching arms (12, 13) being connected together in parallel, each switching arm (12, 13) including two switches (Q1, Q2, Q3, Q4) connected to one another in series, each switch (Q1, Q2, Q3, Q4) including two terminals and a control grid, each switch (Q1, Q2, Q3, Q4) being capable of being controlled by controlling the potential applied to the control grid (G1, G2, G3, G4) thereof; and measurement means (MM1, MM2, MM3, MM4) capable of measuring the voltage at the terminals of each switch (Q1, Q2, Q3, Q4). |
