Abstract: An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network.

Abstract: Voltage inverter provided with four switching cells (Q1 to Q4) to be connected to the terminals of a DC voltage source (Vdc), each comprising two semiconductor switches (I11, I12, I21, I22, I31, I32, I41, I42) installed in series, these switches having a common point (A0) to be connected to an AC current source (Mac) with three phases (p1, p2, p3) and a neutral (n), the connection being made onto one phase (p1, p2, p3) for three of the cells (Q1, Q2, Q3) and onto the neutral (n) for the fourth cell (Q4). Each cell (Q1 to Q4) cooperates with a semiconductor electrical isolating device (S1, (S2.1 and S2.2)) to be put into a turn-off state if the cell should fail, this isolating device (S1, (S2.1 and S2.2)) being arranged either on the connection to the AC current source (Mac), or on connections to the terminals of the DC voltage source (Vdc).