High-power light-weight control power distribution circuit applied to spacecraft

The invention discloses a high-power light-weight control power distribution circuit applied to a spacecraft, and the circuit comprises a first MOS tube and a first magnetic latching relay, and the signal input end of the first magnetic latching relay is used for receiving an instruction pulse signal. The controlled end of the first magnetic latching relay controls the voltage difference between the source electrode and the grid electrode of the first MOS tube so as to control the on-off state of the first MOS tube to be kept, and the source electrode and the drain electrode of the first MOS tube are connected in series in the control power distribution circuit. The grid electrode of the first MOS tube is connected with a DC power supply through a first divider resistor, and is connected with the controlled end of the first magnetic latching relay through a second divider resistor. Based on a high-power and light-weight power supply and distribution framework combining a low-power relay and an MOS (Metal Oxid