Multi-rotor aircraft propulsion system with reconfigurable electric network
In the field of multi-rotor rotary-wing aircraft a propulsion system for such an aircraft includes a reconfigurable electric network for supplying the electric motors driving the rotors. The system includes: a supply source, a supply bus connected to the supply source, at least four drive units each including an electric motor and its control circuit, and an electrical ring network including: an electrical line which is interrupted at each drive unit and whose ends are connected to the supply bus, and, for each drive unit, a first switch and a second switch that are connected between the control circuit and the electrical line, on either side of the interruption.
1. A propulsion system for multi-rotor rotary wing aircraft, comprising:
an electrical power source capable of outputting a power supply current,
an electrical power supply bus connected to the electrical power supply source,
at least four motor units, each motor unit comprising a control circuit, an electric motor connected to the control circuit and a propeller mechanically connected to a rotor of the electric motor, the control circuit being capable of supplying power to the electric motor from the power supply current output by the electrical power supply source, and
an annular electrical network capable of connecting each motor unit control circuit to the electrical power supply bus, the annular electrical network comprising:
an electrical line, having a first end and a second end connected to the electrical power supply bus, the electrical line being interrupted at each motor unit and comprising a first connection point at the first end and a second connection point at the second end, and
for each motor unit, a first switch and a second switch, the first switch connecting the motor unit control circuit to the first connection point of the electrical line, the second switch connecting said control circuit to the second connection point of the electrical line.
2. The propulsion system of claim 1 , wherein the annular electrical network also comprises a third switch for each motor unit, connecting the first connection point to the second connection point of the electrical line.
3. The propulsion system of claim 1 , also comprising a control unit of the annular electrical network, the control unit being arranged to control opening and closing of the switches of the annular electrical network as a function of the detection of electrical faults at motor units and/or the electrical line.
4. The propulsion system claim 1 , wherein the electrical power supply source comprises one or several electricity generating sets, each set comprising an internal combustion engine and an electricity generator, the electricity generator being mechanically coupled to a rotor of the internal combustion engine and being connected to the electrical power supply bus.
5. The propulsion system of claim 4 , wherein the electrical power supply source comprises a switch and/or a circuit breaker between each electricity generator and the electrical power supply bus.
6. The propulsion system of claim 1 , wherein the electrical power supply source comprises an electrical energy storage unit connected to the electrical power supply bus.
7. The propulsion system of claim 6 , wherein the electrical power supply source comprises a switch and/or a circuit breaker between the electrical energy storage unit and the electrical power supply bus.
8. The propulsion system of claim 1 , wherein the control circuit of each motor unit comprises a converter.
9. A multi-rotor rotary wing aircraft comprising a propulsion system according to claim 1 .