Abstract: A propulsion and motion-transmission assembly (1), in particular for a rotary-wing aircraft, the assembly (1) comprising: a first motor-reducer assembly (2); and a second motor-reducer assembly (4), wherein the first and second motor-reducer assemblies (2, 4) are arranged for driving in rotation at least one rotor of a rotary-wing aircraft; and wherein each of said first and second motor-reducer assemblies (2, 4) comprises:—a mechanical differential (6, 24) including a first input shaft (8; 26), a second input shaft (10; 28) and an output shaft (12, 30); and—a first electric motor (14; 32) and a second electric motor (16; 34) connected, respectively, to said first and second input shafts (8, 10; 26, 28), the output shaft of each motor-reducer assembly being arranged for connection in rotation to a rotor of a rotary-wing aircraft.

Abstract: A propulsion and motion-transmission assembly (1), in particular for a rotary-wing aircraft, the assembly (1) comprising:—a first hydrostatic transmission (2) including a first fluid machine for converting mechanical energy into fluid energy (18) and a first fluid machine for converting fluid energy into mechanical energy (26);—a second hydrostatic transmission (8) including a second fluid machine for converting mechanical energy into fluid energy (62) and a second fluid machine for converting fluid energy into mechanical energy (70); and wherein each of said first and second hydrostatic transmissions (2, 8) comprises a high-pressure branch (24, 68) and a low-pressure branch (30, 74), which, in each of said first and second hydrostatic transmissions (2, 8), hydraulically connect the fluid machine.

Abstract: A propulsion and motion-transmission assembly (1), in particular for a rotary-wing aircraft, the assembly (1) comprising: a first motor-reducer assembly (2); and a second motor-reducer assembly (4), wherein the first and second motor-reducer assemblies (2, 4) are arranged for driving in rotation at least one rotor of a rotary-wing aircraft; and wherein each of said first and second motor-reducer assemblies (2, 4) comprises:—a mechanical differential (6, 24) including a first input shaft (8; 26), a second input shaft (10; 28) and an output shaft (12, 30); and—a first electric motor (14; 32) and a second electric motor (16; 34) connected, respectively, to said first and second input shafts (8, 10; 26, 28), the output shaft of each motor-reducer assembly being arranged for connection in rotation to a rotor of a rotary-wing aircraft.

Abstract: A propulsion and motion-transmission assembly (1), in particular for a rotary-wing aircraft, the assembly (1) comprising:—a first hydrostatic transmission (2) including a first fluid machine for converting mechanical energy into fluid energy (18) and a first fluid machine for converting fluid energy into mechanical energy (26);—a second hydrostatic transmission (8) including a second fluid machine for converting mechanical energy into fluid energy (62) and a second fluid machine for converting fluid energy into mechanical energy (70); and wherein each of said first and second hydrostatic transmissions (2, 8) comprises a high-pressure branch (24, 68) and a low-pressure branch (30, 74), which, in each of said first and second hydrostatic transmissions (2, 8), hydraulically connect the fluid machine.