FIELD: engines and pumps.
SUBSTANCE: proposed device comprises engine electric supply circuit independent of aircraft onboard electric circuit and circuits of excitation, control or servo control of engine electrical hardware elements. Note here that engine electric supply circuit comprises: first bus 24 to distribute DC or AC voltages for circuits of excitation, control or servo control of engine electrical hardware first elements, second bus 30 to distribute DC or AC voltages for circuits of excitation, control or servo control of engine electrical hardware other elements that required higher electric power compared with that consumed by aforesaid first elements, and third bus that incorporates communication line to receive power from electric power source and connected with said first and second buses for electric power supply.
EFFECT: expanded operating performances and higher reliability.
11 cl, 9 dwg
