| 摘要 |
The invention relates to the execution of an architecture capable of rationalising the chain of electric components of an aircraft. The chain of components for transmitting electric power of an aircraft comprises an auxiliary power unit (APU) (10), main engines and end consumer systems (ECS) via power networks (R1, R2; LP1, LP2) and electronic links (EP1, EP2) controlled by a unit (U1). The APU (10) supplies power to a shaft (5a, 5) by a link (P1-P7; 14a, 15a; 14b, 15b; AF1-AF4) to at least one energy conversion unit (MC1, MC2), via a gearbox (8), each conversion unit comprising only one convertible electromechanical component (13a, 13b). The transmission of power takes place by a direct link to the gearbox (8) and to the end consumer system (ECS). The link between a converter unit (MC1, 11a, 13a; MC2, 11b, 13b) and the APU (10) is provided by coupling the shaft (5a, 5) of the APU (10) with the shaft (14a, 14b) of the starter/generator (13a, 13b) by directional power transmission (RL1-RL2-RL3) operating in one direction only (F1, F2, F3) from the shaft of the APU (10) to the shaft (14a, 14b) of the SG (13a, 13b). |
