A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines.
PROCÉDÉ ET ARCHITECTURE DE TRANSFERT D'ÉNERGIE OPTIMISÉ ENTRE UN MOTEUR AUXILIAIRE DE PUISSANCE ET LES MOTEURS PRINCIPAUX D'UN HELICOPTERE
METHOD AND ARCHITECTURE FOR TRANSFERRING ENERGY BETWEEN A PRINCIPAL AND AN AUXILIARY ENGINE IN AN HELICOPTER
METHODE UND ANORDNUNG ZUR ENERGIEÜBERTRAGUNG ZWISCHEN EINEM HAUPT- UND EINEM HILFSANTRIEB IN EINEM HUBSCHRAUBER
2018-10-17
Patent
Electronic Resource
French
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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