The hybrid propulsion system for a multi-engine aircraft includes a plurality of free-turbine engines, each having a gas generator, among which at least a first engine, or hybrid engine, is suitable for operating in at least one standby mode during stabilized flight of the aircraft, while other engines of the plurality of engines operate alone during such stabilized flight. The hybrid engine is associated with first and second identical electric powertrains, each including a respective electrical machine capable of operating as a starter and as a generator, itself connected to a respective electronic power module, itself selectively connected to a specific electrical power supply network, such as an onboard network, and to a respective at least one electrical energy storage member. Each of the electric powertrains is adapted to deliver maximum power not less than half the total power needed for rapid reactivation of the hybrid engine.
ГИБРИДНАЯ СИЛОВАЯ УСТАНОВКА МНОГОМОТОРНОГО ЛЕТАТЕЛЬНОГО АППАРАТА
2018-11-22
Patent
Elektronische Ressource
Russisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
ДВИГАТЕЛЬНАЯ УСТАНОВКА КОСМИЧЕСКОГО ЛЕТАТЕЛЬНОГО АППАРАТА И СПОСОБ
Europäisches Patentamt | 2018