The present invention relates to a control system (34) for an aircraft hybrid propulsion system (5). The hybrid propulsion system (5) includes a gas turbine engine (10) coupled to a generator (28, 32), a propeller (12) coupled to an electric motor (28), and an electrical storage device (30) coupled to the motor (28) and the generator (32). The control system (34) is configured to operate the propulsion system (5) in one of a first descent mode and a second descent mode. In the first descent mode, for a given thrust, the gas turbine engine (10) operates at a first engine power level, and the generator (28, 32) operates at a first generator power level. In the second descent mode, for the given thrust, the gas turbine engine (10) operates at a second engine power level higher than the first engine power level, and the generator (28, 32) operates at a second generator power level higher than the first generator power level. The electrical power generated by the generator (28, 32) during operation in the second drop mode is stored in an electrical storage device (30).
一种用于飞行器混合推进系统(5)的控制系统(34)。该混合推进系统(5)包括联接到发电机(28,32)的气体涡轮引擎(10)、联接到电动马达(28)的推进器(12)、以及联接到马达(28)和发电机(32)的电储存装置(30)。该控制系统(34)被配置为以第一下降模式和第二下降模式中的一者操作推进系统(5)。在第一下降模式中,对于给定推力而言,气体涡轮引擎(10)以第一引擎功率水平操作,并且发电机(28,32)以第一发电机功率水平操作。在第二下降模式中,对于给定推力而言,气体涡轮引擎(10)以高于第一引擎功率水平的第二引擎功率水平操作,并且发电机(28,32)以高于第一发电机功率水平的第二发电机功率水平操作。由发电机(28,32)在以第二下降模式操作期间产生的电力储存在电储存装置(30)中。
Aircraft hybrid propulsion system
飞行器混合推进系统
2022-02-18
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |