An aircraft (100) includes a gas turbine engine (108), an electric motor (110), and a propulsion device (112). The gas turbine engine (108) and the electric motor (110) are configured to provide a target cumulative output to the propulsion device (112). An electronic control unit (106) is configured to: set a gas turbine engine (108) in a first engine mode to provide a first engine output to a propulsion device (112); setting the electric motor (110) in a first motor mode to provide a first motor output to the propulsion device (112), the sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output; and in response to the speed of the aircraft (100) reaching the target speed and the first engine output increasing to the second engine output, setting the motor (110) to a second motor mode.
一种飞行器(100)包括燃气涡轮发动机(108)、电动机(110)和推进装置(112)。燃气涡轮发动机(108)和电动机(110)被构造为向推进装置(112)提供目标累积输出。一种电子控制单元(106)被构造为:将燃气涡轮发动机(108)设置为第一发动机模式以向推进装置(112)提供第一发动机输出;将电动机(110)设置为第一电动机模式以向推进装置(112)提供第一电动机输出,第一发动机输出和第一电动机输出的总和在目标累积输出的预定范围内;并且响应于飞行器(100)的速度达到目标速度并且第一发动机输出增加到第二发动机输出,将电动机(110)设置为第二电动机模式。
Aircraft, system and method for providing constant torque at takeoff
用于在起飞时提供恒定扭矩的飞行器、系统和方法
2024-03-05
Patent
Elektronische Ressource
Chinesisch
AIRCRAFTS, SYSTEMS, AND METHODS FOR PROVIDING CONSTANT TORQUE ON TAKEOFF
Europäisches Patentamt | 2024
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