The invention relates to a hybrid power system, a tilt-rotor aircraft and a control method.The hybrid power system comprises a power device, a main speed reducer, a reversing speed reducer, a transmission part, a transmission shaft and a tail end speed reducer, and the power device is connected with the main speed reducer through the transmission part; an output shaft of the main speed reducer is connected with the reversing speed reducer; one end of the transmission shaft is connected with the reversing speed reducer, and the other end of the transmission shaft is connected with the tail end speed reducer. Through the combined action of the hybrid power system and the transmission system, the maximum power requirement of the tilt-rotor aircraft during vertical take-off and landing is met, the maximum power requirement during forward flight at the highest speed is met, and meanwhile the cruise flight requirement of the tilt-rotor aircraft during long endurance is met. The overall structure is compact, the overall power-to-weight ratio of the system is high, and expansibility and high reliability are achieved.
本发明涉及一种本发明的混合动力系统、倾转旋翼飞行器和控制方法,所述混合动力系统包括动力装置、主减速器、换向减速器、传动部件、传动轴和末端减速器,其中,所述动力装置通过所述传动部件连接所述主减速器;所述主减速器的输出轴连接所述换向减速器;所述传动轴的一端连接所述换向减速器,另一端连接所述末端减速器。本发明通过混合动力系统与传动系统的共同作用,解决了倾转旋翼飞行器垂直起降时的最大功率需求问题,以及最高速前飞时的最大功率需求,同时满足倾转旋翼飞行器长航时的巡航飞行要求。本发明整体结构紧凑,系统总体功重比高,具备拓展性与较高的可靠性。
Hybrid power system, tilt-rotor aircraft and control method
一种混合动力系统、倾转旋翼飞行器和控制方法
21.06.2022
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |