In the prior art, due to the existence of counterweight, the weight of a whole multi-rotor aircraft is increased, and thus the effective load of the whole machine is reduced. In order to overcome the shortage mentioned above, a dual bevel gear transmission system is provided, and the system is provided with two output shafts, wherein two output shafts are in the same axis, rotate at the same time, and rotate in opposite directions. The system comprises a No.1 bevel gear, a No.2 bevel gear, a No.3 bevel gear, a No.4 bevel gear, a first output shaft, a second output shaft, a dynamic source, a small bevel gear, a No.1 rotor, and a No.2 rotor. The work principle is as follows: dynamic is input by the dynamic source and is directly transmitted to the first output shaft, the first output shaft drives the No.1 rotor to rotate; at the same time, the dynamic is transmitted to the No.3 bevel gear through the engaging between No.1 bevel gear and No.2 bevel gear/No.4 bevel gear to drive the No.3 bevel gear to rotate, then the dynamic is transmitted to the second output shaft, the second output shaft drives the No.2 rotor to rotate, and thus the first output shaft and second output shaft are in the same axis, rotate at the same time, and rotate in opposite directions. The system has the advantages that the engine main shaft and the propeller shaft are in the same axis, the functions of co-axis, synchronous rotation, and reverse rotation direction, can be achieved, thus the effective load of aircraft is increased, and the handling performance is improved.
Multi-rotor aircraft dual bevel gear dynamic transmission system
2016-02-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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