Unmanned Aerial Vehicle (UAV)
An unmanned aerial vehicle (UAV) having a UAV body, a propeller, an engine, a motor and a battery. The engine includes an engine body and an engine output shaft arranged on the engine body. The motor includes a stator, a rotor and a stator connector. The UAV provides the motor rotor, propeller and engine output shaft to be coaxially connected, and the motor can be used as a generator to charge the battery by doing negative work on the engine output shaft, or as an electric motor, that is, to receive the power of the battery and do positive work on the engine output shaft to realize power output, so that the UAV can realize high energy utilization and power redundancy at the same time.
1 . An unmanned aerial vehicle, which is characterized by comprising:
a UAV body and a propeller ( 10 ) arranged on the UAV body;
an engine ( 20 ), comprising an engine body ( 21 ) and an engine output shaft ( 22 ) arranged on the engine body ( 21 ); the engine body ( 21 ) is arranged on the UAV body;
a motor ( 30 ), comprising a stator ( 31 ), a rotor ( 32 ) and a stator connector ( 33 ) for connecting the stator ( 31 ) and the rotor ( 32 ); the stator connector ( 33 ) is arranged on the engine body ( 21 ), and the rotor ( 32 ) is coaxially arranged on the engine output shaft ( 22 ); the propeller ( 10 ) is coaxially arranged on the rotor ( 32 );
a battery, which is connected to the motor ( 30 ), and can be discharged to provide electric energy to the motor ( 30 ) or receive the electric energy output by the motor ( 30 ) for charging; A damping device ( 40 ), which is connected to the engine ( 20 ) and comprises damping guide channels ( 41 a , 41 b , 41 c , 41 d ) which includes a first guide channel ( 41 a ), a second guide channel ( 41 b ), a third guide channel ( 41 c ) and a forth guide channel ( 41 d );
the damping guide channel is arranged divergently from the central axis of the damping device body. The adjacent damping device guide channels ( 41 a , 41 b , 41 c , 41 d ) form a preset included angle with each other, and are used to disperse and weaken the vibration generated by the engine during operation.
2 . The UAV according to claim 1 , which is characterized in that the engine ( 20 ) is a two-stroke engine.
3 . The UAV according to claim 2 , which is characterized in that the motor ( 30 ) is a permanent magnet synchronous motor.
4 . The UAV according to claim 1 , which is characterized in that a preset included angle of 30 degrees to 150 degrees is formed between the guide channels of the adjacent damping devices.
5 . The UAV according to claim 1 , which is characterized in that the propeller is a multi-blade thrust propeller.
6 . The UAV according to claim 5 , which is characterized in that the UAV body is composed of carbon fiber composite materials.
7 . The UAV according to claim 1 , which is characterized in that the engine ( 20 ) and the motor ( 30 ) are connected to the UAV body through sound-absorbing materials.
8 . The UAV according to claim 7 , which is characterized in that the engine ( 20 ) and the motor ( 30 ) are connected to the UAV body through highly expanded polyethylene sound-absorbing material.
9 . The UAV according to claim 1 , which is characterized in that the UAV further comprises:
An engine controller, which is used to receive the control command of the control board and output an execution signal to the engine ( 20 ), is electrically connected to the engine ( 20 );
A motor controller, which is used to receive the control command of the control board and output the execution signal to the motor ( 30 ), is electrically connected to the motor ( 30 ).