Electric airplane variable pitch propeller mechanism and electric airplane

Abstract

The application belongs to the technical field of electric aircrafts, and particularly relates to a variable-pitch propeller mechanism of an electric aircraft and the electric aircraft, which comprises a fairing, a plurality of propellers, a propeller rotating assembly and a propeller variable-pitch assembly. The propeller rotating assembly is rotationally connected to the root of each propeller through a first bearing to drive the propeller to rotate. In the propeller variable-pitch assembly, the output end of a linear motor is connected to one end of a guide rod, the other end of the guide rod is axially clamped and radially rotationally connected to a transmission rod, the other end of the transmission rod is vertically provided with a transmission branch rod, the end of the transmission branch rod is provided with a transmission butt joint disc, an arc-shaped groove is arranged on the transmission butt joint disc, the root of the propeller is provided with a variable-pitch butt joint disc, a variable-pitch connecting column is arranged on the variable-pitch butt joint disc, and the variable-pitch connecting column is matched in the arc-shaped groove. The application can monitor and adjust the pitch of the propeller in real time during flight to adapt to different flight stages and environmental conditions, and improve the overall performance and reliability of the electric aircraft.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of electric aircraft, and particularly relates to an electric aircraft variable-pitch propeller mechanism and an electric aircraft. BACKGROUND

[0002] With the continuous development of electric aircraft technology, the demand for improving the performance and efficiency of aircraft is increasing. Traditional internal combustion engine driven aircraft usually use fixed or mechanically adjustable propellers, but with the rise of electric propulsion technology, new energy electric aircraft also need to carry electric propeller propulsion systems to improve flight efficiency. Currently, some existing variable-pitch propeller mechanisms and control systems have problems such as complexity, high cost, and low efficiency. In order to maximize the performance of electric aircraft, an innovative electric aircraft propeller mechanism capable of realizing variable-pitch control and a corresponding variable-pitch propeller control system are needed to solve the above problems and meet the high performance requirements of electric aircraft. SUMMARY

[0003] In order to solve the above technical problems, the present application provides an electric aircraft variable-pitch propeller mechanism and an electric aircraft.

[0004] The present application is implemented in this way, providing an electric aircraft variable-pitch propeller mechanism, comprising a fairing, a plurality of propellers, a propeller rotating assembly, and a propeller variable-pitch assembly. The rear section of the fairing is provided with a number of mounting holes equal to the number of propellers along the circumference. Each mounting hole is provided with a propeller. The propeller rotating assembly is rotatably connected to the root of each propeller through a first bearing, driving the propeller to rotate. The propeller variable-pitch assembly comprises a linear motor, a guide rod, and a transmission rod. The output end of the linear motor is connected to one end of the guide rod. The other end of the guide rod is axially clamped and radially rotatably connected to the transmission rod. The other end of the transmission rod is provided with a number of transmission struts equal to the number of propellers. The end of the transmission strut is provided with a transmission docking disc. An arc-shaped groove is provided on the transmission docking disc. The root of the propeller is provided with a variable-pitch docking disc. A variable-pitch connecting column is provided on the variable-pitch docking disc. The variable-pitch connecting column is matched in the arc-shaped groove and can move along the wall of the arc-shaped groove.

[0005] Preferably, the propeller rotating assembly comprises a hub, a brushless motor rotor, a magnetic flux coil, and a brushless motor stator. One end of the hub is rotatably connected to the root of each propeller through the first bearing. The other end of the hub is fixedly connected to the brushless motor rotor. The magnetic flux coil is provided inside the brushless motor rotor. The magnetic flux coil is fixedly connected to the brushless motor stator.

[0006] Further preferably, the position of the first bearing installed on each propeller is provided with a snap ring structure away from one side of the transmission rod. The hub is arranged between the variable-pitch docking disc and the snap ring structure.

[0007] Further preferably, the transmission rod passes through the center of the brushless motor rotor, and the magnetic flux coil is rotationally connected to the inner side of the brushless motor rotor through a third bearing.

[0008] Preferably, the guide rod is provided with an annular clamping groove at one end away from the linear motor, the transmission rod is provided with an annular clamping block at the end close to the guide rod, the clamping block is installed in the clamping groove, and a second bearing is arranged between the clamping block and the inner wall of the clamping groove.

[0009] Preferably, the variable pitch propeller control system comprises a main control system, an air speed meter, a grating angle encoder, a motor monitoring system and a battery management system which are signal connected to and send signals to the main control system, and a storage battery, a brushless motor driver, a linear motor driver and a display instrument, the storage battery is bidirectionally connected to the battery management system and unidirectionally connected to the main control system to supply power to the main control system, the main control system is connected to the brushless motor driver and the linear motor driver to send control signals to the brushless motor driver and the linear motor driver, the brushless motor driver and the linear motor driver control the operation of the brushless motor and the linear motor respectively, the brushless motor controls the rotation of the propeller through the rotation of the brushless motor rotor, the linear motor controls the variable pitch of the propeller, the variable pitch information is monitored through the grating angle encoder, the state information of the brushless motor is monitored through the motor monitoring system, and the main control system sends information to be displayed to the display instrument.

[0010] Further preferably, the grating angle encoder comprises a grating and an encoder, the grating is arranged on the side of the variable pitch butt joint disc to monitor the rotational displacement of the variable pitch butt joint disc, the grating transmits the rotational displacement of the variable pitch butt joint disc to the encoder, and the encoder transmits the rotational displacement of the variable pitch butt joint disc to the main control system.

[0011] The application also provides an electric airplane, and the electric airplane variable pitch propeller mechanism is arranged in front of the nose and the wing of the electric airplane.

[0012] Preferably, the electric airplane is provided with a first wall plate and a second wall plate, the propeller rotation assembly is connected to the first wall plate through a first damping device, and the propeller variable pitch assembly is connected to the second wall plate through a second damping device.

[0013] Compared with the prior art, the application has the following advantages:

[0014] This invention provides a simple, low-cost, and highly efficient variable-pitch propeller mechanism for electric aircraft. By adjusting the propeller pitch during different flight phases, it maximizes the aircraft's flight efficiency, improves maneuverability, increases flight range, enhances flight stability, and makes aircraft control more flexible. Furthermore, the variable-pitch propeller control system improves flight safety, enhances short-takeoff and landing performance, and enables precise and rapid propeller pitch adjustment to adapt to different flight phases and environmental conditions, thereby improving the overall performance and reliability of the electric aircraft. Attached Figure Description

[0015] Figure 1 This is a cross-sectional view of the variable-pitch propeller mechanism for an electric aircraft provided in Example 1;

[0016] Figure 2 This is a structural diagram of the transmission rod in Example 1;

[0017] Figure 3 This is a structural diagram showing the docking position between the transmission rod and the root of the propeller in Example 1;

[0018] Figure 4 This is a simplified three-dimensional diagram of the variable-pitch propeller mechanism for an electric aircraft provided in Example 1;

[0019] Figure 5 This is a block diagram of the control system for the variable-pitch propeller mechanism of an electric aircraft provided in Example 1;

[0020] Figure 6 The diagram shows the structure of the electric aircraft provided in Example 2. Detailed Implementation

[0021] The following section will provide a more detailed description of the dynamic characteristics analysis method for rigid-flexible coupled box structures made of composite materials through specific implementation examples.

[0022] Example 1

[0023] refer to Figures 1-5The embodiment provides an electric airplane variable-pitch propeller mechanism, which comprises a fairing 1, a plurality of propellers 2, a propeller rotating assembly and a propeller variable-pitch assembly, the rear section of the fairing 1 is provided with a plurality of mounting holes in the circumferential direction, the number of the mounting holes is the same as that of the propellers 2, one propeller 2 is arranged in each mounting hole, the propeller rotating assembly is rotationally connected to the root of each propeller 2 through a first bearing 4, and drives the rotation of the propeller 2; the propeller variable-pitch assembly comprises a linear motor 12, a guide rod 11 and a transmission rod 10, the output end of the linear motor 12 is connected to one end of the guide rod 11, the other end of the guide rod 11 is axially clamped and radially rotationally connected to the transmission rod 10, the other end of the transmission rod 10 is vertically provided with a plurality of transmission branch rods, the number of the transmission branch rods is the same as that of the propellers 2, the end of each transmission branch rod is provided with a transmission butt joint disc 24, an arc-shaped groove 25 is arranged on the transmission butt joint disc 24, the root of each propeller 2 is provided with a variable-pitch butt joint disc 26, a variable-pitch connecting column 27 is arranged on the variable-pitch butt joint disc 26, and the variable-pitch connecting column 27 is matched in the arc-shaped groove 25 and can move along the wall of the arc-shaped groove 25.

[0024] In the working process of the electric airplane variable-pitch propeller mechanism, the plurality of propellers 2 are driven to rotate by the propeller rotating assembly, so as to provide a pulling force for the forward movement of the electric airplane; the propeller variable-pitch assembly controls the variable pitch of the propellers 2 through the following process: the linear motor 12 generates linear power on the guide rod 11, the guide rod 11 transmits the linear power to the transmission rod 10, the transmission rod 10 also moves linearly, and drives the arc-shaped groove 25 on the transmission butt joint disc 24 to move linearly; due to the movement of the arc-shaped groove 25 and the rotationally connected form of the propellers 2 and the propeller rotating assembly, the variable-pitch connecting column 27 moves in the arc-shaped groove 25, so that the angle of the propeller 2 changes, the pitch of the propeller 2 changes, and the distance of the electric airplane driven to move forward by one rotation of the propeller 2 is changed.

[0025] As a specific implementation mode of the propeller rotating assembly, the propeller rotating assembly comprises a hub 3, a brushless motor rotor 5, a magnetic flux coil 6 and a brushless motor stator 7, one end of the hub 3 is rotationally connected to the root of each propeller 2 through the first bearing 4, the other end is fixedly connected to the brushless motor rotor 5, the magnetic flux coil 6 is arranged in the brushless motor rotor 5, and the magnetic flux coil 6 is fixedly connected to the brushless motor stator 7.

[0026] In the process of driving the propeller 2 to rotate, the brushless motor rotor 5 of the brushless motor rotates under the action of the brushless motor stator 7 and the magnetic flux coil 6, so as to drive the hub 3 to rotate, the hub 3 drives the propeller 2, the fairing 1 and the transmission rod 10 to rotate, so as to make the propeller 2 provide a pulling force for the forward movement of the electric airplane.

[0027] In order to reasonably install the clamp hub 3, so that the position of the clamp hub 3 on the propeller 2 does not change, the position of each propeller 2 where the first bearing 4 is installed is away from the side of the transmission rod 10, and a snap ring structure is arranged between the variable pitch butt joint disc 30 and the snap ring structure.

[0028] As a specific connection mode between the transmission rod 10, the brushless motor rotor 5, and the magnetic flux coil 6, the transmission rod 10 passes through the center of the brushless motor rotor 5, and the magnetic flux coil 6 is rotationally connected to the inner side of the brushless motor rotor 5 through the third bearing 28.

[0029] In the working process, the brushless motor rotor 5 rotates, driving the transmission rod 10 and the clamp hub 3 to rotate synchronously, and the magnetic flux coil 6 remains stationary due to the arrangement of the third bearing 28.

[0030] As a specific connection mode between the guide rod 11 and the transmission rod 10, the guide rod 11 is provided with an annular clamping groove at the end away from the linear motor 12, the transmission rod 10 is provided with an annular clamping block at the end close to the guide rod 11, the clamping block is installed in the clamping groove, and a second bearing 29 is arranged between the clamping block and the inner wall of the clamping groove.

[0031] Through this connection structure, the linear drive of the linear motor 12 can be transmitted to the transmission rod 10 through the guide rod 11, and during the rotation of the transmission rod 10, the rotation torque will not be transmitted to the guide rod 11.

[0032] In order to accurately control the variable pitch of the propeller 2, as an improvement, a variable pitch propeller control system is further included, which includes a main control system 22, an air speed meter 15, a grating angle encoder 16, a motor monitoring system 17, and a battery management system 18 which are signal connected to the main control system 22 and send signals to the main control system 22, and further includes a storage battery 19, a brushless motor driver 20, a linear motor driver 21, and a display instrument 23, the storage battery 19 is bidirectionally connected to the battery management system 18 and unidirectionally connected to the main control system 22 to supply power to the main control system 22, the main control system 22 is connected to the brushless motor driver 20 and the linear motor driver 21 to send control signals to the brushless motor driver 20 and the linear motor driver 21, the brushless motor driver 20 and the linear motor driver 21 control the operation of the brushless motor and the linear motor 12 respectively, the brushless motor controls the rotation of the propeller 2 through the rotation of the brushless motor rotor 5, the linear motor 12 controls the variable pitch of the propeller 2, the variable pitch information is monitored by the grating angle encoder 16, the state information of the brushless motor is monitored by the motor monitoring system 17, and the main control system 22 sends the information to be displayed to the display instrument 23.

[0033] When the pitch of the propeller 2 is controlled by the pitch control system, the airspeed meter 15 measures the airspeed perceived when the electric aircraft is moving forward and transmits the information to the main control system 22, the pitch of the propeller 2 is monitored by the grating angle encoder 16, and the pitch information is transmitted to the main control system 22. The main control system 22 adjusts the forward speed of the electric aircraft and adjusts the appropriate pitch to ensure that the propeller obtains the optimal flight performance and fuel efficiency in different flight stages by controlling the brushless motor driver 20 and the linear motor driver 21 to drive the brushless motor and the linear motor 12 according to the airspeed and the pitch.

[0034] The performance of the brushless motor is monitored and managed by the motor monitoring system 17, and the condition of the battery 19 is monitored by the battery management system 18. These information is transmitted to the main control system 22 for real-time monitoring and management. The main control system 22 displays some information that needs to be displayed through the display instrument 23.

[0035] As a specific setting method of the grating angle encoder 16, the grating angle encoder 16 includes a grating 31 and an encoder. The grating 31 is arranged on the side of the pitch interface disc 26 to monitor the rotational displacement of the pitch interface disc 26. The grating 31 transmits the rotational displacement of the pitch interface disc 26 to the encoder, and the encoder transmits the rotational displacement of the pitch interface disc 26 to the main control system 22.

[0036] Embodiment 2

[0037] Reference Figure 6 The embodiment provides an electric aircraft, which is provided with the electric aircraft pitch propeller mechanism of embodiment 1 in front of the nose and the wing.

[0038] In order to better connect the pitch propeller mechanism and the electric aircraft, the first wall plate 9 and the second wall plate 14 are arranged on the electric aircraft, the propeller rotating assembly is connected to the first wall plate 9 through the first damping device 8, and the propeller pitch assembly is connected to the second wall plate 14 through the second damping device 13.

Claims

1. An electrically powered aircraft variable pitch propeller mechanism, characterised in that, The propeller rotating assembly includes a hub (3), a brushless motor rotor (5), a magnetic flux coil (6) and a brushless motor stator (7), one end of the hub (3) is rotatably connected to the root of each propeller (2) through the first bearing (4), the other end is fixedly connected to the brushless motor rotor (5), the brushless motor rotor (5) is internally provided with the magnetic flux coil (6), the magnetic flux coil (6) is fixedly connected to the brushless motor stator (7), in the process of driving the propeller (2) to rotate, the brushless motor rotor (5) of the brushless motor rotates under the action of the brushless motor stator (7) and the magnetic flux coil (6), thereby driving the hub (3) to rotate, and the hub (3) drives the propeller (2), the fairing (1) and the transmission rod (10) to rotate; The position, where each propeller (2) is installed with the first bearing (4), away from the side of the transmission rod (10) is provided with a snap ring structure, and the hub (3) is arranged between the variable-pitch adapter disc (26) and the snap ring structure; The transmission rod (10) passes through the center of the brushless motor rotor (5), and the magnetic flux coil (6) and the inner side of the brushless motor rotor (5) are rotatably connected through a third bearing (28); One end of the guide rod (11) away from the linear motor (12) is provided with an annular clamping groove, and the end of the transmission rod (10) close to the guide rod (11) is provided with an annular clamping block, the clamping block is installed in the clamping groove, and a second bearing (29) is arranged between the clamping block and the inner wall of the clamping groove; ​ The variable pitch propeller control system comprises a main control system (22), an air speed meter (15), a grating angle encoder (16), a motor monitoring system (17) and a battery management system (18) which are in signal connection with the main control system (22) and send signals to the main control system (22), and further comprises a storage battery (19), a brushless motor driver (20), a linear motor driver (21) and a display instrument (23), the storage battery (19) is in bidirectional connection with the battery management system (18) and unidirectional connection with the main control system (22) to supply power to the main control system (22), the main control system (22) is connected with the brushless motor driver (20) and the linear motor driver (21) to send control signals to the brushless motor driver (20) and the linear motor driver (21), the brushless motor driver (20) and the linear motor driver (21) control the operation of the brushless motor and the linear motor (12) respectively, the brushless motor controls the rotation of the propeller (2) through the rotation of the brushless motor rotor (5), the linear motor (12) controls the variable pitch of the propeller (2), the grating angle encoder (16) monitors the variable pitch information, the motor monitoring system (17) monitors the state information of the brushless motor, and the main control system (22) sends the information to be displayed to the display instrument (23).

2. An electrically powered aircraft variable pitch propeller mechanism according to claim 1, characterised in that, The grating angle encoder (16) comprises a grating (31) and an encoder, the grating (31) is arranged on the side of the variable pitch butt joint disc (26) to monitor the rotational displacement of the variable pitch butt joint disc (26), the grating (31) transmits the rotational displacement of the variable pitch butt joint disc (26) to the encoder, and the encoder transmits the rotational displacement of the variable pitch butt joint disc (26) to the main control system (22).

3. An electrically powered aircraft characterised in that, The electric aircraft variable pitch propeller mechanism of any one of claims 1-2 is arranged in front of the nose and the wing of the electric aircraft.

4. The electrically powered aircraft of claim 3, wherein, The electric aircraft is provided with a first wall plate (9) and a second wall plate (14), the propeller rotation assembly is connected with the first wall plate (9) through the first damping device (8), and the propeller variable pitch assembly is connected with the second wall plate (14) through the second damping device (13).

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