Connector and connection method for multi-rotor aircraft motor and arm

Abstract

The present invention provides a connector and a connection method between a motor and an arm of a multi-rotor aircraft, which relates to the technical field of motor installation of aircraft. It includes a base, a locking disk component, and a guiding and positioning component. One end of the forward locking disk structure is connected to the forward propeller motor, and the other end is inserted into the forward end of the base through the forward guiding and positioning structure and is threadedly connected to the forward end of the base through a forward thread. During the process of screwing into the root of the base, the guiding and positioning component ensures accurate installation and positioning of the motor, and the stator of the motor does not rotate, and the wire harness will not be entangled. One side of the base is connected to the arm, and both the motor and the arm of the multi-rotor aircraft are tightly locked and connected. One end of the reverse locking disk structure is connected to the reverse propeller motor, and the other end is inserted into the reverse end of the base through the reverse guiding and positioning structure and is threadedly connected to the reverse end of the base through a reverse thread. During the screwing process, the guiding and positioning component ensures accurate installation and positioning of the motor, and the stator of the motor does not rotate, and the wire harness will not be entangled.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft motor installation, and particularly to a connector and connection method for a motor and an arm of a multi-rotor aircraft. Background Art

[0002] When connecting the motor of a multi-rotor aircraft to the arm, the following problems are often faced: the connection between the motor and the arm is not firm, the connector between the motor and the arm is complex and bulky, and it is difficult to position the production and installation of the motor.

[0003] Currently, the connection between the motor of a multi-rotor aircraft and the arm is mostly based on a motor base, with bolts fixed radially or axially on the motor stator. However, during the operation of the propeller of a multi-rotor aircraft, complex aerodynamic forces, gyroscopic precession, vibration and other working conditions are coupled. The stiffness, strength and resonance of the connector between the motor and the arm occur. The method of fixing bolts radially on the motor stator makes it easy for bolts to loosen and break under the coupling of complex multi-physical fields in a multi-rotor aircraft.

[0004] To solve the above technical problems, a prior art discloses a double-insurance quick disassembly and assembly structure with interlocking buckles for a drone propeller, which is for the connection between the propeller and the motor upper cover, including a propeller fixing component, a motor fixing component and a positioning component. Through the first clamping block, the first clamping groove, the second clamping block, the second clamping groove, the locking plate, the movable shaft, the pull ring, the pagoda spring, the nut, the corrugated gasket, etc. inside the upper plate and the base, double fixation of the propeller and the motor upper cover is achieved. The double circumferential positioning of the first clamping block, the first clamping groove, the second clamping block and the second clamping groove inside the upper plate and the base can provide a high concentricity, and can also be used when the propeller generates pushing and pulling forces. The cooperation and fixation of the V-shaped convex blocks at both ends of the locking plate with the first V-shaped groove of the upper plate and the second V-shaped groove of the base reduce the radial clearance between the motor fixing component and the propeller fixing component, eliminating the risk of the propeller loosening during the forward and reverse rotation of the motor. However, due to the relatively fixed size of the motor, the space at the connection part of the motor fixing component is limited, resulting in difficulties in routing and leading out the thick motor wire harness and difficulties in operating the torque wrench for the motor base and the motor. Summary of the Invention

[0005] To solve the problems of difficult installation and positioning, insecure connection with the arm, complex connector and easy winding of the thick motor wire harness during the connection process between the motor of a multi-rotor aircraft and the arm, the present invention proposes a connector and connection method for the motor and the arm of a multi-rotor aircraft, which can not only achieve reliable installation of the motor of the multi-rotor aircraft, but also keep the motor stator from rotating during locking connection, avoiding the winding phenomenon of the motor wire harness routing and leading out.

[0006] To achieve the above technical effects, the technical solution of the present invention is as follows:

[0007] A connector for a multi-rotor aircraft motor and an arm, the connector comprising a base, a locking disc component, and a guiding and positioning component. One side of the base is connected to the arm. The locking disc component includes a forward locking disc structure and a reverse locking disc structure. The guiding and positioning component includes a forward guiding and positioning structure and a reverse guiding and positioning structure. The forward guiding and positioning structure and the reverse guiding and positioning structure are respectively embedded in the forward locking disc structure and the reverse locking disc structure. One end of the forward locking disc structure is connected to the forward propeller motor, and the other end is inserted into the forward end of the base through the forward guiding and positioning structure and is threadedly connected to the forward end of the base by a forward thread. One end of the reverse locking disc structure is connected to the reverse propeller motor, and the other end is inserted into the reverse end of the base through the reverse guiding and positioning structure and is threadedly connected to the reverse end of the base by a reverse thread.

[0008] The connector proposed in this technical solution includes a base, a locking disc component, and a guiding and positioning component. One end of the forward locking disc structure is connected to the forward propeller motor, and the other end is inserted into the forward end of the base through the forward guiding and positioning structure and is threadedly connected to the forward end of the base by a forward thread. Finally, it can be screwed into the root of the base by a customized torque wrench. During the screwing process, the guiding and positioning component ensures accurate installation and positioning of the motor, and the motor stator does not rotate, and the wire harness will not be entangled. One side of the base is connected to the arm, and both the multi-rotor aircraft motor and the arm are tightly locked and connected. One end of the reverse locking disc structure is connected to the reverse propeller motor, and the other end is inserted into the reverse end of the base through the reverse guiding and positioning structure and is threadedly connected to the reverse end of the base by a reverse thread. During the reverse screwing process, the guiding and positioning component ensures accurate installation and positioning of the motor, and the motor stator does not rotate, and the wire harness will not be entangled.

[0009] Preferably, the base includes a connecting frame and a sleeve. One end of the connecting frame is connected to the arm, and the other end of the connecting frame is perpendicularly connected to the sleeve. The forward end of the sleeve is threadedly connected to the forward locking disc structure by a forward thread, and the reverse end of the sleeve is threadedly connected to the reverse locking disc structure by a reverse thread. Overall, the threaded connection between the locking disc component and the base corresponds to the forward and reverse rotations of the propeller, ensuring that the torque of the locking disc component and the propeller cancels each other out when the propeller rotates, so as to prevent the locking disc component from loosening from the base.

[0010] Preferably, a plurality of inclined slot holes are provided on the sleeve.

[0011] Here, in the rotation direction of the multi-rotor aircraft motor rotor and the propeller, the motor stator receives a reaction force, and the reaction force received by the electronic stator is transmitted to the base. The forward end and the reverse end of the base respectively receive the reaction forces of the forward propeller motor and the reverse propeller motor, and the directions of the two reaction forces are opposite. The inclination direction of the inclined slot holes is set to be conducive to the bending and torsion resistance of the base.

[0012] Preferably, each of the forward locking disk structure and the reverse locking disk structure includes a locking disk joint. A platform extends radially from the inner wall of the sleeve along the sleeve axis on the locking disk body. A plurality of anti-rotation grooves are provided on the platform, and a plurality of anti-rotation bosses are provided on the locking disk joint. When the locking disk joint is sleeved on the locking disk body, the anti-rotation bosses are arranged in the anti-rotation grooves.

[0013] Here, the locking disk joint is provided with anti-rotation bosses, and the base is provided with a platform and anti-rotation grooves, so that the anti-rotation function can be realized before the forward locking disk structure / reverse locking disk structure is threadedly connected to the base. In this way, the locking disk joint can be stationary, while the forward locking disk structure / reverse locking disk structure can perform both axial spiral movement and radial rotation movement, realizing the threaded locking of the locking disk joint by the forward locking disk structure / reverse locking disk structure.

[0014] Preferably, a guiding and positioning groove is also vertically provided on the inner wall of the sleeve. The forward guiding and positioning structure and the reverse guiding and positioning structure respectively embedded in the forward locking disk structure and the reverse locking disk structure are guided into the sleeve through the guiding and positioning groove, realizing the precise installation of the motor.

[0015] Preferably, both the forward guiding and positioning structure and the reverse guiding and positioning structure adopt guiding and positioning pins.

[0016] Preferably, the locking disk joint in the forward locking disk structure is connected to the forward propeller motor by bolts, and the locking disk joint in the reverse locking disk structure is connected to the reverse propeller motor by bolts.

[0017] Here, after the locking disk joint is connected to the motor by bolts, the forward locking disk structure / reverse locking disk structure is threadedly connected and locked to the base. Under the action of the threaded locking force of the forward locking disk structure / reverse locking disk structure, there is a large enough frictional force between the end face of the locking disk joint and the base platform. Coupled with the anti-rotation bosses on the locking disk joint and the guiding and positioning structure in the guiding and positioning groove, it ensures the firm and reliable installation of the motor and the base.

[0018] Preferably, the connector further includes a plurality of anti-loosening components. A plurality of first fixing holes are provided on the outer side surface of the base, and a plurality of second fixing holes are provided on the locking disk body. Each anti-loosening component passes through a first fixing hole on the base and a second fixing hole on the locking disk body in sequence and then is locked, ensuring the firm and reliable installation of the motor and the base.

[0019] Preferably, the anti-loosening component is an anti-loosening fuse.

[0020] This application also proposes a connection method for a motor of a multi-rotor aircraft and an arm. The method includes the connection method for a forward multi-rotor aircraft motor and an arm and the connection method for a reverse multi-rotor aircraft motor and an arm that are carried out in sequence. The steps are as follows:

[0021] S1. Connect one end of the forward locking disk structure to the forward propeller motor, and insert the other end into the forward end of the base through the forward guiding and positioning structure, and connect it to the forward end of the base through forward threading;

[0022] S2. Connect one side of the base to the arm;

[0023] S3. Screw the forward locking disk structure into the root of the base by a customized torque wrench;

[0024] S4. Connect one end of the reverse locking disk structure to the reverse propeller motor, and insert the other end into the reverse end of the base through the reverse guiding and positioning structure, and connect it to the reverse end of the base through reverse threading;

[0025] S5. Screw the reverse locking disk structure into the root of the base by a customized torque wrench. Compared with the prior art, the beneficial effects of the technical solution of the present invention are:

[0026] The present invention provides a connector and a connection method for a multi-rotor aircraft motor and an arm. The connector includes a base, a locking disk component, and a guiding and positioning component. One end of the forward locking disk structure is connected to the forward propeller motor, and the other end is inserted into the forward end of the base through the forward guiding and positioning structure and is connected to the forward end of the base through forward threading, and is screwed into the root of the base. During the screwing process, the guiding and positioning component ensures accurate installation and positioning of the motor, and the motor stator does not rotate, and the wire harness will not be wound. One side of the base is connected to the arm, and both the multi-rotor aircraft motor and the arm are tightly connected. One end of the reverse locking disk structure is connected to the reverse propeller motor, and the other end is inserted into the reverse end of the base through the reverse guiding and positioning structure and is connected to the reverse end of the base through reverse threading. During the reverse screwing process, the guiding and positioning component ensures accurate installation and positioning of the motor, and the motor stator does not rotate, and the wire harness will not be wound. Description of the Drawings

[0027] Figure 1 It shows the overall structural schematic diagram of the connector for the multi-rotor aircraft motor and the arm proposed in Embodiment 1 of the present invention;

[0028] Figure 2 It shows the exploded view of the structure of the connector for the multi-rotor aircraft motor and the arm proposed in Embodiment 1 of the present invention;

[0029] Figure 3 It shows the cross-sectional view of the connector for the multi-rotor aircraft motor and the arm proposed in Embodiment 1 of the present invention;

[0030] Figure 4 It shows the schematic diagram of the rotation direction of the motor rotor and the direction of the reaction force received by the motor stator on the connector for the multi-rotor aircraft motor and the arm proposed in Embodiment 2 of the present invention;

[0031] Figure 5 Schematic flow diagram showing the connection between the motor and the arm of the multi-rotor aircraft proposed in Embodiment 3 of the present invention.

[0032] Wherein, 1 - base; 2 - lock disk component; 3 - guiding and positioning component; 21 - forward lock disk structure; 22 - reverse lock disk structure; 31 - forward guiding and positioning structure; 32 - reverse guiding and positioning structure; 11 - connecting frame; 12 - sleeve; 121 - inclined slot hole; lock disk joint - 201; lock disk body - 202; 122 - platform; 123 - anti-rotation groove; 203 - anti-rotation boss; 124 - guiding and positioning groove; 4 - anti-loosening component; 13 - first fixing hole; 204 - second fixing hole; 5 - anti-loosening external hexagon bolt. Detailed implementation mode

[0033] The accompanying drawings are only for illustrative purposes and should not be construed as a limitation of this patent;

[0034] To better illustrate this embodiment, some parts of the accompanying drawings will be omitted, enlarged or reduced, and do not represent the actual size;

[0035] For those skilled in the art, it is understandable that some well-known content descriptions in the accompanying drawings may be omitted.

[0036] The technical solutions of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0037] The description of the positional relationship in the accompanying drawings is only for illustrative purposes and should not be construed as a limitation of this patent;

[0038] Embodiment 1

[0039] As Figure 1 shown in Figure 2 this embodiment proposes a connector for the motor and the arm of a multi-rotor aircraft. This connector includes a base 1, a lock disk component 2, and a guiding and positioning component 3. One side of the base 1 is connected to the arm. The lock disk component 2 includes a forward lock disk structure 21 and a reverse lock disk structure 22. The guiding and positioning component 3 includes a forward guiding and positioning structure 31 and a reverse guiding and positioning structure 32. The forward guiding and positioning structure 31 and the reverse guiding and positioning structure 32 are respectively embedded in the forward lock disk structure 21 and the reverse lock disk structure 22. One end of the forward lock disk structure 21 is connected to the forward propeller motor, and the other end is inserted into the forward end of the base 1 through the forward guiding and positioning structure 31 and is threadedly connected to the forward end of the base 1 through a forward thread; one end of the reverse lock disk structure 22 is connected to the reverse propeller motor, and the other end is inserted into the reverse end of the base 1 through the reverse guiding and positioning structure 32 and is threadedly connected to the reverse end of the base 1 through a reverse thread.

[0040] See Figure 1, the base 1 includes a connecting frame 11 and a sleeve 12. One end of the connecting frame 11 is connected to the machine arm, and the other end of the connecting frame 11 is perpendicularly connected to the sleeve 12. The forward end of the sleeve 12 is threadedly connected to the forward locking disc structure 21, and the reverse end of the sleeve 12 is threadedly connected to the reverse locking disc structure 21 through a reverse thread.

[0041] In this embodiment, both the forward guiding and positioning structure 31 and the reverse guiding and positioning structure 32 adopt guiding and positioning pins.

[0042] See Figure 2 and Figure 3 , each of the forward locking disc structure 21 and the reverse locking disc structure 22 includes a locking disc joint 201 and a locking disc body 202. A platform 122 extends radially from the inner wall of the sleeve 12 along the axis of the sleeve 12. A plurality of anti-rotation grooves 123 are provided on the platform 122, and a plurality of anti-rotation protrusions 203 are provided on the locking disc joint 202. When the locking disc joint 202 is sleeved on the locking disc body 201, the anti-rotation protrusions 203 are arranged in the anti-rotation grooves 123.

[0043] The locking disc joint 201 is provided with anti-rotation protrusions 203, and the base 1 is provided with a platform 122 and anti-rotation grooves 123, so that the anti-rotation function can be realized before the forward locking disc structure 21 / reverse locking disc structure 22 is threadedly connected to the base 1. In this way, the locking disc joint 201 can be kept stationary, while the forward locking disc structure 21 / reverse locking disc structure 22 can perform both axial spiral movement and radial rotation movement, realizing the threaded locking of the locking disc joint by the forward locking disc structure 21 / reverse locking disc structure 22.

[0044] As Figure 3 shown, a guiding and positioning groove 124 is also vertically provided along the inner wall of the sleeve 12. The forward guiding and positioning structure 31 and the reverse guiding and positioning structure 32 respectively embedded in the forward locking disc structure 21 and the reverse locking disc structure 22 are introduced into the sleeve 12 through the guiding and positioning groove 124, which can ensure the precise installation of the motor.

[0045] The locking disc joint 201 in the forward locking disc structure 21 is connected to the forward propeller motor through a bolt 4, and the locking disc joint 201 in the reverse locking disc structure 22 is connected to the reverse propeller motor through a bolt 4. In this embodiment, the locking disc joint 201 is connected to the motor through a locknut external hexagonal bolt 5. The forward locking disc structure 21 / reverse locking disc structure 22 is threadedly connected and locked with the base 1. Under the action of the threaded locking force of the forward locking disc structure 21 / reverse locking disc structure 22, there is a large enough frictional force between the end face of the locking disc joint 201 and the platform of the base 1. Coupled with the anti-rotation protrusions 203 on the locking disc joint 201 and the guiding and positioning structure in the guiding and positioning groove 124, it ensures the firm and reliable installation of the motor and the base 1.

[0046] See Figure 2, this connector further includes several anti-loosening components 4. There are several first fixing holes 13 on the outer side surface of the base 1, and several second fixing holes 204 on the lock disk body 202. Each anti-loosening component 4 passes through a first fixing hole 13 on the base 1 and a second fixing hole 204 on the lock disk body 202 in sequence and then is tightened. In this embodiment, the anti-loosening component 4 is an anti-loosening fuse.

[0047] Embodiment 2

[0048] In this embodiment, based on the basic structure of the connector in Embodiment 1, it is proposed that there are several inclined slot holes 121 on the sleeve 12. Under the rotation direction of the motor rotor and the propeller of the multi-rotor aircraft, the motor stator receives a reaction force, and the reaction force received by the electronic stator is transmitted to the base 1. The forward end and the reverse end of the base 1 are respectively subjected to the reaction forces of the forward propeller motor and the reverse propeller motor. Figure 4 The figure shows a schematic diagram of the rotation direction of the motor rotor and the direction of the reaction force received by the motor stator on the connector between the motor of the multi-rotor aircraft and the arm. Among them, the "arrow" represents the general direction of the reaction force received by the motor stator. It can be seen that the directions of the two reaction forces are opposite, and Figure 3 it can be concluded that the setting of the inclination direction of the inclined slot holes 121 is beneficial to the bending and torsion resistance of the base.

[0049] Embodiment 3

[0050] As Figure 5 shown, in this embodiment, a connection method between the motor of the multi-rotor aircraft and the arm is proposed. This method includes the connection method between the forward multi-rotor aircraft motor and the arm and the connection method between the reverse multi-rotor aircraft motor and the arm, which are carried out in sequence. The steps are as follows:

[0051] S1. Connect one end of the forward lock disk structure 21 to the forward propeller motor, and insert the other end into the forward end of the base 1 through the forward guiding and positioning structure 31, and connect it to the forward end of the base 1 through forward thread connection;

[0052] S2. Connect one side of the base 1 to the arm;

[0053] S3. Screw the forward lock disk structure 21 into the root of the base 1 through a customized torque wrench;

[0054] S4. Connect one end of the reverse lock disk structure 21 to the reverse propeller motor, and insert the other end into the reverse end of the base 1 through the reverse guiding and positioning structure 32, and connect it to the reverse end of the base 1 through reverse thread connection;

[0055] S5. Screw the reverse lock disk structure 22 into the root of the base 1 through a customized torque wrench.

[0056] In specific implementation, in combination with the content of Embodiment 1, for the assembly of the forward propeller motor part, the forward guiding and positioning structure 31 is installed on the lock plate joint 201. After the lock plate joint 202 is sleeved on the lock plate body 201, it is defined as Component 1. Component 1 and the forward propeller motor are tightly connected by anti-loosening hex bolts. Of course, in actual implementation, it is not limited to the tightening method. And the above-assembled part is defined as Component 2. One end of the connecting frame 11 of the base 1 is installed with the arm by glue and rivets, and the same as the above part is defined as Component 3. The lock plate body 201 of Component 2 is coated with thread glue and inserted into the forward end of the base 1 of Component 3 through the guiding and positioning of the forward guiding and positioning structure 31, and then screwed into the root of the base by a customized torque wrench. During the screwing process, the motor stator always remains stationary, so that the motor outgoing wire harness will not be entangled. Finally, the lock plate body 201 is tightened, and the assembly of the forward motor is completed and defined as Component 4.

[0057] For the assembly of the reverse propeller motor part: Another set, that is, the reverse guiding and positioning structure 32, is installed on another lock plate joint 201. After being sleeved with the lock plate body 202, it is defined as Component 5. Component 5 and the reverse propeller motor are tightly connected by another set of anti-loosening hex bolts 5. Of course, in actual implementation, it is not limited to the tightening method and is defined as Component 6. Component 6 is inserted into the reverse end of the base 1 of Component 4 through the guiding and positioning of the reverse guiding and positioning structure 32, and then screwed into the root of the base 1 by a customized torque wrench. During the screwing process, the motor stator always remains stationary, so that the wire harness will not be entangled, and the lock plate body on this side is tightened, and the assembly of the reverse propeller motor part is completed. Finally, anti-loosening fuses are installed between the lock plate bodies 202 in two directions and the base 1. Of course, in actual implementation, it is not limited to this anti-loosening method, and the connection and installation of the motors and arms of the entire multi-rotor aircraft are completed.

[0058] Obviously, the above embodiments of the present invention are only examples for clearly explaining the present invention, and are not intended to limit the implementation manners of the present invention. For those of ordinary skill in the art, other different forms of changes or variations can be made based on the above description. It is not necessary and impossible to list all the implementation manners here. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A connector for a multi-rotor aircraft motor and an arm, characterized in that, the connector includes a base (1), a locking disc component (2), and a guiding and positioning component (3). One side of the base (1) is connected to the arm. The locking disc component (2) includes a forward locking disc structure (21) and a reverse locking disc structure (22). The guiding and positioning component (3) includes a forward guiding and positioning structure (31) and a reverse guiding and positioning structure (32). The forward guiding and positioning structure (31) and the reverse guiding and positioning structure (32) are respectively embedded in the forward locking disc structure (21) and the reverse locking disc structure (22). One end of the forward locking disc structure (21) is connected to the forward propeller motor, and the other end is inserted into the forward end of the base (1) through the forward guiding and positioning structure (31) and is threadedly connected to the forward end of the base (1) through a forward thread; one end of the reverse locking disc structure (22) is connected to the reverse propeller motor, and the other end is inserted into the reverse end of the base (1) through the reverse guiding and positioning structure (32) and is threadedly connected to the reverse end of the base (1) through a reverse thread; the base (1) includes a connecting frame (11) and a sleeve (12). One end of the connecting frame (11) is connected to the arm, and the other end of the connecting frame (11) is perpendicularly connected to the sleeve (12). The forward end of the sleeve (12) is threadedly connected to the forward locking disc structure (21) through a forward thread, and the reverse end of the sleeve (12) is threadedly connected to the reverse locking disc structure (21) through a reverse thread; each of the forward locking disc structure (21) and the reverse locking disc structure (22) includes a locking disc joint (201) and a locking disc body (202). A platform (122) extends radially from the inner wall of the sleeve (12) towards the axis of the sleeve (12). A plurality of anti-rotation grooves (123) are provided on the platform (122). A plurality of anti-rotation bosses (203) are provided on the locking disc joint (201). When the locking disc joint (201) is sleeved on the locking disc body (202), the anti-rotation bosses (203) are arranged in the anti-rotation grooves (123); the locking disc joint (201) is stationary, while the forward locking disc structure (21) and / or the reverse locking disc structure (22) can perform both axial screw movement and radial rotational movement to achieve threaded locking of the locking disc joint (201) by the forward locking disc structure (21) and / or the reverse locking disc structure (22).

2. The connector for a multi-rotor aircraft motor and an arm according to claim 1, characterized in that, a plurality of inclined slot holes (121) are provided on the sleeve (12).

3. The connector for a multi-rotor aircraft motor and an arm according to claim 1, characterized in that, a guiding and positioning groove (124) is also vertically provided along the inner wall of the sleeve (12). The forward guiding and positioning structure (31) and the reverse guiding and positioning structure (32) respectively embedded in the forward locking disc structure (21) and the reverse locking disc structure (22) are introduced into the sleeve (12) through the guiding and positioning groove (124).

4. The connector for a multi-rotor aircraft motor and an arm according to claim 3, characterized in that, Both the forward guiding and positioning structure (31) and the reverse guiding and positioning structure (32) adopt guiding and positioning pins.

5. The connector for the motor and the arm of a multi-rotor aircraft according to claim 1, characterized in that the locking disc joint (201) in the forward locking disc structure (21) is connected to the forward propeller motor through a bolt (4), and the locking disc joint (201) in the reverse locking disc structure (22) is connected to the reverse propeller motor through a bolt (4).

6. The connector for the motor and the arm of a multi-rotor aircraft according to claim 1, characterized in that the connector further includes a plurality of anti-loosening components (4), a plurality of first fixing holes (13) are provided on the outer side surface of the base (1), and a plurality of second fixing holes (204) are provided on the locking disc body (202). Each anti-loosening component (4) passes through a first fixing hole (13) on the base (1) and a second fixing hole (204) on the locking disc body (202) in sequence and then is locked.

7. The connector for the motor and the arm of a multi-rotor aircraft according to claim 6, characterized in that the anti-loosening component (4) is an anti-loosening fuse.

8. A method for connecting the motor and the arm of a multi-rotor aircraft, characterized in that the method includes the forward connection method of the motor and the arm of the multi-rotor aircraft and the reverse connection method of the motor and the arm of the multi-rotor aircraft carried out in sequence, and the steps are as follows: S1. Connect one end of the forward locking disc structure (21) to the forward propeller motor, and insert the other end into the forward end of the base (1) through the forward guiding and positioning structure (31), and connect it to the forward end of the base (1) through forward threading; S2. Connect one side of the base (1) to the arm; S3. Screw the forward locking disc structure (21) into the root of the base (1) through a customized torque wrench; S4. Connect one end of the reverse locking disc structure (21) to the reverse propeller motor, and insert the other end into the reverse end of the base (1) through the reverse guiding and positioning structure (32), and connect it to the reverse end of the base (1) through reverse threading; S5. Screw the reverse locking disc structure (22) into the root of the base (1) through a customized torque wrench.

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