An aircraft

Abstract

The application discloses an aircraft, comprising: a fuselage, an arm, a brushless motor and a propeller. The arm is arranged on the fuselage. The brushless motor is arranged on the arm, and the brushless motor has a stator and an outer rotor arranged outside the stator. The propeller has a cap body and a plurality of blades, the cap body comprises a barrel portion, one end of the barrel portion is provided with an end plate, the other end is an opening, the barrel portion is sleeved on the outer rotor, the end plate is attached to the outer rotor, each blade is connected to the barrel portion, and each blade is sequentially and spacedly arranged along the circumference of the barrel portion. The aircraft of the application adopts the brushless motor with the stator inside and the rotor outside, the propeller is sleeved on the outer rotor, the superimposed part of the motor axial height and the propeller connection structure is effectively eliminated, the arm thickness and the longitudinal size of the aircraft are reduced, the additional components for connecting the propeller and the motor are saved, the lightweight material of the arm can be adapted, the overall weight is reduced, the aircraft is convenient to transport and store, the air resistance in the flight process is reduced, and the flight flexibility and stability are improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an aircraft. Background Technology

[0002] Existing drones typically consist of a fuselage, arms, motors, and propellers, with the arms connected to the fuselage. The motors are mounted on the arms, and the propellers are directly connected to the top output of the motors. This results in the axial height of the motors and the propeller connection structure overlapping along the height of the arms, increasing the overall size of the arms and consequently the drone's longitudinal size. Furthermore, the need for additional connectors between the propellers and the top of the motors (such as adapters and extended fasteners) adds to the overall weight. These connectors are not only heavy themselves but also force the arms to be thicker and larger to accommodate the axial installation space of the motors, indirectly increasing the overall weight. Ultimately, this leads to a heavier drone overall. This increases space occupancy during transport and storage and causes greater air resistance during flight due to the larger longitudinal size and weight, affecting flight maneuverability and stability.

[0003] In view of the above, this utility model is hereby proposed. Utility Model Content

[0004] This utility model provides an aircraft.

[0005] This application provides the following technical solution: An aircraft comprising: body; A machine arm, which is disposed on the machine body; A brushless motor is disposed on the machine arm, and the brushless motor has a stator and an outer rotor disposed outside the stator; The propeller has a cap and multiple blades. The cap includes a cylindrical part, one end of which is provided with an end plate and the other end is an opening. The cylindrical part is sleeved on an outer rotor, and the end plate is attached to the outer rotor. Each blade is connected to the cylindrical part and the blades are arranged sequentially at intervals along the circumference of the cylindrical part.

[0006] Optionally, the end plate is provided with connection holes; One end of the fastener passes through the connecting hole and is connected to the outer rotor, while the other end of the fastener is confined to the end plate.

[0007] Optionally, the root of the blade extends from the end plate to one side of the opening.

[0008] Optionally, a lower convex shaft is provided on the inner wall of the end plate; The rotor is provided with slots; With the propeller connected to the outer rotor, the lower convex shaft is inserted into the slot.

[0009] Optionally, the arm is rotatably connected to the bottom of the machine body; The axis of rotation of the arm extends along the length of the body; When the aircraft is in a folded state, the arms on both sides of the fuselage rotate to the bottom side of the fuselage.

[0010] Optionally, the arm includes a first arm, a second arm, and a connecting portion; The first arm is rotatably connected to the fuselage; One end of the connecting part is vertically connected to the first arm; One end of the second arm is connected to the other end of the connecting part. The second arm is parallel to the first arm. The brushless motor is located at the end of the second arm that is away from the connecting part. When the aircraft is in the open state, the connecting part extends along the height direction of the fuselage, the second arm is not higher than the lower surface of the fuselage, and the propeller is not higher than the upper surface of the fuselage.

[0011] Optionally, a rotating groove is provided at the end of the arm, and a plurality of slots are provided on the peripheral sidewall of the rotating groove, with each slot arranged sequentially at intervals along the circumference of the rotating groove; The machine body is provided with a fastener, the fastener is located in the rotating groove, and the fastener is provided with multiple protrusions along the circumferential direction; When the aircraft is in a folded state, the rotating groove rotates around the fastener in the forward direction, so that each protrusion on the fastener can be engaged in the corresponding slot. When the aircraft is in the open state, the rotating groove rotates in the opposite direction around the fastener, so that each protrusion on the fastener can be engaged into the corresponding slot.

[0012] Optionally, the aircraft includes a rotating light assembly; The fuselage has a cavity, and a light-transmitting cover is provided on the fuselage; The rotating lamp assembly is located in the cavity and is rotatably connected to the body; The rotating lamp assembly has several light-transmitting parts arranged sequentially along the circumference of the rotation axis, and each light-transmitting part has a different shape. The rotation of the rotating lamp assembly allows different light-transmitting parts to face the light-transmitting cover; The light emitted by the rotating lamp assembly can pass through the light-transmitting part and enter the light-transmitting cover.

[0013] Optionally, the fuselage is provided with a groove communicating with the cavity; The rotating lamp assembly is provided with an outer flange in the circumferential direction; The outer flange portion extends out of the groove.

[0014] Optionally, the rotating lamp assembly includes a rotating housing and a lamp body; The rotating cylindrical shell is rotatably connected to the machine body; The rotating cylindrical shell has an inner cavity, and each of the light-transmitting parts is disposed on the cylindrical wall of the rotating cylindrical shell and is arranged sequentially at intervals along the circumference of the rotating cylindrical shell. The light-transmitting part includes a light-transmitting groove formed on the cylindrical wall. The lamp body is disposed in the inner cavity.

[0015] By adopting the above technical solution, this application has the following beneficial effects: The aircraft of this application adopts a brushless motor with the stator inside and the rotor outside, and the propeller is sleeved on the outer rotor. This effectively eliminates the superposition of the axial height of the motor and the propeller connection structure, reduces the thickness of the arm and the longitudinal dimension of the aircraft, and eliminates the need for additional components connecting the propeller and the motor. It can also be adapted to the lightweight materials of the arm, reducing the overall weight. This facilitates transportation and storage, reduces air resistance during flight, and improves flight flexibility and stability. Attached Figure Description

[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments and descriptions of the present invention are used to explain the present invention, but do not constitute an undue limitation of the present invention. Obviously, the drawings described below are merely some embodiments, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of the aircraft in the open state provided by an embodiment of the present invention; Figure 2 This is a structural schematic diagram of the aircraft in a folded state, provided as an embodiment of the present invention. Figure 3 A schematic diagram of the structure of an aircraft with part of its shell removed, provided for an embodiment of this utility model; Figure 4 A schematic diagram of the propeller of an aircraft provided in an embodiment of this utility model; Figure 5 A schematic diagram of the structure of the brushless motor of the aircraft provided in this embodiment of the utility model; Figure 6 A schematic diagram of the structure of the aircraft arm provided in this embodiment of the utility model; Figure 7 A schematic diagram of the fuselage of the aircraft provided in this embodiment of the utility model; Figure 8 A schematic diagram of the structure for removing the fastener from the fuselage of an aircraft provided in this embodiment of the utility model; Figure 9 A schematic diagram of the structure of the aircraft's fastener provided in this embodiment of the utility model; Figure 10 This is a schematic diagram of the internal structure of the aircraft provided in an embodiment of the present invention.

[0018] In the diagram: 1. Body, 11. Fastener, 111. Cross-shaped limiting groove, 112. Light-transmitting cover, 12. Groove, 13. Limiting part, 14. Groove, 15. Cross-shaped limiting post, 151. Arm 2, 21. First arm, 21. Rotating groove, 211. Slot, 2111. Second arm, 22. Connecting part, 23. Brushless motor 3. Outer rotor, 31. Slot, 311. Threaded groove, 312. Propeller 4. Cap, 41. End plate, 411. Connecting hole, 4111. Lower convex shaft, 4112. Blade, 42. Fastener 5. Rotating lamp assembly 6. Rotating cylinder shell, 61. Light-transmitting part, 611. Outer flange, 612. Limiting plate, 613. Lamp body, 62. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate this utility model, but are not intended to limit the scope of this utility model.

[0020] In the description of this utility model, it should be noted that the terms "upper", "lower", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0021] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0022] See Figures 1 to 10As shown in the illustration, this application provides an aircraft, including: a fuselage 1, an arm 2, a brushless motor 3, and a propeller 4. The arm 2 is disposed on the fuselage 1. The brushless motor 3 is disposed on the arm 2, and the brushless motor 3 has a stator and an outer rotor 31 disposed outside the stator. The propeller has a cap 41 and multiple blades 42. The cap 41 includes a cylindrical portion, one end of which is provided with an end plate 411, and the other end is an opening. The cylindrical portion is sleeved on the outer rotor 31, and the end plate 411 is attached to the outer rotor 31. Each blade 42 is connected to the cylindrical portion, and each blade 42 is arranged sequentially at intervals along the circumference of the cylindrical portion. The brushless motor 3 is an outer rotor motor, with its stator disposed on the inner side and its rotor disposed on the outer side. The height of each blade 42 is not higher than the end plate 411, which allows the blades 42 to be positioned lower, which is beneficial for reducing the longitudinal dimensions and overall weight of the aircraft. The brushless motor 3 described herein is a mature existing technology and is not the inventive point of this application; therefore, its structure and principle will not be elaborated upon here. The aircraft of this application employs a brushless motor 3 with the stator inside and the rotor outside, and the propeller 4 is fitted onto the outer rotor 31. This effectively eliminates the overlap between the axial height of the motor and the connection structure of the propeller 4, reduces the thickness of the arm 2 and the longitudinal dimensions of the aircraft, eliminates the need for additional components connecting the propeller 4 and the motor, and allows for the use of lightweight materials in the arm 2, reducing the overall weight. This facilitates transportation and storage, reduces air resistance during flight, and improves flight flexibility and stability. The aircraft of this application can be a drone.

[0023] In one possible implementation, such as Figure 1 and Figure 4 As shown, the end plate 411 is provided with a connecting hole 4111. One end of the fastener 5 passes through the connecting hole 4111 and is connected to the outer rotor 31, while the other end of the fastener 5 is confined within the end plate 411. The fastener 5 can be a screw. The outer rotor 31 is provided with a corresponding threaded groove 312. The screw shank passes through the connecting hole 4111 and is threaded into the threaded groove 312. The screw cap 41 is located on the side of the end plate 411 facing away from the outer rotor 31. By using only screws to fix the propeller 4, no additional transition components are needed. This ensures the firmness of the connection between the propeller 4 and the brushless motor 3, while avoiding the weight increase caused by additional connecting components. At the same time, the screw cap 41 confining the side of the end plate 411 facing away from the outer rotor 31 prevents any additional structural height increase in the longitudinal direction of the arm 2.

[0024] like Figure 1 and Figure 4As shown, the root of the blade 42 extends from the end plate 411 to the opening side, which can increase the contact area between the blade 42 and the cap 41, strengthen the connection strength, and prevent the blade 42 from breaking or deforming due to excessive force when the aircraft is flying at high speed. This increases the service life of the aircraft and does not require additional reinforcement, resulting in a stable structure.

[0025] like Figure 4 and Figure 5 As shown, a lower convex shaft 4112 is provided on the inner wall of the end plate 411, and a slot 311 is provided on the rotor. When the propeller 4 is connected to the outer rotor 31, the lower convex shaft 4112 is inserted into the slot 311. The insertion and engagement structure of the lower convex shaft 4112 and the slot 311 allows for quick and accurate positioning of the propeller 4 and the brushless motor 3 during assembly, eliminating the need for repeated adjustments to the circumferential angle between the propeller 4 and the outer rotor 31. This significantly simplifies the assembly process and improves assembly efficiency. Furthermore, the insertion and engagement structure of the lower convex shaft 4112 and the slot 311 can also share the force of the threaded connection, preventing the screws from loosening due to uneven force distribution during propeller 4 rotation during flight. This further enhances the stability of the connection between the propeller 4 and the brushless motor 3, ensuring the reliability of the aircraft in this application.

[0026] In one possible implementation, such as Figure 2 As shown, the arm 2 is rotatably connected to the bottom of the fuselage 1. The axis of rotation of the arm 2 extends along the length of the fuselage 1. When the aircraft is in a folded state, the arms 2 on both sides of the fuselage 1 rotate to the bottom side of the fuselage 1 and can be in a close-fitting state. This can significantly reduce the overall volume of the aircraft after folding, improving the convenience of transportation and storage. At the same time, the compact folding structure can effectively prevent the arms 2 from being damaged by bumps during carrying, further ensuring the structural integrity and safety of the aircraft.

[0027] In one possible implementation, such as Figure 1 , Figure 2 and Figure 6As shown, the arm 2 includes a first arm 21, a second arm 22, and a connecting portion 23. The first arm 21 is rotatably connected to the fuselage 1, and one end of the connecting portion 23 is perpendicularly connected to the first arm 21. One end of the second arm 22 is connected to the other end of the connecting portion 23, and the second arm 22 is parallel to the first arm 21. The brushless motor 3 is located at the end of the second arm 22 facing away from the connecting portion 23. When the aircraft is in the deployed state, the connecting portion 23 extends along the height direction of the fuselage 1, the second arm 22 is not higher than the lower surface of the fuselage 1, and the propeller 4 is not higher than the upper surface of the fuselage 1. This avoids the propeller 4 occupying extra space due to protruding above the fuselage 1, and also prevents the propeller 4 from scratching foreign objects during flight or storage, reducing the risk of damage. Simultaneously, the structure of the second arm 22 not exceeding the lower surface of the fuselage 1 significantly reduces the overall size of the aircraft, improving its portability for transportation and storage. Furthermore, the compact, flat structure reduces air resistance during flight, lowers energy consumption of the power system, and increases flight endurance. In addition, this structure lowers the drone's center of gravity, enhancing its wind resistance and reducing the swaying of the fuselage 1 under strong airflow disturbances, thereby improving the precision and reliability of flight control.

[0028] like Figure 6 , Figure 7 and Figure 9 As shown, a rotating groove 211 is provided at the end of the arm 2. The peripheral wall of the rotating groove 211 is provided with several slots 2111, which are spaced apart sequentially along the circumference of the rotating groove 211. A fastener 11 is provided on the fuselage 1, located within the rotating groove 211. The fastener 11 has multiple protrusions 111 arranged circumferentially. When the aircraft is in the folded state, the rotating groove 211 rotates around the fastener 11 in the forward direction, allowing each protrusion 111 on the fastener 11 to engage with its corresponding slot 2111. When the aircraft is in the open state, the rotating groove 211 rotates around the fastener 11 in the reverse direction, allowing each protrusion 111 on the fastener 11 to engage with its corresponding slot 2111. Figure 7 , Figure 8 and Figure 9As shown, a groove 15 is provided at the bottom of the fuselage 1, and a cross-shaped limiting post 151 is provided on the inner wall of the groove 15. A cross-shaped limiting groove 112 is provided in the middle of the fastener 11, and the cross-shaped limiting post 151 is inserted into the cross-shaped limiting groove 112 to fix the fastener 11. The rotation groove 211 is provided at the end of the first arm 21 away from the connecting part 23. After the arm 2 completes the folding or unfolding action, the locking protrusion 111 can accurately engage with the corresponding locking groove 2111 to form a stable limiting and fixing structure, preventing the arm 2 from rotating unexpectedly during transportation or flight, and ensuring structural stability. At the same time, the multiple sets of locking grooves 2111 and locking protrusions 111 arranged circumferentially can quickly switch between folding and unfolding states by simply rotating the arm 2 in the forward or reverse direction, without the need for additional tools, simplifying the operation process and improving the convenience and efficiency of the arm 2's state switching.

[0029] In one possible implementation, such as Figure 8 and Figure 10 As shown, the aircraft includes a rotating light assembly 6. The fuselage 1 has a cavity, and a light-transmitting cover 12 is disposed on the fuselage 1. The rotating light assembly 6 is located in the cavity and is rotatably connected to the fuselage 1. The rotating light assembly 6 has a plurality of light-transmitting parts 611 arranged sequentially along the circumference of the rotation axis. Each light-transmitting part 611 has a different shape. The rotation of the rotating light assembly 6 allows the different light-transmitting parts 611 to face the light-transmitting cover 12. The light emitted by the rotating light assembly 6 can pass through the light-transmitting parts 611 and enter the light-transmitting cover 12. The light-transmitting cover 12 can be made of ABS plastic, which has a certain degree of light transmittance and structural shielding. It can ensure that the light from the rotating light assembly 6 can pass through smoothly, while effectively shielding the internal structure of the cavity of the fuselage 1, avoiding direct exposure of the internal structure and affecting the overall appearance of the aircraft. Each of the aforementioned light-transmitting sections 611 can be customized with patterns such as eyes or facial expressions. Different lighting effects can be achieved by switching between different shaped light-transmitting sections 611, making the lighting more visually distinctive and improving the visibility and aesthetics of the aircraft during nighttime flight, while reducing the risk of collisions. Furthermore, diverse lighting effects can be presented without changing the lights, enriching the aircraft's functionality and user experience.

[0030] like Figure 1 , Figure 3 and Figure 10As shown, the body 1 is provided with a groove 13 communicating with the cavity, and the rotating lamp assembly 6 is provided with an outer flange 612 along the circumference, with a portion of the outer flange 612 extending out of the groove 13. The rotating lamp assembly 6 can be driven to rotate by flicking the outer flange 612 with a finger, thereby achieving rapid switching of the various light-transmitting parts 611. No additional tools are required, making operation simple and efficient, allowing users to change the lighting display style as needed. Furthermore, the manual control method is precise and controllable, preventing misalignment of the light-transmitting parts 611 during switching, ensuring consistency in the lighting display effect, and improving the user experience.

[0031] In one possible implementation, such as Figure 10 As shown, the rotating light assembly 6 includes a rotating cylindrical shell 61 and a lamp body 62. The rotating cylindrical shell 61 is rotatably connected to the fuselage 1. The rotating cylindrical shell 61 has an inner cavity, and each of the light-transmitting parts 611 is disposed on the cylindrical wall of the rotating cylindrical shell 61 and is arranged sequentially at intervals along the circumference of the rotating cylindrical shell 61. Each light-transmitting part 611 includes a light-transmitting groove formed on the cylindrical wall. The lamp body 62 is disposed in the inner cavity. The lamp body 62 is disposed at both ends of the rotating cylindrical shell 61 along the rotation axis, so that its wiring position avoids the rotating area of ​​the rotating cylindrical shell 61, which facilitates electrical connection with the circuit board (not shown) inside the aircraft through a power supply line (not shown), and avoids pulling the power supply line when the rotating cylindrical shell 61 rotates, ensuring that the lamp body 62 of the aircraft can be powered on and lit normally. At the same time, the light emitted by the lamp body 62 can more evenly cover the light-transmitting groove on the cylindrical wall, ensuring that the light transmitted through the light-transmitting groove with different shapes has the same brightness, thus improving the lighting display effect.

[0032] like Figure 10 As shown, the rotating cylindrical shell 61 is provided with limiting plates 613 on both sides along its rotation axis, and the inner shell of the body 1 is provided with a limiting part 14 at the corresponding position. When the rotating cylindrical shell 61 rotates to the limit position in the forward or reverse direction, the limiting plate 613 abuts against the limiting part 14, and the rotation angle of the rotating cylindrical shell 61 is limited to within 180° to prevent it from rotating indefinitely. This ensures that the rotating cylindrical shell 61 can accurately switch to each light-transmitting part 611 when rotating, prevents the light-transmitting part 611 from being misaligned with the light-transmitting cover 12, and ensures the accuracy of the light display effect. It also prevents the internal power supply lines from getting tangled and pulled due to excessive rotation of the rotating cylindrical shell 61, protects the stability of the line connection, and extends the service life of the rotating lamp assembly 6.

[0033] The preferred embodiments disclosed above are merely illustrative of this application. These preferred embodiments do not exhaustively describe all details, nor do they limit the application to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this application, thereby enabling those skilled in the art to better understand and utilize this application. This application is limited only by the claims and their full scope and equivalents.

Claims

1. An aircraft, characterized in that, include: body; A machine arm, which is disposed on the machine body; A brushless motor is disposed on the machine arm, and the brushless motor has a stator and an outer rotor disposed outside the stator; The propeller has a cap and multiple blades. The cap includes a cylindrical part, one end of which is provided with an end plate and the other end is an opening. The cylindrical part is sleeved on an outer rotor, and the end plate is attached to the outer rotor. Each blade is connected to the cylindrical part and the blades are arranged sequentially at intervals along the circumference of the cylindrical part.

2. The aircraft according to claim 1, characterized in that, The end plate is provided with connection holes; One end of the fastener passes through the connecting hole and is connected to the outer rotor, while the other end of the fastener is confined to the end plate.

3. The aircraft according to claim 1, characterized in that, The root of the blade extends from the end plate to one side of the opening.

4. The aircraft according to claim 1, characterized in that, The inner wall of the end plate is provided with a lower convex shaft; The rotor is provided with slots; With the propeller connected to the outer rotor, the lower convex shaft is inserted into the slot.

5. The aircraft according to claim 1, characterized in that, The arm is rotatably connected to the bottom of the machine body; The axis of rotation of the arm extends along the length of the body; When the aircraft is in a folded state, the arms on both sides of the fuselage rotate to the bottom side of the fuselage.

6. The aircraft according to claim 5, characterized in that, The arm includes a first arm, a second arm, and a connecting part; The first arm is rotatably connected to the fuselage; One end of the connecting part is vertically connected to the first arm; One end of the second arm is connected to the other end of the connecting part. The second arm is parallel to the first arm. The brushless motor is located at the end of the second arm that is away from the connecting part. When the aircraft is in the open state, the connecting part extends along the height direction of the fuselage, the second arm is not higher than the lower surface of the fuselage, and the propeller is not higher than the upper surface of the fuselage.

7. The aircraft according to claim 5, characterized in that, The end of the arm is provided with a rotating groove, and the peripheral sidewall of the rotating groove is provided with a plurality of slots, and each slot is arranged sequentially at intervals along the circumference of the rotating groove. The machine body is provided with a fastener, the fastener is located in the rotating groove, and the fastener is provided with multiple protrusions along the circumferential direction; When the aircraft is in a folded state, the rotating groove rotates around the fastener in the forward direction, so that each protrusion on the fastener can be engaged in the corresponding slot. When the aircraft is in the open state, the rotating groove rotates in the opposite direction around the fastener, so that each protrusion on the fastener can be engaged into the corresponding slot.

8. The aircraft according to claim 1, characterized in that, Includes rotating light assembly; The fuselage has a cavity, and a light-transmitting cover is provided on the fuselage; The rotating lamp assembly is located in the cavity and is rotatably connected to the body; The rotating lamp assembly has several light-transmitting parts arranged sequentially along the circumference of the rotation axis, and each light-transmitting part has a different shape. The rotation of the rotating lamp assembly allows different light-transmitting parts to face the light-transmitting cover; The light emitted by the rotating lamp assembly can pass through the light-transmitting part and enter the light-transmitting cover.

9. The aircraft according to claim 8, characterized in that, The fuselage is provided with grooves that communicate with the cavity; The rotating lamp assembly is provided with an outer flange in the circumferential direction; The outer flange portion extends out of the groove.

10. The aircraft according to claim 8, characterized in that, The rotating lamp assembly includes a rotating cylindrical shell and a lamp body; The rotating cylindrical shell is rotatably connected to the machine body; The rotating cylindrical shell has an inner cavity, and each of the light-transmitting parts is disposed on the cylindrical wall of the rotating cylindrical shell and is arranged sequentially at intervals along the circumference of the rotating cylindrical shell. The light-transmitting part includes a light-transmitting groove formed on the cylindrical wall. The lamp body is disposed in the inner cavity.

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