Unmanned aerial vehicle propeller protection cover and unmanned aerial vehicle

Abstract

The invention discloses an unmanned aerial vehicle propeller protection cover and an unmanned aerial vehicle, and relates to the field of unmanned aerial vehicles, the unmanned aerial vehicle propeller protection cover comprises a vehicle body, multiple sets of landing cylinders are symmetrically arranged on the outer wall of the vehicle body, driving assemblies are arranged in the landing cylinders, propellers are arranged at the output ends of the driving assemblies, and air inlets are formed in the tops of the landing cylinders; a flexible air bag is arranged at the bottom of the driving assembly, a clamping groove is formed in the outer wall of the rising and falling cylinder, a clamping plate is clamped in the clamping groove, a protective cover is connected to the outer wall of the clamping plate, and an inserting groove is formed in the clamping plate. The flexible air bag drives the inserting rod to move downwards, so that the limiting work of the protective cover is completed, and when the vertical rod makes contact with the interior of the inserting groove, the piston plate is driven to slide towards the inner side of the through hole, so that the sealing work of the through hole is relieved, and the buffering air bag is supported to complete the buffering work of the protective cover; and it is guaranteed that when the protective cover is impacted, the impact force can be relieved.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicles, and in particular to a propeller protective cover for an unmanned aerial vehicle and an unmanned aerial vehicle. Background Art

[0002] Drone is a general term for unmanned aerial vehicles, which are equipped with flight controllers, GPS and other equipment. They can be tracked and located by ground stations or pilots. Compared with manned aircraft, they have the advantages of small size, low cost and easy use. They can take off vertically under radio remote control, land automatically when recovered, and can be used repeatedly. Among them, plant protection drones are widely used in agricultural-related tasks such as pesticide spraying, pollination, and sowing.

[0003] The propeller is one of the core components of the UAV power system, and it is also the component that is most easily damaged in the event of a flight accident. Some models of UAVs currently on the market use a protective cover to protect the propeller. In order to prevent the propeller cover of the UAV from increasing the overall weight, the protective cover itself has a weaker structural strength and a lighter weight. In the event of a slight collision, the propeller cover is easily deformed and damaged, reducing the overall service life of the propeller cover, and staff are required to disassemble and replace it subsequently. Since the propeller cover is mostly installed through multiple sets of bolt assemblies, the subsequent replacement and installation of the propeller cover is cumbersome, wasting a lot of manpower and material resources.

[0004] To sum up, in actual application, the propeller protection cover of the above-mentioned UAV has a weak structural strength and light weight, which can easily cause the propeller protection cover to be deformed and damaged in the event of a slight collision. In addition, the propeller protection cover is mostly installed by means of multiple sets of bolt assemblies. Therefore, the subsequent replacement and installation of the propeller protection cover is rather cumbersome, wasting a lot of manpower and material resources. Summary of the invention

[0005] Based on this, the purpose of the present invention is to provide a UAV propeller protective cover and a UAV, so as to solve the technical problem that in actual application, the protective cover itself has weak structural strength and light weight, which can easily cause the propeller protective cover to be deformed and damaged, and the subsequent replacement and installation of the propeller protective cover is cumbersome, wasting a lot of manpower and material resources.

[0006] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a propeller protective cover for an unmanned aerial vehicle, comprising a body, an outer wall of the body being symmetrically provided with an array of landing tubes, an interior of the landing tube being provided with a driving assembly, and an output end of the driving assembly passing through the landing tube is connected with a propeller, an air inlet is provided at the top of the landing tube, and a flexible airbag is provided at the bottom of the driving assembly, a slot is provided on the outer wall of the landing tube, and a card plate is carded in the slot, a protective cover is connected to the outer wall of the card plate, and a slot is provided in the vertical direction of the card plate, a plug rod matching the slot is connected to one side of the top of the flexible airbag, a piston plate is elastically sealed at the top of the plug rod, and a through hole is provided on the inner wall of the plug rod, a buffer airbag is provided on the outer wall of the protective cover, and an air pipe is connected between the buffer airbag and the slot.

[0007] By adopting the above technical solution, air is blown into the flexible airbag through the air inlet, and the insertion rod is driven downward by the action of the flexible airbag and inserted into the slot of the card plate, thereby completing the limiting work of the protective cover. When the vertical rod contacts the slot, it will drive the piston plate to slide inwardly of the through hole, thereby releasing the sealing work of the through hole. At this time, the excess gas in the flexible airbag will be discharged into the buffer airbag on the outer wall of the protective cover through the air pipe, so that the buffer airbag is propped up to complete the buffering work of the protective cover, ensuring that the impact force of the protective cover can be reduced when it is impacted.

[0008] The present invention is further configured such that the driving assembly is a lifting motor, and the lifting motor is used to drive the propeller at the output end to rotate.

[0009] By adopting the above technical solution, it is convenient for the staff to control the rotation of the propeller through the action of the lifting and lowering motor, and at the same time control the rotation speed of the internal rotating blades, thereby further improving the overall practicality.

[0010] The present invention is further configured such that a sealing plate is rotatably provided at the bottom of the air inlet, and rotating blades are symmetrically hinged at the output end of the lifting and lowering motor, and a torsion spring is provided at the connection between the rotating blades and the output end of the lifting and lowering motor. In a normal state, the rotating blades are arranged in a vertical direction at the output end of the lifting and lowering motor.

[0011] By adopting the above technical solution, when the lifting and lowering motor is started and the propeller is driven to rotate rapidly, the output end of the lifting and lowering motor will cause the rotating blades to expand to both sides under the action of centrifugal force. At this time, the rotating blades release the support for the sealing plate, and thus rotate downward under the action of the sealing plate's own gravity, thereby releasing the sealing work on the air inlet. At the same time, the rotating blades draw air under the action of the lifting and lowering motor, thereby discharging the gas into the flexible airbag at the bottom.

[0012] The present invention is further configured such that a limit block is provided at a connection between the sealing plate and the landing tube, and the sealing plate is arranged to be inclined toward the landing motor when rotating downward by its own gravity.

[0013] By adopting the above technical solution, when the rotating blades are unfolded to both sides, the sealing plate will rotate downward due to its own gravity. Since a limit block is provided at the rotating shaft of the sealing plate, the sealing plate is inclined in the landing tube. Therefore, during the process of extracting air at the air inlet, part of the external air will be blown toward the landing motor under the action of the sealing plate, thereby completing the heat dissipation of the landing motor.

[0014] The present invention is further configured such that one end of the piston plate is connected to a vertical rod, and an insertion rod passes through one end of the vertical rod, and compression springs are symmetrically arranged on both sides of the vertical rod at one end of the piston plate, and the other end of the compression spring is connected to the inner wall of the insertion rod.

[0015] By adopting the above technical solution, when the insertion rod slides into the slot, the vertical rod at one end of the insertion rod will contact the inner wall of the slot first. At this time, when the insertion rod continues to move, it will squeeze the vertical rod and drive the piston plate to move to the inside of the through hole, thereby releasing the sealing work of the through hole. In this process, the gas in the flexible airbag is ensured to be discharged into the slot, ensuring that air can be continuously taken in the flexible airbag.

[0016] The present invention is further configured such that a top plate is provided on the top of the flexible airbag, and a plurality of air holes are provided on the top of the top plate, and limiting components are provided on the inner walls of the landing tube on both sides of the top plate.

[0017] By adopting the above technical solution, the top plate will be driven to slide upward during the inflation of the flexible airbag. The array of air holes on the top plate ensures that the external gas can be stably input into the flexible airbag, and the limit components on both sides of the top plate ensure that the top plate can slide in the vertical direction during the sliding process, ensuring that the insertion rod can be stably inserted into the slot of the card plate.

[0018] The present invention is further configured such that a one-way valve is provided through the inner wall of the landing tube and the buffer airbag.

[0019] By adopting the above technical solution, the one-way valve in the landing tube is closed and the one-way valve in the cushion airbag is opened during the process of air intake at the air inlet. At this time, it is ensured that air can always be taken inward into the landing tube to prevent air leakage. The cushion airbag maintains a state of taking in air and exhausting air at the same time, ensuring that the gas in the intake cushion airbag can be discharged stably, thereby improving the overall cushioning effect of the cushion airbag.

[0020] The present invention is further configured such that the contact surface between the insertion rod and the slot is smooth.

[0021] By adopting the above technical solution, the smooth setting reduces the sliding friction between the insertion rod and the slot, ensuring that the top plate will not tilt due to its own friction when the insertion rod slides into the slot, further improving the overall practicality of the device.

[0022] A drone comprises a body, wherein a shell cover is detachably provided on the top of the body through a bolt assembly, and a solar panel body is installed on the top of the shell cover.

[0023] By adopting the above technical solution, it is convenient to maintain and replace the electronic components in the fuselage by removing the shell cover. At the same time, the solar panel body can provide part of the power demand for the device, saving a lot of flight costs.

[0024] The present invention is further configured such that a controller and a converter cooperating with the solar panel body are arranged inside the machine body.

[0025] By adopting the above technical solution, the solar energy absorbed by the solar panel body can be easily converted into electrical energy under the action of the controller and the converter, thereby ensuring the normal operation of some electronic components in the body.

[0026] In summary, the present invention mainly has the following beneficial effects: The present invention provides a flexible air bag inside the landing tube, wherein the protective cover is connected to the landing tube by a snap-fitting manner. Subsequently, when the UAV is started, the rotating fan blades are unfolded by the centrifugal force of the landing motor output end. At this time, the external air cylinder can be blown into the flexible air bag through the air inlet. The insertion rod is driven downward by the action of the flexible air bag and inserted into the slot of the card plate, thereby completing the limiting work of the protective cover and ensuring the stability of the protective cover on the outer wall of the landing tube. When the UAV is subsequently stopped, the insertion rod slides out of the slot through the exhaust of the flexible air bag itself to release the limiting work of the protective cover. At this time, the staff can directly remove the protective cover from the outer wall of the landing tube. In this process, the removal and installation of the protective cover are convenient, saving a lot of manpower and material resources. The present invention provides a through hole in the insertion rod, and the piston plate seals the through hole under normal conditions. At this time, the flexible airbag will not leak when air is taken in, ensuring that the flexible airbag drives the insertion rod to be normally propped up and inserted into the slot of the card plate. When the vertical rod contacts the slot, it will drive the piston plate to slide toward the inside of the through hole, thereby releasing the sealing work of the through hole. At this time, the excess gas in the flexible airbag will be discharged into the buffer airbag on the outer wall of the protective cover through the air pipe, so that the buffer airbag props up to complete the buffering work of the protective cover, ensuring that the impact force of the protective cover can be reduced when it is impacted, effectively reducing the damage to the protective cover during the impact process, and extending the overall service life of the protective cover. The present invention provides a limiting block at the rotating shaft of the sealing plate. When the rotating blades are unfolded to both sides, the sealing plate will rotate downward under the action of its own gravity. Since the limiting block is provided at the rotating shaft of the sealing plate, the sealing plate is inclined in the landing tube. Therefore, during the process of extracting air at the air inlet, part of the external air will be blown toward the landing motor under the action of the sealing plate, thereby completing the heat dissipation work of the landing motor, improving the overall heat dissipation effect of the device, and ensuring that the UAV can work for a long time. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 A perspective view of the present invention; Figure 2 A top view of the present invention; Figure 3 It is a schematic diagram of the structure of the landing gear of the present invention; Figure 4 is a cross-sectional view of the landing tube of the present invention; Figure 5 This is a schematic diagram of the internal structure of the landing gear when the propeller of the present invention rotates; Figure 6 It is a schematic diagram of the structure of the flexible airbag of the present invention; Figure 7 It is a cross-sectional view of the plunger of the present invention: Figure 8 For the present invention Figure 4 A magnified view of middle; Fig. 9 For the present invention Figure 8 Enlarged view of middle B; Fig.10 It is a schematic diagram of the partial structure of the second embodiment of the present invention.

[0028] In the figure: 1. body; 2. shell cover; 3. solar panel body; 4. landing tube; 5. propeller; 6. protective cover; 7. cushion airbag; 8. card plate; 9. air pipe; 10. flexible airbag; 11. card slot; 12. air inlet; 13. sealing plate; 14. rotating fan blade; 15. landing motor; 16. plug rod; 17. top plate; 18. air hole; 19. limit assembly; 20. vertical rod; 21. piston plate; 22. through hole; 23. compression spring; 24. slot. DETAILED DESCRIPTION

[0029] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0030] The following describes an embodiment of the present invention based on its overall structure. Example

[0031] A UAV propeller protection cover and a UAV, such as Figure 1-Figure 9 As shown, it includes a body 1, a shell cover 2, a solar panel body 3, a landing tube 4, a sealing mechanism, a buffer mechanism and a limit mechanism. An array of landing tubes 4 are symmetrically arranged on the outer wall of the body 1, wherein a landing motor 15 is arranged inside the landing tube 4, and a propeller 5 is connected to the landing tube 4 through the output end of the landing motor 15, and a card slot 11 is opened on the outer wall of the landing tube 4, and a card plate 8 is clamped in the card slot 11, and a protective cover 6 is connected to the outer wall of the card plate 8, and a slot 24 is opened in the vertical direction of the card plate 8, and the protective cover 6 is clamped to the outer wall of the landing tube 4 by clamping, and then the landing motor 15 is started, and the propeller 5 is driven to rotate by the landing motor 15, so as to drive the body 1 to fly, an air inlet 12 is opened on the top of the landing tube 4, and a flexible airbag 10 is arranged at the bottom of the landing motor 15; A sealing plate 13 is rotatably arranged at the bottom of the air inlet 12, and a rotating blade 14 is symmetrically hinged at the output end of the lifting motor 15, and a torsion spring is arranged at the connection between the rotating blade 14 and the output end of the lifting motor 15. The rotating blade 14 is arranged vertically at the output end of the lifting motor 15 under normal conditions. When the lifting motor 15 is started, the output end of the lifting motor 15 will cause the rotating blade 14 to expand to both sides under the action of centrifugal force. At this time, the rotating blade 14 releases the support for the sealing plate 13, thereby the sealing plate 13 is automatically The airbag 10 is rotated downward under the action of the body gravity to release the sealing work of the air inlet 12. At the same time, the rotating blades 14 are sucked under the action of the lifting motor 15 to discharge the gas extracted by the rotating blades 14 to the inside of the flexible airbag 10 at the bottom. The top side of the flexible airbag 10 is connected with a plug rod 16 that cooperates with the slot 24. The plug rod 16 is driven downward by the action of the flexible airbag 10 and inserted into the slot 24 of the card plate 8, thereby completing the limiting work of the protective cover 6 and ensuring the stability of the protective cover 6 on the outer wall of the landing tube 4; In addition, a piston plate 21 is elastically sealed at the top of the insertion rod 16, and a through hole 22 is opened on the inner wall of the insertion rod 16, a buffer airbag 7 is arranged on the outer wall of the protective cover 6, and an air pipe 9 is connected between the buffer airbag 7 and the slot 24. Under normal conditions, the piston plate 21 seals the through hole 22. At this time, the flexible airbag 10 will not be deflated when air is taken in, ensuring that the flexible airbag 10 drives the insertion rod 16 to be normally propped up and inserted into the slot 24 of the card plate 8. When the vertical rod 20 contacts the slot 24, it will drive the piston plate 21 to slide toward the inside of the through hole 22, thereby releasing the sealing work of the through hole 22. At this time, the excess gas in the flexible airbag 10 will be discharged into the buffer airbag 7 on the outer wall of the protective cover 6 through the air pipe 9, so that the buffer airbag 7 is propped up to complete the buffering work of the protective cover 6, ensuring that the protective cover 6 can reduce its impact force when it is impacted, effectively reducing the damage to the protective cover during the impact process, and extending the overall service life of the protective cover; When the subsequent staff needs to disassemble the protective cover, the lifting motor 15 stops working. At this time, the rotating fan blade 14 is reset under the action of the torsion spring and drives the sealing plate 13 to seal the air inlet 12, thereby preventing dust and impurities in the air from entering the interior of the landing tube 4 through the air inlet 12 when the body is not working and causing erosion to the lifting motor 15. The flexible airbag 10 is discharged, so that the insertion rod 16 slides out of the slot 24 of the card plate 8, thereby releasing the limiting work of the protective cover 6. At this time, the staff can directly disassemble the protective cover 6 from the outer wall of the landing tube 4, and the disassembly and installation of the protective cover 6 are convenient in this process. The fuselage 1 is equipped with a shell cover 2 which is detachable, and a solar panel body 3 is installed on the top of the shell cover 2. The electronic components in the fuselage 1 can be easily maintained and replaced by removing the shell cover 2. The solar panel body 3 can provide part of the power demand for the device, which saves a lot of flight costs. A controller and a converter which cooperate with the solar panel body 3 are arranged inside the fuselage 1. Under the action of the controller and the converter, the solar energy absorbed by the solar panel body 3 is easily converted into electrical energy, thereby ensuring the normal operation of some electronic components in the fuselage 1.

[0032] See also Figure 8 and Fig. 9A vertical rod 20 is connected to one end of the piston plate 21, and one end of the vertical rod 20 passes through the insertion rod 16. Compression springs 23 are symmetrically arranged on both sides of the vertical rod 20 at one end of the piston plate 21, and the other end of the compression spring 23 is connected to the inner wall of the insertion rod 16. When the insertion rod 16 slides into the slot 24, the vertical rod 20 at one end of the insertion rod 16 will contact the inner wall of the slot 24 first. At this time, when the insertion rod 16 continues to move, it will squeeze the vertical rod 20 to drive the piston plate 21 to move toward the inside of the through hole 22, thereby releasing the sealing work of the through hole 22. In this process, it is ensured that the gas in the flexible airbag 10 will be discharged into the slot 24, ensuring that the flexible airbag 10 can always be filled with air. When the subsequent insertion rod 16 is reset and slid downward, it will be reset under the action of the compression spring 23 to reseal the through hole 22.

[0033] See also Figure 7 A top plate 17 is provided on the top of the flexible airbag 10, and an array of air holes 18 are opened on the top of the top plate 17, wherein limit components 19 are provided on the inner walls of the landing tube 4 on both sides of the top plate 17. During the inflation of the flexible airbag 10, the top plate 17 will be driven to slide upward. The array of air holes 18 on the top plate 17 ensure that the external gas can be stably input into the flexible airbag 10, and the limit components 19 on both sides of the top plate 17 ensure that the top plate 17 can slide in the vertical direction during the sliding process, thereby ensuring that the insertion rod 16 can be stably inserted into the slot 24 of the card plate 8. Example

[0034] like Fig.10 The propeller protection cover and the UAV shown in the figure have an overall structure similar to that of the first embodiment, wherein a limit block is provided at the connection between the sealing plate 13 and the landing tube 4, and the sealing plate 13 is inclined toward the landing motor 15 when it rotates downward due to its own gravity. In the process of the rotating fan blades 14 unfolding to both sides, the sealing plate 13 will rotate downward due to the action of its own gravity. Since the limit block is provided at the rotating shaft of the sealing plate 13, the sealing plate 13 is inclined in the landing tube 4. Therefore, in the process of exhausting air at the air inlet 12, part of the external air will be blown toward the landing motor 15 under the action of the sealing plate 13, thereby completing the heat dissipation of the landing motor 15.

[0035] The working principle of the present invention is as follows: when in use, the card plate 8 at one end of the protective cover 6 is inserted into the card slot 11 of the outer wall of the landing tube 4 through the card connection structure, and then the propeller 5 is driven to rotate rapidly under the action of the landing motor 15, so as to realize the lifting of the body 1 as a whole. In this process, when the output end of the landing motor 15 rotates, the rotating blades 14 of its outer wall will be spread to both sides under the action of centrifugal force, and the sealing plate 13 releases the seal of the air inlet 12 under the action of its own gravity. In this process, the outside air will be drawn into the landing tube 4 through the air inlet, so that part of the air will enter the flexible airbag 10. At this time, the flexible airbag 10 drives the top plate 17 to rise upward, thereby driving the insertion rod 16 to move upward. At this time, the insertion rod 16 will be inserted into the slot 24 of the card plate 8, realizing the limiting work of the protective cover 6, which is convenient for the staff to disassemble it later; At the same time, a through hole 22 is provided in the insertion rod 16, and the through hole 22 is sealed under the action of the piston plate 21 to prevent deflation during the inflation of the flexible airbag 10. In the process of the insertion rod 16 moving into the slot 24, the vertical rod 20 will contact the inner wall of the slot 24. At this time, the vertical rod 20 will drive the piston plate 21 to slide toward the inside of the through hole 22, thereby releasing the sealing work of the through hole 22, so that part of the gas will be discharged into the buffer airbag 7 on the outer wall of the protective cover 6 through the air pipe 9, thereby realizing the inflation of the buffer airbag 7, so that the buffer airbag 7 is propped up to complete the buffering work of the protective cover 6, and ensure that the impact force of the protective cover 6 can be reduced when it is impacted.

[0036] Although an embodiment of the present invention has been shown and described, this specific embodiment is only an explanation of the present invention and is not a limitation of the invention. The specific features, structures, materials or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. After reading this specification, those skilled in the art may make modifications, substitutions and variations to the embodiments without creative contribution as needed without departing from the principles and purpose of the present invention. However, as long as they are within the scope of the claims of the present invention, they are protected by patent law.

Claims

1. A propeller protective cover for a drone, comprising a body (1), wherein an outer wall of the body (1) is symmetrically provided with a plurality of landing tubes (4), characterized in that: A driving assembly is provided inside the landing cylinder (4), and a propeller (5) is connected to the landing cylinder (4) at the output end of the driving assembly. An air inlet (12) is provided at the top of the landing cylinder (4), and a flexible air bag (10) is provided at the bottom of the driving assembly. A card slot (11) is provided on the outer wall of the landing cylinder (4), and a card plate (8) is clamped in the card slot (11). The outer wall of the card plate (8) is connected to a protective cover (6), and a slot (24) is provided in the vertical direction of the card plate (8). A plug rod (16) that cooperates with the slot (24) is connected to one side of the top of the flexible air bag (10). A piston plate (21) is provided at the top elastic seal of the plug rod (16), and a through hole (22) is provided on the inner wall of the plug rod (16). A buffer air bag (7) is provided on the outer wall of the protective cover (6), and an air pipe (9) is connected between the buffer air bag (7) and the slot (24).

2. The UAV propeller protective cover according to claim 1, characterized in that: The driving component is a lifting motor (15), and the lifting motor (15) is used to drive the propeller (5) at the output end to rotate.

3. The UAV propeller protective cover according to claim 2, characterized in that: A sealing plate (13) is rotatably provided at the bottom of the air inlet (12), and a rotating fan blade (14) is symmetrically hinged at the output end of the lifting motor (15), and a torsion spring is provided at the connection between the rotating fan blade (14) and the output end of the lifting motor (15). In a normal state, the rotating fan blade (14) is arranged in a vertical direction at the output end of the lifting motor (15).

4. The UAV propeller protective cover according to claim 3, characterized in that: A limit block is provided at the connection between the sealing plate (13) and the lifting cylinder (4), and the sealing plate (13) is arranged to be inclined toward the lifting motor (15) when rotating downward due to its own gravity.

5. The UAV propeller protective cover according to claim 1, characterized in that: One end of the piston plate (21) is connected to the vertical rod (20), and one end of the vertical rod (20) passes through the insertion rod (16). One end of the piston plate (21) is symmetrically provided with compression springs (23) on both sides of the vertical rod (20), and the other end of the compression springs (23) is connected to the inner wall of the insertion rod (16).

6. The UAV propeller protective cover according to claim 1, characterized in that: A top plate (17) is provided on the top of the flexible airbag (10), and a plurality of air holes (18) are provided on the top of the top plate (17). Limiting components (19) are provided on the inner wall of the landing tube (4) on both sides of the top plate (17).

7. The UAV propeller protective cover according to claim 1, characterized in that: One-way valves are provided through the inner wall of the lifting cylinder (4) and the cushioning airbag (7).

8. The UAV propeller protective cover according to claim 1, characterized in that: The contact surface between the insertion rod (16) and the slot (24) is smooth.

9. A drone, comprising a body (1), characterized in that: A shell cover (2) is detachably provided on the top of the machine body (1) via a bolt assembly, and a solar panel body (3) is installed on the top of the shell cover (2).

10. The UAV according to claim 9, characterized in that: A controller and a converter that cooperate with the solar panel body (3) are provided inside the machine body (1).

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