Fan

Abstract

The invention provides a draught fan which comprises a fan body, a supporting foot stand used for supporting the fan body, a first rotation matching component, a second rotation matching component, a clamping pin and a plurality of clamping grooves corresponding to the clamping pin, the first rotation matching component and the second rotation matching component are at least partially nested in the axial direction parallel to the rotation axis, and the supporting foot stand is used for supporting the fan body. Along with the rotation of the machine body around the rotation axis relative to the supporting foot stool, the first rotation matching part and the second rotation matching part rotate relatively; the plurality of clamping grooves are positioned between the first rotation matching part and the second rotation matching part, and can be respectively matched with the clamping pins in a clamping manner, so that the machine body can be kept at different angles relative to the supporting foot stool; the clamping pin can elastically stretch out and draw back in the process that the machine body rotates around the rotating axis relative to the supporting foot stand so as to be switched among the multiple clamping grooves. According to the design, the user experience for adjusting the pitching angle of the fuselage can be improved.

Description

[Technical field]

[0001] The invention relates to a fan, and in particular to a rotationally connected structure between a body of the fan and a supporting frame. [Background technology]

[0002] In the relevant prior art, the fan includes a head, a supporting tripod, and a locking knob. The locking knob includes a screw and a knob operating part. The locking knob can fasten the head and the supporting tripod together. When adjusting the pitch angle of the head, it is usually necessary to loosen the locking knob first, then turn the head to the desired angle, and finally tighten the locking knob so that the head remains at the desired angle. The operation is inconvenient and the user experience is poor. [Summary of the invention]

[0003] One of the technical problems solved by this patent application is to improve the user experience of adjusting the pitch angle of the wind turbine body.

[0004] 14. The swiftly and minutely adjusting device for a wood-planer working table as claimed in claim 13, wherein the first and second rotating mating parts are respectively and sequentially engaged with each other and are arranged on a platform where the first and second rotating mating parts are engaged with each other and are under the effect of the rotation of the steering wheel.

[0005] With such a design, with the help of the first rotating matching component and the second rotating matching component that are at least partially nested along the axial direction parallel to the rotation axis, the fuselage can be promoted to rotate relatively smoothly around the rotation axis relative to the supporting tripod; the locking pin can elastically telescope during the process of the fuselage rotating around the rotation axis relative to the supporting tripod, so as to switch between multiple locking slots, thereby switching to different angles, and the multiple locking slots can respectively engage with the locking pin, so that the fuselage can be maintained at different angles relative to the supporting tripod, so that the present design can facilitate the user to adjust the pitch angle of the fuselage; in summary, the present design can improve the user experience of adjusting the pitch angle of the fuselage.

[0006] Optionally, the first rotating matching component is in radial contact with the second rotating matching component, and as the first rotating matching component rotates relative to the second rotating matching component, the first rotating matching component and the second rotating matching component slide and rub against each other; the locking pin can telescopically move along the axial direction, and the multiple locking grooves are arranged in sequence around the rotation axis, and the multiple locking grooves are radially distributed relative to the rotation axis; the second rotating matching component is fixed to the supporting tripod, and the fuselage includes a first air inlet grille, which is located on one of the opposite sides of the fuselage in the axial direction, and the first rotating matching component is fixed to the first air inlet grille and can rotate synchronously with the first air inlet grille, and the first rotating matching component is arranged in the central area of ​​the first air inlet grille, and the first air inlet grille includes a plurality of ribs respectively integrally connected to the first rotating matching component, and the plurality of ribs are radially distributed around the first rotating matching component on the periphery of the first rotating matching component.

[0007] Optionally, the first rotating fitting component is fixed to the fuselage, and the second rotating fitting component is fixed to the supporting bracket; the fan also includes a stopping component for preventing the second rotating fitting component from detaching from the first rotating fitting component, and a first fastening element for fixing the stopping component, and the first fastening element passes through the stopping component and fixes the stopping component to the first rotating fitting component.

[0008] Optionally, the first rotating matching component includes a locking portion, the locking portion is provided with a first matching hole for matching with the first fastening element, the first matching hole extends along the rotation axis, the rotation axis passes through the first matching hole, the locking portion at least partially penetrates the first rotating matching component, the stopping component blocks the side of the second rotating matching component that is away from the fuselage in the axial direction, the first fastening element includes a rod portion and a cap head, the rod portion of the first fastening element passes through the stopping component and is screwed and fixed to the first matching hole, the cap head of the first fastening element presses the stopping component against the locking portion, and the stopping component is at least partially clamped between the end of the locking portion and the cap head of the first fastening element.

[0009] Optionally, the first rotating fitting component includes a locking portion, and the second rotating fitting component includes a first barrel portion, and the first barrel portion is sleeved on the outside of the locking portion; the first rotating fitting component includes a second barrel portion, and the second barrel portion surrounds the periphery of the locking portion, and the second barrel portion is sleeved on the outside of the first barrel portion. As the fuselage rotates relative to the supporting tripod, the locking portion and the second barrel portion rotate relative to the first barrel portion, and the locking portion and / or the second barrel portion can slide and rub against the first barrel portion.

[0010] Optionally, the first barrel portion includes a plurality of first reinforcing ribs, the plurality of first reinforcing ribs are disposed on the inner circumference of the first barrel portion, the plurality of first reinforcing ribs are arranged in sequence around the locking portion, and the plurality of first reinforcing ribs are radially distributed on the periphery of the locking portion.

[0011] Optionally, the first rotating matching component also includes a first substrate, and the second rotating matching component also includes a second substrate, the first substrate and the second substrate are spaced opposite to each other in the axial direction, the multiple positioning grooves are located between the first substrate and the second substrate, and the stopping component blocks the side of the second substrate facing away from the first substrate; the locking portion is fixedly connected to the first substrate, the locking portion at least partially penetrates the second substrate, and the end of the locking portion away from the first substrate abuts against the stopping component; the second barrel is located between the first substrate and the second substrate, and the second barrel extends integrally from the first substrate toward the second substrate; the first barrel extends integrally from the second substrate toward the first substrate.

[0012] Optionally, the stopping component is a blocking piece, the locking portion extends integrally from the first substrate along the axial direction, and the locking portion passes through the second substrate.

[0013] Optionally, the second rotating matching component includes a first cylinder portion, the first rotating matching component includes a second cylinder portion, the first cylinder portion and the second cylinder portion respectively surround the rotation axis, the second cylinder portion is sleeved on the outside of the first cylinder portion, the second cylinder portion includes a plurality of convex ribs, the plurality of convex ribs are respectively protruding from the inner periphery of the second cylinder portion, the plurality of convex ribs respectively extend along the axial direction, the plurality of convex ribs are arranged in sequence around the first cylinder portion, and as the fuselage rotates relative to the supporting tripod, the plurality of convex ribs rotate relative to the first cylinder portion and can slide and rub against the outer peripheral surface of the first cylinder portion.

[0014] Optionally, in the axial direction, the multiple locking grooves are located between the first rotating matching component and the second rotating matching component, and the locking pin can telescopically move along the axial direction; the second rotating matching component includes a first barrel portion and a third barrel portion, and the third barrel portion surrounds the periphery of the first barrel portion; the first rotating matching component includes a second barrel portion and a fourth barrel portion, and the fourth barrel portion surrounds the periphery of the second barrel portion, and the multiple locking grooves are located between the fourth barrel portion and the second barrel portion; the first barrel portion, the second barrel portion, the third barrel portion, and the fourth barrel portion respectively surround the rotation axis, the first barrel portion and the second barrel portion are nested along the axial direction, and the third barrel portion and the fourth barrel portion are nested along the axial direction, as the fuselage rotates relative to the supporting tripod, the first barrel portion and the second barrel portion rotate relative to each other and the third barrel portion and the fourth barrel portion rotate relative to each other; as the fuselage rotates relative to the supporting tripod, the first barrel portion can slide and rub with the second barrel portion and / or the third barrel portion can slide and rub with the fourth barrel portion.

[0015] Optionally, the first rotating mating component also includes a first substrate, and the second rotating mating component also includes a second substrate. The first substrate and the second substrate are spaced apart from each other in the axial direction, and the multiple positioning grooves are located between the first substrate and the second substrate. The first barrel portion, the second barrel portion, and the third barrel portion are respectively at least partially located between the first substrate and the second substrate. The first barrel portion and the third barrel portion are respectively integrally connected to the second substrate, and the second barrel portion and the fourth barrel portion are respectively integrally connected to the first substrate.

[0016] Optionally, the locking pin is located between the third barrel portion and the first barrel portion; the first rotating mating component also includes a plurality of second reinforcing ribs, the plurality of second reinforcing ribs respectively protrude from the first substrate toward the second substrate, the plurality of second reinforcing ribs are radially distributed relative to the rotation axis, the plurality of second reinforcing ribs are located between the second barrel portion and the fourth barrel portion, the fan also includes a locking member, the locking member is located between the first substrate and the second substrate, the plurality of locking grooves are part of the locking member, the locking member is provided with at least two positioning protrusions, the at least two positioning protrusions are located between the second barrel portion and the fourth barrel portion, and each positioning protrusion is respectively clamped and fixed between two second reinforcing ribs.

[0017] Optionally, the fuselage includes a first air inlet grille, which is located on one of the opposite sides of the fuselage in the axial direction, and the first rotating matching component can rotate synchronously with the first air inlet grille. The first air inlet grille includes a plurality of ribs respectively integrally connected to the first rotating matching component, and the plurality of ribs respectively extend integrally from the fourth cylinder portion, and the plurality of ribs are radially distributed relative to the fourth cylinder portion.

[0018] Optionally, the first rotating matching component is fixed to the fuselage, the second rotating matching component is fixed to the supporting bracket, the locking pin is mounted on the second rotating matching component, the locking pin can telescope along the axial direction, and the multiple locking grooves are located between the first rotating matching component and the second rotating matching component in the axial direction; the fan also includes an elastic element corresponding to the locking pin, the elastic element and the locking pin are assembled on the second rotating matching component, the elastic element can telescope along the axial direction, and the elastic element is used to elastically support the locking pin; the second rotating matching component also includes an installation cavity, the elastic element is installed in the installation cavity, the locking pin is at least partially located in the installation cavity and can telescope relative to the installation cavity, and the locking pin can be at least partially embedded in the locking groove under the push of the elastic element.

[0019] Optionally, the first rotating matching component is fixed to the fuselage, and the fan also includes a first cover, which at least partially covers the second rotating matching component, and the first cover is installed on the second rotating matching component. As the fuselage rotates relative to the supporting tripod, the first rotating matching component rotates relative to the first cover; the second rotating matching component is located in a receiving cavity defined by the first cover and the first rotating matching component; the supporting tripod includes a first support rod and a second support rod, the first support rod and the second support rod are located on the left and right sides of the fuselage, a part of the first support rod is located in the receiving cavity and is covered by the first cover, and the second rotating matching component is fixed to the part of the first support rod.

[0020] Optionally, the fan also includes at least one second fastening element for locking the second rotating fitting component to the first support rod, the first support rod includes a first flat section, the first flat section is located on the side of the second rotating fitting component facing away from the fuselage, the first flat section is flat in the axial direction, the first cover at least partially covers the first flat section, the at least one second fastening element is located within the accommodating cavity, the at least one second fastening element locks the second rotating fitting component to the first flat section, and the portion of the first support rod is a part of the first flat section.

[0021] Optionally, the fan also includes a stopping component for preventing the second rotating matching component from disengaging from the first rotating matching component, and a first fastening element for fixing the stopping component, wherein the stopping component is located between the first rotating matching component and the first flat section, and during the rotation of the fuselage around the rotation axis relative to the supporting tripod, the first fastening element and the stopping component rotate synchronously with the fuselage and the first flat section does not contact the first fastening element and the stopping component and does not hinder the rotation of both the first fastening element and the stopping component; the first flat section is provided with at least one clearance hole for avoiding the first fastening element, the rotation axis passes through the at least one clearance hole, and the at least one clearance hole is covered by the first cover.

[0022] Optionally, the first flat section obliquely penetrates the accommodating cavity, the second fastening element is a screw, and the second rotating matching component is also provided with a mounting groove corresponding to the first flat section and at least one second matching hole corresponding to the at least one second fastening element, the mounting groove is located on the side of the second rotating matching component facing away from the fuselage, the first flat section is partially embedded in the mounting groove, and the mounting groove extends in a radial direction perpendicular to the rotation axis through the radially opposite sides of the second rotating matching component; the at least one second fastening element is correspondingly screwed to the at least one second matching hole to lock the second rotating matching component to the first flat section, the at least one second fastening element respectively penetrates the first flat section, and the cap head of the at least one second fastening element is covered by the first cover.

[0023] Optionally, the fan also includes a stopping component for preventing the second rotating matching component from disengaging from the first rotating matching component, and a first fastening element for fixing the stopping component, and in a radial direction intersecting and perpendicular to the rotation axis, one of the second fastening elements and the other second fastening element are located on opposite sides of the first fastening element, and the first cover is also provided with a first notch and a second notch, and the first notch and the second notch are respectively adjacent to the first rotating matching component, and the first notch and the second notch are located on opposite sides of the first cover in the radial direction, and the mounting groove is located between the first notch and the second notch, and the first flat section passes through the first notch and the second notch.

[0024] Optionally, the fan also includes a matching third rotating matching component and a fourth rotating matching component, the first rotating matching component and the third rotating matching component are located on the left and right sides of the fuselage, the rotation axis extends left and right, the fuselage includes a casing, a motor, an exhaust wheel, a first air inlet grille, a second air inlet grille, and an air outlet grille, the casing is provided with a tangential air outlet, the air outlet grille is located at the tangential air outlet, the first air inlet grille and the second air inlet grille are located on the left and right sides of the casing, the exhaust wheel is located inside the casing, the exhaust wheel can rotate around the rotation axis driven by the motor to drive the air flow, and under the drive of the exhaust wheel, the air enters the casing through the first air inlet grille and the second air inlet grille, flows through the exhaust wheel and is further discharged through the air outlet grille.

[0025] Optionally, the first rotating matching component is fixed to the first air inlet grille, the third rotating matching component is fixed to the second air inlet grille, the first rotating matching component is arranged in the central area of ​​the first air inlet grille, and the third rotating matching component is arranged in the central area of ​​the second air inlet grille; the second rotating matching component and the fourth rotating matching component are respectively fixed to the supporting tripod; when the fuselage rotates around the rotation axis relative to the supporting tripod, the first rotating matching component rotates around the rotation axis along with the first air inlet grille and the third rotating matching component rotates around the rotation axis along with the second air inlet grille.

[0026] Optionally, the exhaust wheel is cylindrical, the casing is whistle-shaped, the first air inlet grille and the second air inlet grille are respectively installed and fixed to the casing; the first rotating matching component is integrally formed with the first air inlet grille, and the third rotating matching component is integrally formed with the second air inlet grille.

[0027] Optionally, the fan also includes a first cover and a second cover, the first cover and the second cover are located on the left and right sides of the fan, the second rotating matching component is at least partially covered by the first cover, and the fourth rotating matching component is at least partially covered by the second cover, the first cover is installed on the second rotating matching component, and the second cover is installed on the fourth rotating matching component; the supporting tripod includes a first support rod and a second support rod, the first support rod and the second support rod are located on the left and right sides of the fuselage, the second rotating matching component is fixed to the first support rod, and the fourth rotating matching component is fixed to the second support rod, the first support rod is partially located between the first cover and the second rotating matching component, the first cover and the first rotating matching component jointly hide the second rotating matching component, the second support rod is partially located between the second cover and the fourth rotating matching component, and the second cover and the third rotating matching component jointly hide the fourth rotating matching component.

[0028] Optionally, the first support rod includes a first flat section, the second support rod includes a second flat section, the first flat section and the second flat section are flat in the axial direction, the first flat section and the second flat section are located on the left and right sides of the fuselage, the first flat section is located on the side of the second rotating matching component facing away from the fuselage, the second flat section is located on the side of the fourth rotating matching component facing away from the fuselage, the second rotating matching component is fixed to the first flat section, the fourth rotating matching component is fixed to the second flat section, the first flat section is at least partially covered by the first cover, the second flat section is at least partially covered by the second cover, the first flat section runs through between the first cover and the first rotating matching component, and the second flat section runs through between the second cover and the second rotating matching component.

[0029] Optionally, in the axial direction, the first support rod, the first air inlet grille, the second air inlet grille, and the second support rod are distributed in sequence; in a radial direction intersecting and perpendicular to the rotation axis, the first support rod extends beyond the radially opposite sides of the first air inlet grille, and in a radial direction intersecting and perpendicular to the rotation axis, the second support rod extends beyond the radially opposite sides of the second air inlet grille, and the first support rod and the second support rod are respectively composed of inclined extending pipe sections.

[0030] Optionally, the fuselage can rotate 360 ​​degrees relative to the supporting tripod, and the supporting tripod includes a first support rod, a second support rod, a top connecting rod, a bottom connecting rod, a first bottom extension rod, and a second bottom extension rod, the first support rod and the second support rod are located on the left and right sides of the fuselage, the first support rod and the second support rod extend obliquely, the first support rod, the top connecting rod, and the second support rod are connected in sequence to form a U-shaped frame framed on the fuselage, the first bottom extension rod, the bottom connecting rod, and the second bottom extension rod are connected in sequence to form a U-shaped frame located at the bottom of the fan, the top connecting rod is connected between the upper end of the first support rod and the upper end of the second support rod, the first bottom extension rod is connected between the lower end of the first support rod and one of the left and right ends of the bottom connecting rod, and the second bottom extension rod is connected between the lower end of the second support rod and the other of the left and right ends of the bottom connecting rod.

[0031] Optionally, the supporting tripod further comprises a flexible sheath, wherein the flexible sheath is wrapped around a portion of the top connecting rod and forms a handle for holding together with the portion of the top connecting rod.

[0032] Optionally, the fan also includes a locking piece, the multiple locking grooves are part of the locking piece, the locking piece is installed and fixed on the first rotating matching component and can rotate synchronously with the first rotating matching component, the locking pin is arranged on the second rotating matching component, the fuselage includes a first air inlet grille, the first rotating matching component and the first air inlet grille are made of the same material and are integrally formed, the locking piece and the first rotating matching component are made of different materials and are installed and fixed on the first rotating matching component, the material of the locking piece has stronger wear resistance than the material of the first rotating matching component, and during the rotation of the fuselage around the rotation axis relative to the supporting tripod, the locking piece and the locking pin slide and rub and push the locking pin to telescopically move relative to the second rotating matching component.

[0033] Optionally, the fan also includes a locking piece, which is located between the first rotating matching part and the second rotating matching part. The locking piece includes a concave-convex structure for forming the multiple locking grooves, and the concave-convex structure is arranged around the rotation axis. The concave-convex structure forms a plurality of tooth grooves, and the tooth grooves constitute the locking grooves. When the locking piece rotates around the rotation axis along with the fuselage, the concave-convex structure slides and rubs with the locking pin and pushes the locking pin to telescope.

Brief Description of the Drawings

[0034] Figure 1 A three-dimensional diagram of the fan of the present application;

[0035] Figure 2 Another three-dimensional view of the fan of the present application;

[0036] Figure 3 A cross-sectional view of the fan of the present application (the cross-section is the cross-section where the rotation axis is located and is parallel to the first support rod);

[0037] Figure 4 A cross-sectional view of the fan of the present application (the cross-section is the cross-section where the rotation axis is located and is perpendicular to the first support rod);

[0038] Figure 5 for Figure 3 Enlarged view of the area in the middle B box;

[0039] Figure 6 for Figure 4 Enlarged view of the C-frame area;

[0040] Figure 7 A partial exploded view of the fan of the present application;

[0041] Figure 8 Another partial exploded view of the fan of the present application. [Specific implementation method]

[0042] Please refer to Figures 1 to 8As shown, the fan 1 of the present design includes a fuselage 2 and a support bracket 3, wherein the support bracket 3 is used to support the fuselage 2, and the fuselage 2 can rotate relative to the support bracket 3 around a rotation axis A so as to adjust the pitch angle of the fuselage 2, thereby adjusting the air outlet angle of the fan 1; the fan 1 also includes a matching first rotating matching component 4 and a second rotating matching component 5, a locking pin 600, and a plurality of locking grooves 610 corresponding to the locking pin 600, the first rotating matching component 4 and the second rotating matching component 5 are at least partially nested along an axial direction parallel to the rotation axis A, and as the fuselage 2 rotates relative to the support bracket 3 around the rotation axis A, the first rotating matching component 4 and the second rotating matching component 5 rotate relatively; one of the first rotating matching component 4 and the second rotating matching component 5 is fixed to the fuselage 2, so that the first rotating matching component 4 and the second rotational matching component 5 can rotate synchronously with the fuselage 2; the other of the first rotational matching component 4 and the second rotational matching component 5 is fixed to the support tripod 3; the plurality of locking grooves 610 are located between the first rotational matching component 4 and the second rotational matching component 5, and the plurality of locking grooves 610 can respectively lock and match with the locking pin 600, so that the fuselage 2 can be maintained at different angles relative to the support tripod 3; the locking pin 600 can be elastically telescopic, and the locking pin 600 can be elastically telescopic during the process of the fuselage 2 rotating relative to the support tripod 3 around the rotation axis A to switch between the plurality of locking grooves 610, so that after the fuselage 2 is rotated to a certain angle, the locking pin 600 selectively cooperates with one of the locking grooves 610, so that the fuselage 2 can be maintained at the angle. For this design, with the help of the first rotational matching component 4 and the second rotational matching component 5, the fuselage 2 can be promoted to rotate relative to the support tripod 3; this design can facilitate the user to adjust the pitch angle of the fuselage 2, and improve the user experience of adjusting the pitch angle of the fuselage 2. The shape of the locking pin 600 can be arbitrary, for example, it can also be a spherical shape.

[0043] The first rotating matching component 4 is in radial contact with the second rotating matching component 5 (i.e., the first rotating matching component 4 and the second rotating matching component 5 are in radial contact with each other), and as the first rotating matching component 4 rotates relative to the second rotating matching component 5, the first rotating matching component 4 and the second rotating matching component 5 slide and rub against each other; the locking pin 600 can move telescopically along the axial direction, and the multiple locking grooves 610 are arranged in sequence around the rotation axis A, and the multiple locking grooves 610 extend respectively along the direction perpendicular to the rotation axis A, and the multiple locking grooves 610 are radially distributed relative to the rotation axis A; the second rotating matching component 5 is fixed to the supporting tripod 3, and the fuselage 2 includes a first air inlet grille 20 The first air inlet grille 20 is located on one of the two opposite sides of the fuselage 2 in the axial direction, and the first rotating matching component 4 is fixed to the fuselage 2. Further, the first rotating matching component 4 is fixed to the first air inlet grille 20 and can rotate synchronously with the first air inlet grille 20. The first rotating matching component 4 is arranged in the central area of ​​the first air inlet grille 20. The first air inlet grille 20 includes a plurality of ribs 200 respectively connected to the first rotating matching component 4 in one piece, and the plurality of ribs 200 respectively extend from the first rotating matching component 4 in one piece in a direction away from the rotation axis A. The plurality of ribs 200 are radially distributed around the first rotating matching component 4 on the periphery of the first rotating matching component 4. The rotating matching components are effectively arranged based on the first air inlet grille 20, which is convenient and practical. The first air inlet grille 20 and the first rotating matching component 4 form a disc shape.

[0044] The fan 1 further comprises a stopper 62 and a first fastening element 63. The stopper 62 is used to prevent the second rotating matching component 5 from being separated from the first rotating matching component 4. The first fastening element 63 is used to fix the stopper 62. The first fastening element 63 penetrates the stopper 62 and fixes the stopper 62 to the first rotating matching component 4. The stopper 62 blocks the side of the second rotating matching component 5 that is opposite to the first rotating matching component 4 in the axial direction. A little gap can be reserved between the stopper 62 and the second rotating matching component 5, so that there is a little movable space between the stopper 62 and the second rotating matching component 5 in the axial direction. When the fuselage 2 rotates around the rotation axis A relative to the support stand 3, the stopper 62 rotates along with the first rotating matching component 4 and can slide and rub with the second rotating matching component 5.

[0045] The first rotating matching component 4 includes a locking portion 40, the locking portion 40 is provided with a first matching hole 400 for matching with the first fastening element 63, the first matching hole 400 extends along the rotation axis A, the rotation axis A passes through the first matching hole 400, the locking portion 40 at least partially penetrates the first rotating matching component 4, the first fastening element 63 includes a rod 630 and a cap head 631, the rod 630 passes through the stopper component 62 and is screwed and fixed to the first matching hole 400, the cap head 631 presses the stopper component 62 against the locking portion 40, and the stopper component 62 is at least partially clamped between the end of the locking portion 40 and the cap head 631. In this embodiment, the cap head 631 indirectly presses against the stopper component 62 to press the stopper component 62 against the locking portion 40, specifically, the cap head 631 indirectly presses against the stopper component 62 through the washer 64.

[0046] The second rotating matching component 5 also includes a first barrel 50, which is sleeved on the outside of the locking portion 40 and is located between the fuselage 2 and the stopper 62; the first rotating matching component 4 includes a second barrel 41, which surrounds the periphery of the locking portion 40 and is sleeved on the outside of the first barrel 50. As the fuselage 2 rotates relative to the supporting tripod 3, the locking portion 40 and the second barrel 41 rotate relative to the first barrel 50, and the locking portion 40 and / or the second barrel 41 can slide and rub against the first barrel 50. Such a design is conducive to the effective nesting and stable relative rotation of the first rotating matching component 4 and the second rotating matching component 5.

[0047] The first barrel portion 50 includes the plurality of first reinforcing ribs 500, which are arranged on the inner periphery of the first barrel portion 50, are arranged in sequence around the locking portion 40, and are radially distributed on the periphery of the locking portion 40. Such a design enhances the structural stability of the first barrel portion 50, and facilitates the stable cooperation between the first barrel portion 50 and the locking portion 40.

[0048] The first rotating matching component 4 further includes a first base plate 42, and the second rotating matching component 5 further includes a second base plate 51. The first base plate 42 and the second base plate 51 are spaced and opposite to each other in the axial direction. The plurality of positioning grooves 610 are located between the first base plate 42 and the second base plate 51, and the stopper 62 blocks the side of the second base plate 51 facing away from the first base plate 42. The locking portion 40 is fixedly connected to the first base plate 42, and the locking portion 40 at least partially penetrates the second base plate 51, and the end of the locking portion 40 away from the first base plate 42 abuts against the stopper 62. The second barrel 41 is located between the first base plate 42 and the second base plate 51, and the second barrel 41 extends integrally from the first base plate 42 toward the second base plate 51. The first barrel 50 extends integrally from the second base plate 51 toward the first base plate 42. Such a design promotes a simple and effective matching design of the first rotating matching component 4 and the second rotating matching component 5.

[0049] The stopping component 62 may be a blocking piece. The locking portion 40 integrally extends from the first substrate 42 along the axial direction. The locking portion 40 passes through the second substrate 51 .

[0050] The first barrel 50 and the second barrel 41 surround the rotation axis A respectively. The first barrel 50 and the second barrel 41 are nested along the axial direction. As the fuselage 2 rotates relative to the support tripod 3, the first barrel 50 and the second barrel 41 rotate relatively. The second barrel 41 is sleeved on the outer side of the first barrel 50. The second barrel 41 includes the plurality of convex ribs 410. The plurality of convex ribs 410 are respectively protruding and arranged on the inner periphery of the second barrel 41. The plurality of convex ribs 410 extend respectively along the axial direction. The plurality of convex ribs 410 are arranged in sequence around the first barrel 50. As the fuselage 2 rotates relative to the support tripod 3, the plurality of convex ribs 410 rotate relative to the first barrel 50 and can slide and rub against the outer peripheral surface of the first barrel 50. The plurality of convex ribs 410 enhance the stability of the second barrel 41 and also help to avoid the second barrel 41 and the first barrel 50 from being locked due to large-area contact.

[0051] In the axial direction, the plurality of positioning grooves 610 are located between the first rotating matching component 4 and the second rotating matching component 5, and the positioning pin 600 can telescopically move along the axial direction; the second rotating matching component 5 also includes a third barrel 52, which surrounds the periphery of the first barrel 50, and the first rotating matching component 4 also includes a fourth barrel 43, which surrounds the periphery of the second barrel 41, and the plurality of positioning grooves 610 are located between the fourth barrel 43 and the second barrel 41; the first barrel 50, the second barrel 41, the third barrel 52 surrounds the periphery of the first barrel 50, and the fourth barrel 43 surrounds the periphery of the second barrel 41. The barrel 52 and the fourth barrel 43 surround the rotation axis A respectively, the first barrel 50 and the second barrel 41 are nested along the axial direction, and the third barrel 52 and the fourth barrel 43 are nested along the axial direction. As the fuselage 2 rotates relative to the support tripod 3, the first barrel 50 and the second barrel 41 rotate relatively, and the third barrel 52 and the fourth barrel 43 rotate relatively; as the fuselage 2 rotates relative to the support tripod 3, the first barrel 50 can slide and rub against the second barrel 41 and / or the third barrel 52 can slide and rub against the fourth barrel 43. Such a design is conducive to the effective nesting and stable relative rotational cooperation of the first rotating matching component 4 and the second rotating matching component 5. The multiple ribs 200 extend integrally from the fourth barrel 43 in a direction away from the rotation axis A, and the multiple ribs 200 are radially distributed relative to the fourth barrel 43.

[0052] The first barrel 50, the second barrel 41, and the third barrel 52 are at least partially located between the first substrate 42 and the second substrate 51, respectively. The first barrel 50 and the third barrel 52 are respectively connected to the second substrate 51 in one piece, and the second barrel 41 and the fourth barrel 43 are respectively connected to the first substrate 42 in one piece. Such a design is conducive to realizing the simple and effective matching design and manufacturing of the first rotating matching component 4 and the second rotating matching component 5.

[0053] The second barrel 41 extends toward the second substrate 51 ; the fourth barrel 43 extends integrally from the first substrate 42 , the fourth barrel 43 is sleeved on the outside of the third barrel 52 , the second substrate 51 is located inside the fourth barrel 43 , and the third barrel 52 extends integrally from the second substrate 51 .

[0054] The locking pin 600 is located between the third barrel portion 52 and the first barrel portion 50; the first rotating matching component 4 further includes a plurality of second reinforcing ribs 44, the plurality of second reinforcing ribs 44 protrude from the first base plate 42 toward the second base plate 51, the plurality of second reinforcing ribs 44 are radially distributed relative to the rotation axis A, and the plurality of second reinforcing ribs 44 are located between the second barrel portion 41 and the fourth barrel portion 43; the fan 1 further includes a locking member 61, the locking member 61 is located between the first rotating matching component 4 and the second rotating matching component 5, further, the locking member 61 is located between the first base plate 42 and the second base plate 51, the plurality of locking grooves 610 are part of the locking member 61, the locking member 61 is provided with at least two positioning protrusions 611, the at least two positioning protrusions 611 are located between the second barrel portion 41 and the fourth barrel portion 43, and each positioning protrusion 611 is respectively fixed between two corresponding second reinforcing ribs 44. Each positioning protrusion 611 is respectively engaged with two corresponding adjacent second reinforcing ribs 44 by interference, and is thus locked. In this embodiment, the number of the positioning protrusions 61 is 4. The positioning member 61 can be formed by a gear ring or an arc-shaped rack, and the positioning member 61 is located between the fourth barrel portion 43 and the second barrel portion 41 .

[0055] The locking pin 600 is mounted on the second rotating matching component 5. The fan 1 also includes an elastic element 601 corresponding to the locking pin 600. The elastic element 601 and the locking pin 600 are assembled on the second rotating matching component 5. The elastic element 601 can be extended and retracted along the axial direction. The elastic element 601 is used to elastically support the locking pin 600 to provide elastic reset force to the locking pin 600, and support the locking pin 600 to be able to elastically retract and move. The second rotating matching component 5 also includes a mounting cavity 530. The elastic element 601 is installed in the mounting cavity 530. The locking pin 600 is at least partially located in the mounting cavity 530 and can be retracted and moved relative to the mounting cavity 530. The locking pin 600 can be at least partially embedded in the locking groove 610 under the push of the elastic element 601 to engage with the locking groove 610. The second rotating matching component 5 also includes a barrel portion 53 surrounding the mounting cavity 530.

[0056] The fan 1 also includes a first cover 10, which at least partially covers the second rotating matching component 5. The first cover 10 is installed on the second rotating matching component 5. As the fuselage 2 rotates relative to the supporting stand 3, the first rotating matching component 4 rotates relative to the first cover 10; the second rotating matching component 5 is located in a receiving cavity 11 defined by the first cover 10 and the first rotating matching component 4; the supporting stand 3 includes a first support rod 30 and a second support rod 31, the first support rod 30 and the second support rod 31 are located on the left and right sides of the fuselage 2, the first support rod 30 and the second support rod 31 extend obliquely, and the first support rod 30 passes through the receiving cavity 11. Specifically, the first support rod 30 passes through the receiving cavity 11 obliquely, a part of the first support rod 30 is located in the receiving cavity 11 and is covered by the first cover 10, and the second rotating matching component 5 is fixed to the said part of the first support rod 30. The first cover 10 is provided with a plurality of hook portions 100, and the second rotational matching component 5 is provided with a plurality of engaging grooves 54. The plurality of hook portions 100 and the plurality of engaging grooves 54 are correspondingly buckled together, so that the first cover 10 is mounted and fixed on the second rotational matching component 5. The plurality of engaging grooves 54 are distributed on the third barrel portion 52. In this embodiment, the number of the hook portions 100 and the number of the engaging grooves 54 are respectively 4.

[0057] The fan 1 further includes at least one second fastening element 65, which is used to lock the second rotating matching component 5 to the first support rod 30. The first support rod 30 includes a first flat section 300, which is located on the side of the second rotating matching component 5 facing away from the fuselage 2. The first flat section 300 is flat in the axial direction. The first cover 10 at least partially covers the first flat section 300. The at least one second fastening element 65 is located in the receiving cavity 11. The at least one second fastening element 65 locks the second rotating matching component 5 to the first flat section 300. The part of the first support rod 30 belongs to a part of the first flat section 300. The first flat section 300 has high adaptability, and is more convenient to be locked with the second rotating matching component 5 for the adaptability structural design requirements of the second rotating matching component 5 and the first cover 10.

[0058] The stopping component 62 is located between the first rotating matching component 4 and the first flat section 300. When the fuselage 2 rotates around the rotation axis A relative to the supporting tripod 3, the first fastening element 63 and the stopping component 62 rotate synchronously with the fuselage 2, and the first flat section 300 does not contact the first fastening element 63 and the stopping component 62, and does not hinder the rotation of both the first fastening element 63 and the stopping component 62. The first flat section 300 is provided with at least one clearance hole 3000 for avoiding the first fastening element 63, and the rotation axis A passes through the at least one clearance hole 3000, and the at least one clearance hole 3000 is covered by the first cover 10.

[0059] The first flat section 300 obliquely penetrates the receiving cavity 11, the second fastening element 65 can be a screw, and the second rotating matching component 5 is further provided with a mounting groove 55 corresponding to the first flat section 300 and at least one second matching hole 56 corresponding to the at least one second fastening element 65. The mounting groove 55 is located on the side of the second rotating matching component 5 facing away from the fuselage 2, the first flat section 300 is partially embedded in the mounting groove 55, and the mounting groove 55 extends through the radially opposite sides of the second rotating matching component 5 in a radial direction perpendicular to the rotation axis A; the at least one second fastening element 65 is at least partially located in the mounting groove 55, and the at least one second fastening element 65 is correspondingly screwed to the at least one second matching hole 56 to lock the second rotating matching component 5 to the first flat section 300; the at least one second fastening element 65 penetrates the first flat section 300, and the cap 650 of the at least one second fastening element 65 is covered by the first cover 10. The second matching hole 56 penetrates the first substrate 42.

[0060] In the radial direction intersecting and perpendicular to the rotation axis A, one of the second fastening elements 65 and the other second fastening element 65 are located on opposite sides of the first fastening element 63, so as to more evenly fix the first flat section 300 and the second rotating matching component 5; the first cover 10 is also provided with a first notch 101 and a second notch 102, the first notch 101 and the second notch 102 are respectively adjacent to the first rotating matching component 4, the first notch 101 and the second notch 102 are located on opposite sides of the first cover 10 in the radial direction, the mounting groove 55 is located between the first notch 101 and the second notch 102, and the first flat section 300 passes through the first notch 101 and the second notch 102. Such a design is conducive to compact space utilization. The first notch 101 and the second notch 102 are respectively connected to the receiving chamber 11 and the outside of the fan 1.

[0061] The fan 1 also includes a third rotating matching component 120 and a fourth rotating matching component 121, the first rotating matching component 4 and the third rotating matching component 120 are located on the left and right sides of the fuselage 2, and the rotation axis A extends left and right. The fuselage 2 includes a housing 21, a motor 22, an exhaust wheel 23, a second air inlet fence 24, and an air outlet fence 25. The fuselage 2 discharges air tangentially. The housing 21 is provided with a tangential air outlet 210. The fuselage 2 discharges air tangentially through the tangential air outlet 210; the air outlet fence 25 is located at the tangential air outlet 210. The first air inlet grille 20 and the second air inlet grille 24 are located on the left and right sides of the housing 21, and the exhaust wheel 23 is located inside the housing 21. The exhaust wheel 23 can rotate around the rotation axis A driven by the motor 22 to drive the air flow. Driven by the exhaust wheel 23, the air enters the housing 21 through the first air inlet grille 20 and the second air inlet grille 24, and is further discharged through the exhaust grille 25 after passing through the exhaust wheel 23. The first air inlet grille 20, the second air inlet grille 24, and the exhaust grille 25 are respectively fixed to the housing 21. The motor 22 includes a rotating shaft 220, which is fixedly connected to the exhaust wheel 23 so as to drive the exhaust wheel 23 to rotate. The rated power of the motor 22 is between 50w and 3300 watts. The motor 22 is located inside the housing 21 and is fixedly mounted on the housing 21.

[0062] The first rotating matching component 4 is fixed to the first air inlet grille 20, and the third rotating matching component 120 is fixed to the second air inlet grille 24. The first rotating matching component 4 is arranged in the central area of ​​the first air inlet grille 20, and the third rotating matching component 120 is arranged in the central area of ​​the second air inlet grille 24; the second rotating matching component 5 and the fourth rotating matching component 121 are respectively fixed to the supporting stand 3; when the fuselage 2 rotates around the rotation axis A relative to the supporting stand 3, the first rotating matching component 4 rotates around the rotation axis A along with the first air inlet grille 20 and the third rotating matching component 120 rotates around the rotation axis A along with the second air inlet grille 24. With such a design, the structure of the fan 1 is novel and practical. The second air inlet grille 24 and the third rotating matching component both form a disc shape.

[0063] The exhaust wheel 23 is cylindrical, and the casing 21 is whistle-shaped. The first air inlet grille 20 and the second air inlet grille 24 are respectively installed and fixed to the casing 21. Furthermore, the first air inlet grille 20 and the second air inlet grille 24 are respectively locked to the casing 21 by a plurality of screws; the first rotating matching component 4 is integrally formed with the first air inlet grille 20, thereby fixed to the first air inlet grille 20, ensuring the consistency of the first air inlet grille 20 and the first rotating matching component 4; the third rotating matching component 120 is integrally formed with the second air inlet grille 24, thereby fixed to the second air inlet grille 24, ensuring the consistency of the second air inlet grille 24 and the third rotating matching component 120.

[0064] In this embodiment, the second rotational matching component 5 is the same as the fourth rotational matching component 121 and can be used interchangeably, which also causes the second rotational matching component 5 and the fourth rotational matching component 121 to be not completely symmetrical on the fan 1. The structure of the third rotational matching component 120 is the same as the base plate of the first rotational matching component 4, and will not be repeated. In this embodiment, a locking member and a locking pin are also provided between the third rotational matching component 120 and the fourth rotational matching component 121.

[0065] The fan 1 further includes a second cover 13, the first cover 10 and the second cover 13 are located on the left and right sides of the fan 1, the second rotational matching component 5 is at least partially covered by the first cover 10, the fourth rotational matching component 121 is at least partially covered by the second cover 13, and the second cover 13 is mounted on the fourth rotational matching component 121; the second rotational matching component 5 is fixed to the first support rod 30, the fourth rotational matching component 121 is fixed to the second support rod 31, the first support rod 30 is partially located between the first cover 10 and the second rotational matching component 5, the first cover 10 and the first rotational matching component 4 jointly hide the second rotational matching component 5, the second support rod 31 is partially located between the second cover 13 and the fourth rotational matching component 121, and the second cover 13 and the third rotational matching component 120 jointly hide the fourth rotational matching component 121. The edge of the first cover 10 surrounding the rotation axis A is nested with the edge of the first rotational matching component 4 surrounding the rotation axis A.

[0066] The second support rod 31 includes a second flat section 310. The first flat section 300 and the second flat section 310 are flat in the axial direction. The first flat section 300 and the second flat section 310 are located on the left and right sides of the fuselage 2. The first flat section 300 is located on the side of the second rotating matching component 5 that is away from the fuselage 2. The second flat section 310 is located on the side of the fourth rotating matching component 121 that is away from the fuselage 2. The second rotating matching component 5 is fixed to the first flat section 300, and the fourth rotating matching component 121 is fixed to the second flat section 310. The first flat section 300 is at least partially covered by the first cover 10, and the second flat section 310 is at least partially covered by the second cover 13. The first flat section 300 runs through between the first cover 10 and the first rotating matching component 4, and the second flat section 310 runs through between the second cover 13 and the second rotating matching component 5.

[0067] In the axial direction, the first support rod 30, the first air inlet grille 20, the second air inlet grille 24, and the second support rod 31 are distributed in sequence. In the radial direction intersecting and perpendicular to the rotation axis A, the first support rod 30 extends beyond the radially opposite sides of the first air inlet grille 20, and in the radial direction intersecting and perpendicular to the rotation axis A, the second support rod 31 extends beyond the radially opposite sides of the second air inlet grille 24. The first support rod 30 and the second support rod 31 are respectively composed of inclined extending pipe sections. With such a design, although the first support rod 30 and the second support rod 31 extend beyond the radially opposite sides of the corresponding air inlet grille, the air inlet obstruction to the air inlet grille is relatively weak, which is conducive to ensuring the air inlet efficiency of the fan 1.

[0068] The fuselage 2 can rotate 360 ​​degrees relative to the support stand 3. The support stand 3 also includes a top connecting rod 32, a bottom connecting rod 33, a first bottom extension rod 34, and a second bottom extension rod 35. The first support rod 30 and the second support rod 31 extend obliquely. The first support rod 30, the top connecting rod 32, and the second support rod 31 are connected in sequence to form a U-shaped frame framed on the fuselage 2. The first bottom extension rod 34, the bottom connecting rod 33, and the second bottom extension rod 35 are connected in sequence to form a U-shaped frame located at the bottom of the fan 1. The top connecting rod 32 is connected between the upper end of the first support rod 30 and the upper end of the second support rod 31. The first bottom extension rod 34 is connected between the lower end of the first support rod 30 and one of the left and right ends of the bottom connecting rod 33. The second bottom extension rod 35 is connected between the lower end of the second support rod 31 and the other of the left and right ends of the bottom connecting rod 33. Such a design makes the support stand 3 of the fan 1 simple and stable in structure, which is conducive to its reliable support of the fuselage 2.

[0069] The support stand 3 further comprises a flexible sheath 36, which is wrapped around a portion of the top connecting rod 32 and forms a grip for holding with the portion of the top connecting rod 32. The user can hold the grip to lift or drag the fan 1. The flexible sheath 36 can be made of rubber.

[0070] The locking member 61 is installed and fixed on the first rotating matching component 4 and can rotate synchronously with the first rotating matching component 4. The locking pin 600 is set on the second rotating matching component 5. During the rotation of the fuselage 2 around the rotation axis A relative to the supporting tripod 3, the locking member 61 and the locking pin 600 slide and rub against each other and push the locking pin 600 to telescopically move relative to the second rotating matching component 5; the first rotating matching component 4 and the first air inlet grille 20 are made of the same material and are integrally formed. The locking member 61 and the first rotating matching component 4 are made of different materials and are installed and fixed on the first rotating matching component 4. The wear resistance of the material of the locking member 61 is stronger than that of the material of the first rotating matching component 4. In order to prevent the locking member 61 from being easily worn by the locking pin 600, the locking member 61 needs to be made of a material with relatively good wear resistance. The first air inlet grille 20 and the first rotating matching component 4 use more materials. If the first air inlet grille 20 and the first rotating matching component 4 use the same material as the locking member 61, the material cost of the first air inlet grille 20 and the first rotating matching component 4 will be greatly increased. Based on this design, the locking member 61 can be independently selected from the first air inlet grille 20 and the first rotating matching component 4. Similarly, the first air inlet grille 20 and the first rotating matching component 4 can be independently selected from the locking member 61. In summary, this design is beneficial to reducing the material cost of the first air inlet grille 20 and the first rotating matching component 4, while achieving relatively free material selection for the locking member 61 to ensure the wear resistance of the locking member 61. In this embodiment, the first air inlet grille 20 and the first rotating matching component 4 are made of polypropylene plastic material, and the locking member 61 is made of polyoxymethylene plastic material.

[0071] The locking member 61 includes a concave-convex structure 612 for forming the plurality of locking grooves 610. The concave-convex structure 612 is arranged around the rotation axis A. The concave-convex structure 612 is formed with the plurality of tooth grooves, which constitute the locking grooves 610. When the locking member 61 rotates around the rotation axis A along with the fuselage 2, the concave-convex structure 612 slides and rubs with the locking pin 600 and pushes the locking pin 600 to move telescopically. The locking pin 600 abuts against the surface of the concave-convex structure 612. The support stand 3 also includes a plurality of support foot pads 37 at the bottom thereof.

Claims

1. A fan, comprising a body and a support frame for supporting the body, wherein the body can rotate relative to the support frame about a rotation axis, and wherein: The fan also includes a matching first rotating matching component and a second rotating matching component, a locking pin, and a plurality of locking grooves corresponding to the locking pin, wherein the first rotating matching component and the second rotating matching component are at least partially nested along an axial direction parallel to the rotation axis, and the first rotating matching component and the second rotating matching component rotate relatively as the fuselage rotates around the rotation axis relative to the supporting tripod; one of the first rotating matching component and the second rotating matching component is fixed to the fuselage, and the other of the first rotating matching component and the second rotating matching component is fixed to the supporting tripod; the plurality of locking grooves are located between the first rotating matching component and the second rotating matching component, and the plurality of locking grooves can be respectively locked and matched with the locking pin so that the fuselage can be maintained at different angles relative to the supporting tripod; the locking pin can elastically telescopically move during the rotation of the fuselage around the rotation axis relative to the supporting tripod to switch between the plurality of the locking grooves.

2. The fan according to claim 1, characterized in that: The first rotating matching component is in radial contact with the second rotating matching component, and as the first rotating matching component rotates relative to the second rotating matching component, the first rotating matching component and the second rotating matching component slide and rub against each other; the locking pin can telescopically move along the axial direction, and the multiple locking grooves are arranged in sequence around the rotation axis, and the multiple locking grooves are radially distributed relative to the rotation axis; the second rotating matching component is fixed to the supporting tripod, and the fuselage includes a first air inlet grille, and the first air inlet grille is located on one of the opposite sides of the fuselage in the axial direction. The first rotating matching component is fixed to the first air inlet grille and can rotate synchronously with the first air inlet grille. The first rotating matching component is arranged in the central area of ​​the first air inlet grille, and the first air inlet grille includes a plurality of ribs respectively connected to the first rotating matching component as an integral whole, and the plurality of ribs are radially distributed around the first rotating matching component on the periphery of the first rotating matching component.

3. The fan according to claim 1, characterized in that: The first rotating matching component is fixed to the fuselage, and the second rotating matching component is fixed to the supporting bracket; the fan also includes a stopping component for preventing the second rotating matching component from detaching from the first rotating matching component, and a first fastening element for fixing the stopping component, and the first fastening element penetrates the stopping component and fixes the stopping component to the first rotating matching component.

4. The fan according to claim 3, characterized in that: The first rotating matching component includes a locking portion, and the locking portion is provided with a first matching hole for matching with the first fastening element. The first matching hole extends along the rotation axis, and the rotation axis passes through the first matching hole. The locking portion at least partially penetrates the first rotating matching component, and the stopping component blocks the side of the second rotating matching component that is away from the fuselage in the axial direction. The first fastening element includes a rod portion and a cap head. The rod portion of the first fastening element passes through the stopping component and is screwed and fixed to the first matching hole. The cap head of the first fastening element presses the stopping component against the locking portion, and the stopping component is at least partially clamped between the end of the locking portion and the cap head of the first fastening element.

5. The fan according to claim 3, characterized in that: The first rotating matching component includes a locking part, and the second rotating matching component includes a first barrel, and the first barrel is sleeved on the outside of the locking part; the first rotating matching component includes a second barrel, and the second barrel surrounds the periphery of the locking part, and the second barrel is sleeved on the outside of the first barrel. As the fuselage rotates relative to the supporting tripod, the locking part and the second barrel rotate relative to the first barrel, and the locking part and / or the second barrel can slide and rub with the first barrel.

6. The fan according to claim 5, characterized in that: The first barrel portion includes a plurality of first reinforcing ribs, the plurality of first reinforcing ribs are arranged on the inner circumference of the first barrel portion, the plurality of first reinforcing ribs are sequentially arranged around the locking portion, and the plurality of first reinforcing ribs are radially distributed on the periphery of the locking portion.

7. The fan according to claim 5, characterized in that: The first rotating matching component also includes a first substrate, and the second rotating matching component also includes a second substrate. The first substrate and the second substrate are spaced apart and opposite to each other in the axial direction, and the multiple positioning grooves are located between the first substrate and the second substrate. The stopping component blocks the side of the second substrate facing away from the first substrate; the locking portion is fixedly connected to the first substrate, and the locking portion at least partially penetrates into the second substrate, and the end of the locking portion away from the first substrate abuts against the stopping component; the second barrel is located between the first substrate and the second substrate, and the second barrel extends integrally from the first substrate toward the second substrate; the first barrel extends integrally from the second substrate toward the first substrate.

8. The fan according to claim 7, characterized in that: The blocking component is a blocking piece, the locking portion integrally extends from the first substrate along the axial direction, and the locking portion penetrates the second substrate.

9. The fan according to claim 1, characterized in that: The second rotating matching component includes a first barrel portion, and the first rotating matching component includes a second barrel portion. The first barrel portion and the second barrel portion are respectively surrounded by the rotation axis, and the second barrel portion is sleeved on the outside of the first barrel portion. The second barrel portion includes a plurality of convex ribs, and the plurality of convex ribs are respectively protruding from the inner circumference of the second barrel portion. The plurality of convex ribs extend along the axial direction respectively, and the plurality of convex ribs are arranged in sequence around the first barrel portion. As the fuselage rotates relative to the supporting tripod, the plurality of convex ribs rotate relative to the first barrel portion and can slide and rub against the outer peripheral surface of the first barrel portion.

10. The fan according to claim 1, characterized in that: In the axial direction, the multiple locking grooves are located between the first rotating matching component and the second rotating matching component, and the locking pin can telescopically move along the axial direction; the second rotating matching component includes a first barrel and a third barrel, and the third barrel surrounds the outer periphery of the first barrel; the first rotating matching component includes a second barrel and a fourth barrel, and the fourth barrel surrounds the outer periphery of the second barrel, and the multiple locking grooves are located between the fourth barrel and the second barrel; the first barrel, the second barrel, the third barrel, and the fourth barrel respectively surround the rotation axis, the first barrel and the second barrel are nested along the axial direction, and the third barrel and the fourth barrel are nested along the axial direction, as the fuselage rotates relative to the supporting tripod, the first barrel and the second barrel rotate relatively and the third barrel and the fourth barrel rotate relatively; as the fuselage rotates relative to the supporting tripod, the first barrel can slide and rub with the second barrel and / or the third barrel can slide and rub with the fourth barrel.

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