Propeller, propelling device and water area movable equipment

Abstract

The invention provides a propeller (100), a propelling device (1000) and water area movable equipment (2000). The propeller (100) comprises a machine body (10) and a tilting support (20). The warping support (20) is used for being detachably connected with a clamp (200) fixed to a carrier. The machine body (10) is rotationally connected with the tilting support (20) so as to tilt relative to the clamp (200) through the tilting support (20). And after the tilting bracket (20) is separated from the clamp (200), the tilting bracket (20) can move relative to the fuselage (10) until the tilting bracket (20) is folded with the fuselage (10).

Description

Technical Field

[0001] The present disclosure relates to the technical field of mobile equipment in water areas, and in particular to a propeller, a propulsion device and a mobile equipment in water areas. Background Art

[0002] The propeller is installed on a carrier in the water area and can push the carrier to move in the water area. In order to facilitate the disassembly and maintenance of the propeller, the propeller will be equipped with a connection mechanism to stabilize or disassemble it with the ship. However, in order to enhance the stability of the connection with the ship, the current propeller will be equipped with more locking parts in the connection mechanism, resulting in a complex structure and heavy weight of the connection mechanism, which affects the overall portability of the propeller. Summary of the invention

[0003] Embodiments of the present disclosure provide a propeller, a propulsion device, and a movable device in water areas.

[0004] An embodiment of the present disclosure provides a propeller, which includes a body and a lifting bracket, wherein the lifting bracket is used to be detachably connected to a clamp fixed on a carrier, and the body is rotatably connected to the lifting bracket so as to be lifted relative to the clamp through the lifting bracket. After the lifting bracket is detached from the clamp, the lifting bracket can move relative to the body until it is folded with the body.

[0005] An embodiment of the present disclosure provides a propulsion device, which includes a fuselage, a clamp and a lifting bracket, wherein the clamp is used to be fixed to a carrier; the lifting bracket is detachably connected to the clamp, and the fuselage is rotatably connected to the lifting bracket so as to be lifted relative to the clamp through the lifting bracket. After the lifting bracket is detached from the clamp, the lifting bracket can move relative to the fuselage until it is folded with the fuselage.

[0006] An embodiment of the present disclosure provides a movable device for use in water areas, which includes a carrier and a propulsion device, wherein the propulsion device includes a fuselage, a clamp and a lifting bracket, wherein the clamp is fixed to the carrier; the lifting bracket is detachably connected to the clamp, and the fuselage is rotatably connected to the lifting bracket so as to be lifted relative to the clamp by the lifting bracket, and after the lifting bracket is detached from the clamp, the lifting bracket can move relative to the fuselage until it is folded with the fuselage.

[0007] The propeller, propulsion device and movable water vehicle provided by the present invention are configured such that the tilting bracket is detachably connected to a clamp, and can move relative to the fuselage to be folded with the fuselage after being detached from the clamp, so as to complete the storage of the tilting bracket, making the entire propeller easy to install or disassemble and convenient to carry.

[0008] Additional aspects and advantages of the embodiments of the present disclosure will be given in part in the following description and in part will be obvious from the following description or will be learned through practice of the embodiments of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] The above and / or additional aspects and advantages of the present disclosure will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0010] Figure 1a is a schematic diagram of the three-dimensional structure of a propeller according to an embodiment of the present disclosure;

[0011] Figure 1b yes Figure 1a A schematic diagram of the three-dimensional structure of the propeller after the lifting bracket is stored relative to the fuselage;

[0012] Figure 2 yes Figure 1a A schematic diagram of a three-dimensional structure in which a thruster is assembled on a fixture;

[0013] Figure 3 yes Figure 1a A schematic diagram of the structure of the propeller in a top-down view;

[0014] Figure 4a yes Figure 3 A schematic diagram of the cross-sectional structure of the propeller along the AA direction;

[0015] Figure 4b yes Figure 4a A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0016] Figure 4c yes Figure 4a A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0017] Figure 4d yes Figure 4a A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0018] Figure 5 is a schematic diagram of the partial structure of the propeller of Figure 1;

[0019] Figure 6 yes Figure 4a A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0020] Figure 7a is a schematic diagram of the three-dimensional structure of a propeller according to an embodiment of the present disclosure;

[0021] Figure 7b yes Figure 7a A schematic diagram of the three-dimensional structure of the propeller after the lifting bracket is stored relative to the fuselage;

[0022] Figure 8 yes Figure 7a A schematic diagram of a three-dimensional structure in which a propeller is assembled on a fixture;

[0023] Fig. 9 yes Figure 7a Schematic diagram of the partial structure of the propeller;

[0024] Fig.10 yes Figure 7a A schematic diagram of a cross-sectional structure of a propeller in a front view direction;

[0025] Fig.11 yes Fig.10 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0026] Fig.12 yes Fig.11 A schematic cross-sectional structural diagram of a propeller in a right-view direction;

[0027] Fig.13 yes Fig.10 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0028] Fig.14 yes Fig.13 A schematic diagram of the structure of the enlarged region I of the thruster;

[0029] Fig.15 yes Fig.10 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0030] Fig.16 yes Fig.15 A schematic cross-sectional structural diagram of a propeller;

[0031] Fig.17 yes Fig.16 Schematic diagram of the structure of the enlarged II region;

[0032] Fig.18 yes Fig.16 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0033] Fig.19 is a partial cross-sectional structural schematic diagram of a propeller provided in one embodiment of the present disclosure;

[0034] Fig. 20 yes Fig.19 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0035] Fig.21 yes Fig.19 A schematic partial cross-sectional view of a propeller in another embodiment;

[0036] Fig. 22 yes Fig.21 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0037] Fig.23 yes Fig.19 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0038] Fig.24 yes Fig.19 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0039] Fig.25 yes Fig.19 A schematic cross-sectional structural diagram of a propeller in another embodiment;

[0040] Fig.26 is a schematic structural diagram of a propeller provided in one embodiment of the present disclosure;

[0041] Fig. 27 yes Fig.26 A schematic diagram of a cross-sectional structure of a propeller in a front view direction;

[0042] Fig.28 yes Fig.26 A schematic cross-sectional structural diagram of a propeller in a right-side view in another embodiment;

[0043] Fig.29 yes Fig.26 A schematic structural diagram of a propeller in a top view in another embodiment;

[0044] Fig.30 yes Fig.29 A schematic diagram of a cross-sectional structure of a propeller in a top-down direction;

[0045] Fig.31 yes Fig.26 A schematic structural diagram of a propeller in a top view in another embodiment;

[0046] Fig.32a yes Fig.31 A schematic diagram of a cross-sectional structure of a propeller in a non-use state when viewed from above;

[0047] Figure 32b yes Fig.31 A schematic diagram of a cross-sectional structure of a propeller in a use state when viewed from above;

[0048] Fig.33a yes Fig.26 A schematic structural diagram of a propeller in another embodiment when viewed from above in a non-use state;

[0049] Fig.33b yes Fig.26 A schematic diagram of the structure of a propeller in another embodiment when in use, viewed from above;

[0050] Fig.34a yes Fig.33a A schematic structural diagram of a propeller in another embodiment when viewed from above in a non-use state;

[0051] Fig.34b yes Fig.33a A schematic diagram of the structure of a propeller in another embodiment when in use, viewed from above;

[0052] Fig.35 yes Fig.26 A schematic structural diagram of a propeller in a top view in another embodiment;

[0053] Fig.36 is a schematic diagram of an exploded structure of a propulsion device provided in one embodiment of the present disclosure;

[0054] Fig.37 yes Fig.36 A schematic diagram of the three-dimensional structure of the fixture;

[0055] Fig.38 yes Fig.36 A schematic diagram of the three-dimensional structure of the warping bracket;

[0056] Fig.39 yes Fig.36 A schematic diagram of an exploded structure of a propulsion device in another embodiment;

[0057] Fig.40 is a schematic diagram of an exploded structure of a propulsion device provided in one embodiment of the present disclosure;

[0058] Fig.41 It is a schematic diagram of a movable device for water area provided by one embodiment of the present disclosure. DETAILED DESCRIPTION

[0059] The embodiments of the present disclosure are further described below in conjunction with the accompanying drawings. The same or similar reference numerals in the accompanying drawings represent the same or similar elements or elements with the same or similar functions.

[0060] In addition, the embodiments of the present disclosure described below in conjunction with the accompanying drawings are exemplary and are only used to explain the embodiments of the present disclosure, and should not be construed as limiting the present disclosure.

[0061] In the present disclosure, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0062] The propeller converts internal energy or electrical energy into mechanical energy, and then converts it into kinetic energy (i.e., propulsion) through mechanical transmission and propeller, so as to drive the carrier forward or backward. The carrier is preferably the hull of a boat of the type of water area inspection equipment, water area environment monitoring equipment, etc. The fixture is generally fixed to the tail of the carrier, and then the propeller is installed and fixed on the fixture, so that the propeller and the carrier are relatively fixed, and the propulsion force generated by the propeller can fully act on the carrier.

[0063] Since the clamp is relatively cheap, has a relatively high structural strength, has no electronic devices, and is highly water-resistant, the clamp and carrier are usually not disassembled. Unlike the clamp, the thruster is relatively expensive, and there are circuit boards, gears, motors and other devices inside the thruster. Therefore, it is usually recommended that users only install and fix the thruster to the clamp when traveling, and only disassemble the thruster and the clamp after the trip, so as to store the thruster separately and avoid affecting the life of the thruster.

[0064] In order to fix the thruster on the fixture, the thruster needs to be designed with a mounting structure that matches the fixture. This mounting structure generally protrudes from the body of the thruster, causing the thruster to occupy a large space as a whole, making it less convenient to store the thruster after the trip. In addition, the fixing method of the fixture and the thruster is usually complicated, which makes it cumbersome for users to disassemble and assemble, which is less convenient and provides a poor user experience.

[0065] To solve the above technical problems, please refer to Figure 1a to Figure 2 The embodiment of the present disclosure provides a propeller 100, which includes a body 10 and a tilting bracket 20. The tilting bracket 20 is used to be detachably connected to a clamp 200 fixed on a carrier. The body 10 is rotatably connected to the tilting bracket 20 so as to be tilted relative to the clamp 200 through the tilting bracket 20. After the tilting bracket 20 is separated from the clamp 200, the tilting bracket 20 can move relative to the body 10 until it is folded with the body 10.

[0066] It is understandable that the detachable connection between the tilting bracket 20 and the clamp 200 is preferably a tool-free disassembly and assembly method such as plug-in, clip-on, cam locking, etc., so as to facilitate the user to disassemble and assemble. When in use, the tilting bracket 20 and the clamp 200 are kept in a relatively fixed state to prevent the tilting bracket 20 from shaking relative to the clamp 200 and affecting the operation of the propeller 100.

[0067] The rotational connection between the fuselage 10 and the tilting bracket 20 may be a direct connection between the fuselage 10 and the tilting bracket 20, a rotation pair is formed between the fuselage 10 and the tilting bracket 20, and relative rotation is achieved by relying on the rotation pair, or an indirect connection between the fuselage 10 and the tilting bracket 20, for example, an additional component is provided between the fuselage 10 and the tilting bracket 20, a rotation pair is formed between the component and the fuselage 10, or a rotation pair is formed between the component and the tilting bracket 20, and relative rotation between the fuselage 10 and the tilting bracket 20 is achieved by relying on the rotation pair. The relative rotation between the fuselage 10 and the tilting bracket 20 allows the fuselage 10 to tilt relative to the fixture 200 to change the pitch angle of the propulsion force, or change the height of the fuselage 10 relative to the water surface, so that the fuselage 10 is out of the water surface or immersed in the water. It is understandable that, in an ideal situation, if the carrier is not tilted on the water surface, the tilting movement of the fuselage 10 is completed in the vertical plane, but in general, due to the uneven distribution of gravity of the goods or people on the carrier, the carrier will be slightly tilted relative to the water surface, so that the tilting movement of the fuselage 10 is not absolutely located in the vertical plane, that is, the tilting plane deviates from the vertical plane. Therefore, the definitions of reference planes and reference directions such as vertical planes, horizontal planes, vertical directions, and horizontal directions in the following text are only for understanding the technical solutions of the present disclosure, and should not be used to limit the present disclosure.

[0068] It is understandable that, in the present application, the tilting bracket 20 is a mechanism for connecting the fuselage 10 and the clamp 200. In order to provide the fuselage 10 with the degree of freedom to tilt and to be installed in pair with the clamp 200, the tilting bracket 20 needs to have a certain protrusion relative to the fuselage 10. However, it is precisely because the tilting bracket 20 is partially protruding relative to the fuselage 20 that the tilting bracket 20 affects the overall volume of the propeller 100, which is not convenient to carry. Therefore, in the propeller 100 provided in the embodiment of the present disclosure, after the tilting bracket 20 is separated from the clamp 200, the tilting bracket 20 can move relative to the fuselage 10 to be folded with the fuselage 10, so that the tilting bracket 20 no longer protrudes, or the protrusion becomes smaller, thereby reducing the space occupied by the propeller 100, reducing the difficulty of storage, and improving portability. The folding of the tilting bracket 20 and the fuselage 10 can be understood as that after the propeller 100 is removed from the clamp, at least a part of the tilting bracket 20 is folded with the fuselage 10 to achieve a closer spatial position relationship with the fuselage 10 (they can be in contact with each other or have an air gap), so as to meet the requirement that the propeller as a whole is more regular in space and easy to carry. The relative movement of the tilting bracket 20 and the fuselage 10 can be a rotational connection between the tilting bracket 20 and the fuselage 10, and the tilting bracket 20 rotates relative to the fuselage 10 until it is folded with the fuselage 10. The relative movement of the tilting bracket 20 and the fuselage 10 can also be a sliding connection between the tilting bracket 20 and the fuselage 10, and the tilting bracket 20 slides relative to the fuselage 10 until it is folded with the fuselage 10. Of course, the relative movement of the tilting bracket 20 and the fuselage 10 can also be understood as a combination of the tilting bracket 20 rotating and sliding relative to the fuselage 10 to move to fold with the fuselage 10.

[0069] Therefore, the tilting bracket 20 is arranged to be movable relative to the body 10 to be folded with the body 10 after being separated from the clamp 200, so as to complete the storage of the tilting bracket 20, thereby reducing the space occupied by the entire propeller 100. At the same time, the tilting bracket 20 and the clamp 200 are arranged to be detachably connected, so that the tilting bracket 20 and the clamp 200 are easy to disassemble and assemble before and after the propeller 100 is used, thereby improving convenience and being conducive to improving user experience.

[0070] The fuselage 10 of the propeller 100 provided in the present disclosure is described in detail below.

[0071] In one embodiment of the present disclosure, a propeller 100 is provided. Please continue to refer to Figure 1a to Figure 2The fuselage 10 includes an above-water portion 11a and an underwater portion 11b. The above-water portion 11a refers to the portion of the fuselage 10 that is exposed above the water surface when the propeller 100 is in use, and the underwater portion 11b refers to the portion of the fuselage 10 that is immersed below the water surface when the propeller 100 is in use. The lifting bracket 20 is installed on the horizontal side of the above-water portion 11a, and the underwater portion 11b is equipped with a motor 13 and a propeller 14. The motor 13 and the propeller 14 are connected and used to drive the propeller 14 to rotate to generate propulsion. The lifting bracket 20 is installed on the above-water portion 11a to facilitate the installation of the lifting bracket 20 and the clamp 200.

[0072] In one embodiment, please continue to refer to Figure 1a to Figure 2, a control circuit board 15 and a battery 16 are also provided in the fuselage 10. The battery 16 and the motor 13 are both electrically connected to the control circuit board 15, and the control circuit board 15 is used to control the battery 16 to supply power to the motor 13, and to control the operation of the motor 13. Specifically, the control circuit board 15 includes a central controller 15a and a drive controller 15b, and the central controller 15a communicates and interacts with the drive controller 15b and the battery 16 via a conductive cable, so that the central controller 15a receives the status information of the battery 16 and the status information of the drive controller 15b and the status information of the motor 13, so that the comprehensive control can be performed according to the various operating states of the battery 16, the drive controller 15b and the motor 13, so as to adjust the operating states of the battery 16, the drive controller 15b and the motor 13 to the best. Specifically, the central controller 15a can control the battery 16 to supply power to the motor 13. The drive controller 15b is used to control the operation of the motor 13, so that the motor 13 cooperates with the propeller 14 to generate propulsion. In addition to powering the motor 13, the battery 16 can also power the electronic devices in the fuselage 10, such as the central controller 15a and the drive controller 15b, to ensure their normal operation. The central controller 15a can receive signals sent by the user and perform related actions, such as increasing the speed of the motor 13 by driving the controller 15b. The battery 16 can be partially placed in the underwater part 11b and partially placed in the above-water part 11a, or completely placed in the underwater part 11b or the above-water part 11a. The control circuit board 15 is preferably placed in the above-water part 11a. It can be understood that the battery 16 is arranged inside the fuselage 10 so that the wiring related to the battery 16 is hidden in the fuselage 10, which can reduce external lines and improve the safety of use. Since the battery 16 needs to be charged, the propeller 100 needs to be removed from the clamp 200 and taken indoors or elsewhere for charging. At this time, the advantage of the detachable connection between the tilting bracket 20 and the clamp 200 is more prominent. Since the tilting bracket 20 and the clamp 200 are detachably connected, the propeller 100 can be quickly detached from the clamp 200 and then charged. At the same time, since the tilting bracket 20 can move relative to the fuselage 10 to be folded with the fuselage 10 for storage, the overall space occupied by the propeller 100 is reduced. When charging, the propeller 100 will not occupy too much space, avoiding causing trouble to users.

[0073] In one embodiment, please continue to refer to Figure 1a to Figure 2The fuselage 10 includes a fuselage body 11 and a steering bracket 12. The part of the fuselage body 11 exposed to the water surface is the above-water part 11a, and the part of the fuselage body 11 immersed in the water is the underwater part 11b. The steering bracket 12 is arranged on the horizontal side of the above-water part 11a. A steering shaft 81 is arranged between the fuselage body 11 and the steering bracket 12. The fuselage body 11 is rotatably connected with the steering bracket 12 through the steering shaft 81 to allow the fuselage body 11 to rotate relative to the steering bracket 12 around the axis of the steering shaft 81. For the convenience of description, the axis of the steering shaft 81 is defined as the first axis 91. It can be understood that the steering shaft 81 can be fixed to one of the fuselage body 11 or the steering bracket 12, and is rotatably matched with the other of the fuselage body 11 or the steering bracket 12. The steering freedom provided by the steering shaft 81 can allow the direction of the propeller 14 to change on the horizontal plane to change the driving direction of the carrier, such as turning left or right.

[0074] Further, the propeller 100 also includes a lifting shaft 82, which is arranged between the steering bracket 12 and the lifting bracket 20 to allow the lifting bracket 20 to rotate around the axis of the lifting shaft 82 relative to the steering bracket 12 through the lifting shaft 82. For the convenience of description, the axis of the lifting shaft 82 is defined as the second axis 92, and the first axis 91 and the second axis 92 are perpendicular. It can be understood that there are two situations in which the first axis 91 and the second axis 92 are perpendicular, one is that the first axis 91 and the second axis 92 intersect and form a 90-degree angle, and the other is that the first axis 91 and the second axis 92 are not in the same plane, but there is a straight line parallel to the first axis 91 that intersects with the second axis 92 and forms a 90-degree angle. The lifting shaft 82 can be fixed to one of the steering bracket 12 and the lifting bracket 20, and rotate with the other of the steering bracket 12 and the lifting bracket 20. Preferably, when the propeller 100 is in normal operation, the second axis 92 extends approximately in the horizontal direction, and the first axis 91 is parallel to the tilting surface (i.e., approximately the vertical surface). By providing the steering bracket 12, the steering shaft 81 is provided between the steering bracket 12 and the fuselage body 11, and the tilting shaft 82 is provided between the steering bracket 12 and the tilting bracket 20, the structure is simple, and the fuselage body 11 has both the tilting degree of freedom and the steering degree of freedom.

[0075] For details, please refer to Figure 1a , Figure 3 and Figure 4a, the steering bracket 12 is provided with a steering shaft hole 201 and a tilting shaft hole 202, and the tilting shaft 82 is arranged on the tilting bracket 20 and rotates with the tilting shaft hole 202. The steering shaft 81 is arranged on the fuselage body 11 and rotates with the steering shaft hole 201. In this embodiment, the number of the steering shaft holes 201 is two, and the two steering shaft holes 201 are respectively provided on the opposite sides of the steering bracket 12 in the vertical direction. The number of the steering shafts 81 is also two, one end of the steering shaft 81 is fixed on the fuselage body 11, and the other end of the steering shaft 81 extends into the corresponding steering shaft hole 201 for rotational cooperation. The first axis 91 of the two steering shafts 81 coincides. The tilting shaft hole 202 extends in the horizontal direction and passes through the steering bracket 12. The number of the tilting shafts 82 is two, and the two tilting shafts 82 extend from both sides of the tilting shaft hole 202 respectively, and rotate with the tilting shaft hole 202. The steering bracket 12 is in the shape of a cross formed by two rods that cross and are perpendicular to each other, and is a four-way structure.

[0076] In other embodiments, the number of the steering shaft 81 and the tilting shaft 82 can both be one, or the number of the steering shaft 81 can be one and the number of the tilting shaft 82 can be two, or the number of the steering shaft 81 can be two and the number of the tilting shaft 82 can be one. The steering bracket 12 as a whole can also be in other forms. The present disclosure does not limit the number of the tilting shafts 82 and the steering shaft 81 and the form of the steering bracket 12.

[0077] In another embodiment, please refer to Figure 4b , compared with the previous embodiment, the difference lies in the arrangement of the tilting shaft 82 and the tilting shaft hole 202. In this embodiment, the tilting shaft 82 is fixed to the steering bracket 12 and is rotatably connected to the tilting bracket 20. Specifically, the tilting shaft 82 and the steering bracket 12 are an integrated structure, and the tilting bracket 20 is provided with two tilting shaft holes 202, and the two ends of the tilting shaft 82 extend into the two tilting shaft holes 202 for rotational cooperation. The center lines of the two tilting shaft holes 202 coincide, and both extend horizontally.

[0078] In the above two embodiments, please refer to Figure 4a and Figure 4b , the steering shaft holes 201 are all arranged on the steering bracket 12, and the steering shafts 81 are all arranged to be fixed on the fuselage body 11. In other embodiments, please refer to Figure 4c and Figure 4d, the steering shaft hole 201 can also be set on the fuselage body 11, and the steering shaft 81 is fixed on the steering bracket 12. Specifically, the number of the steering shaft holes 201 is two, both of which are opened on the fuselage body 11 and located on the opposite sides of the steering bracket 12. The number of the steering shafts 81 is two, one end of the steering shaft 81 is fixed on the steering bracket 12, and the other end extends into the corresponding steering shaft hole 201 for rotational engagement, or the number of the steering shaft 81 is one, one end of the steering shaft 81 is rotationally engaged with one of the steering shaft holes 201, and the other end is rotationally engaged with the other steering shaft hole 201. Figure 4c and Figure 4d The differences between the embodiments shown and Figure 4a and Figure 4b The differences of the embodiments shown are the same, which are the arrangement of the lifting shaft 82 and the lifting shaft hole 202, and will not be repeated here.

[0079] The following is a detailed description of the storage solution of the lifting bracket 20 of the propeller 100 provided in the present disclosure.

[0080] In one embodiment of the present disclosure, please refer to Figure 1b , Figure 4a and Figure 5 A tilting shaft 82 is provided between the fuselage 10 and the tilting bracket 20. The fuselage 10 is rotatably connected to the tilting bracket 20 through the tilting shaft 82. After the tilting bracket 20 is separated from the clamp, the tilting bracket 20 can be rotated relative to the fuselage 10 through the tilting shaft 82 until it is folded with the fuselage 10. It can be understood that when in use, the fuselage 10 can be tilted relative to the tilting bracket 20 using the tilting shaft 82. When not in use, after the tilting bracket 20 is removed from the clamp, the tilting bracket 20 can also be rotated relative to the fuselage 10 using the tilting shaft 82 to complete storage. In this embodiment, the tilting of the fuselage 10 and the storage of the tilting bracket 20 are both achieved through the tilting shaft 82, which can greatly simplify the structure of the tilting bracket 20 and the fuselage 10, reduce costs, and also have good structural strength.

[0081] In one embodiment of this implementation, please refer to Figure 4a and Figure 5 The tilting shaft 82 is fixedly arranged on the tilting bracket 20, and the fuselage 10 is provided with a tilting shaft hole 202, and the tilting shaft 82 is rotatably matched with the tilting shaft hole 202. Specifically, the tilting shaft hole 202 is provided on the steering bracket 12 and passes through the steering bracket 12, and there are two tilting shafts 82, which extend from both sides of the tilting shaft hole 202, respectively, and are rotatably matched with the tilting shaft hole 202, so that the tilting bracket 20 can rotate around the second axis 92 relative to the steering bracket 12 through the two tilting shafts 82 and the tilting shaft hole 202, and the second axis 92 is perpendicular to the first axis 91.

[0082] In another embodiment of this embodiment, please refer to Figure 4b , compared with the previous embodiment, the difference lies in the arrangement of the tilting shaft 82 and the tilting shaft hole 202. The tilting shaft 82 in this embodiment is fixedly arranged on the fuselage 10, and the tilting bracket 20 is provided with a tilting shaft hole 202, and the tilting shaft 82 is rotatably matched with the tilting shaft hole 202. Specifically, the tilting shaft 82 is fixed on the steering bracket 12, and the tilting bracket 20 is provided with two tilting shaft holes 202, and the two ends of the tilting shaft 82 are respectively extended into the two tilting shaft holes 202 for rotational cooperation, so that the tilting bracket 20 can rotate around the second axis 92 relative to the steering bracket 12 through the tilting shaft 82 and the tilting shaft hole 202, and the second axis 92 is perpendicular to the first axis 91.

[0083] In one embodiment of this implementation, please refer to Figure 6 , a first bearing 31 is arranged in the lifting shaft hole 202, the outer ring of the first bearing 31 is fixed to the inner wall of the lifting shaft hole 202, and the inner ring of the first bearing 31 is fixed to the lifting shaft 82. Specifically, the first bearing 31 can be a bearing of the type of deep groove ball bearing, needle bearing, thrust roller bearing, etc. The outer peripheral surface of the outer ring of the first bearing 31 is attached to and relatively fixed to the inner wall of the lifting shaft hole 202, and the inner peripheral surface of the inner ring of the first bearing 31 is attached to and relatively fixed to the outer wall of the lifting shaft 82. Since a roller is arranged between the outer ring and the inner ring, the outer ring and the inner ring of the first bearing 31 can rotate relative to each other in the circumferential direction, and are relatively fixed in the axial direction. Such an arrangement can greatly reduce friction, so as to reduce the difficulty of lifting. At the same time, the first bearing 31 can be used to complete the axial fixation between the components of the lifting shaft 82 and the components of the lifting shaft hole 202, such as the lifting bracket 20 and the steering bracket 12 in this embodiment. In addition, the first bearing 31 is preferably set to adapt to the number of the tilting shafts 82. For example, in the present embodiment, the number of the first bearings 31 is two, corresponding to the two tilting shafts 82. However, in other embodiments, when the length of the tilting shaft 82 and the tilting shaft hole 202 is longer, multiple first bearings 31 may be set to correspond to one tilting shaft 82. The embodiment disclosed in the present invention does not limit the number of the first bearings 31.

[0084] In one embodiment of the present disclosure, please refer to Figures 7a to 9A tilting shaft 82 is provided between the body 10 and the tilting bracket 20, and the body 10 is rotatably connected to the tilting bracket 20 through the tilting shaft 82, so as to allow the body 10 to rotate relative to the tilting bracket 20 around the second axis 92. A storage shaft 83 is provided between the tilting shaft 82 and the tilting bracket 20, and the tilting bracket 20 is rotatably connected to the tilting shaft 82 through the storage shaft 83. After the tilting bracket 20 is separated from the clamp 200, the tilting bracket 20 can be rotated relative to the tilting shaft 82 around the axis of the storage shaft 83 through the storage shaft 83 until it is folded with the body 10. For the convenience of description, the axis of the storage shaft 83 is defined as the third axis 93, and the third axis 93 is perpendicular to the second axis 92. Taking into account the manufacturing tolerance and assembly tolerance, in fact, the angle formed by the second axis 92 and the third axis 93 is generally not exactly 90 degrees. Therefore, as long as the angle formed by the second axis 92 and the third axis 93 is close to 90 degrees, the second axis 92 and the third axis 93 can be considered to be perpendicular. Similarly, the determination of the perpendicularity of the first axis 91 and the second axis 92 can also be referred to in this way. Preferably, when in use (i.e., when the tilting bracket 20 is installed on the fixture), the first axis 91 and the third axis 93 are parallel and both are perpendicular to the second axis 92. It can be understood that when in use, the fuselage 10 can be tilted relative to the tilting bracket 20 using the tilting shaft 82. When not in use, after the tilting bracket 20 is removed from the fixture 200, the tilting bracket 20 can be rotated relative to the fuselage 10 using the storage shaft 83 to complete the storage. In this embodiment, the tilting bracket 20 can be stored by rotating around the third axis 93 using the storage shaft 83, or by rotating around the second axis 92 using the tilting shaft 82, or by rotating around the third axis 93 and the second axis 92 using the storage shaft 83 and the tilting shaft 82 at the same time. Therefore, the tilting bracket 20 has multiple storage methods, and storage is more convenient. In addition, in this embodiment, the tilting bracket 20 can also be applied to some scenarios where the tilting shaft 82 cannot be used for storage. For example, due to the structure of the fuselage body 11, the tilting bracket 20 cannot be rotated relative to the fuselage body 11 around the second axis 92 to fold with the fuselage body 11, or only part of the tilting bracket 20 can be stored. At this time, the existence of the storage shaft 83 provides another storage method for the tilting bracket 20, that is, the method of rotating relative to the fuselage body 11 around the third axis 93 to better fold with the fuselage body 11, and the applicability is strong. Therefore, in this embodiment, the requirements for the structure of the main body 11 are relatively low, and the embodiment can be applied to main bodies 11 of various shapes.

[0085] In one embodiment of this implementation, please continue to refer to Figures 7a to 9, the storage shaft 83 is fixedly arranged on the tilting bracket 20, and the tilting shaft 82 is provided with a storage shaft hole 203, and the storage shaft 83 is rotatably matched with the storage shaft hole 203. Specifically, the steering bracket 12 is provided with a tilting shaft hole 202, and one end of the tilting shaft 82 is inserted into the tilting shaft hole 202 for rotational matching, and the other end of the tilting shaft 82 is provided with a storage shaft hole 203 for the storage shaft 83 to be inserted into for rotational matching. With such a configuration, after the tilting bracket 20 is separated from the clamp 200, the degrees of freedom provided by the storage shaft 83 and the degrees of freedom provided by the tilting shaft 82 will not be constrained, and the diversity of the storage methods of the tilting bracket 20 is retained.

[0086] For further information, see Fig.10 Both ends of the storage shaft 83 are fixed to the tilting bracket 20, and the portion between the two ends of the storage shaft 83 is accommodated in the storage shaft hole 203. Specifically, the tilting bracket 20 extends in a direction perpendicular to the third axis 93 to constrain the storage shaft 83 in the storage shaft hole 203, so that the tilting bracket 20 and the tilting shaft 82 remain relatively connected.

[0087] In another embodiment of this embodiment, please refer to Fig.11 and Fig.12 , compared with the previous embodiment, the difference lies in the arrangement of the storage shaft 83 and the storage shaft hole 203. In this embodiment, the storage shaft 83 is fixedly arranged on the tilting shaft 82, and the tilting bracket 20 is provided with a storage shaft hole 203, and the storage shaft 83 is rotatably matched with the storage shaft hole 203. Specifically, both ends of the storage shaft 83 are provided with radially extending bosses 831, and the part between the two ends of the storage shaft 83 is accommodated in the storage shaft hole 203 to be rotatably connected with the tilting bracket 20. The bosses 831 at both ends of the storage shaft 83 can restrain the axial movement of the tilting bracket 20 relative to the tilting shaft 82, so that the tilting bracket 20 and the tilting shaft 82 maintain relative positions. The two bosses 831 can be nuts, nuts, and of course, they can also be limiting structures such as flanges or limit pins.

[0088] In another embodiment of this implementation mode, please refer to Fig.13 and Fig.14, compared with the previous embodiment, the difference lies in the arrangement of the receiving shaft 83 and the receiving shaft hole 203. In this embodiment, a second bearing 32 is arranged in the receiving shaft hole 203. The outer ring of the second bearing 32 is fixed to the inner wall of the receiving shaft hole 203, and the inner ring of the second bearing 32 is fixed to the receiving shaft 83. Specifically, the outer peripheral surface of the outer ring of the second bearing 32 is attached to and relatively fixed to the inner wall of the receiving shaft hole 203, and the inner peripheral surface of the inner ring of the second bearing 32 is attached to and relatively fixed to the outer wall of the receiving shaft 83. Since a roller is arranged between the outer ring and the inner ring, the outer ring and the inner ring of the second bearing 32 can rotate relative to each other in the circumferential direction, and are relatively fixed in the axial direction. It can be understood that such an arrangement can reduce friction to a large extent on the one hand. At the same time, the relative fixation of the tilting bracket 20 and the receiving shaft 83 on the third axis 93 can be achieved by using the second bearing 32. In this embodiment, after the lifting bracket 20 is installed on the clamp, the second bearing 32 needs to bear the gravity of the fuselage 10, which requires a high axial load bearing capacity of the second bearing 32. Therefore, the second bearing 32 is preferably a thrust ball bearing or a thrust roller bearing with better axial load bearing capacity.

[0089] In another embodiment of this implementation mode, please refer to Fig.15 and Fig.16 , compared with the previous embodiment, the difference lies in the arrangement of the storage shaft 83 and the storage shaft hole 203. In this embodiment, the storage shaft 83 is rotatably connected to the tilting bracket 20 to allow the tilting bracket 20 to rotate around the third axis 93 relative to the storage shaft 83 to be folded with the fuselage 10. The storage shaft 83 is rotatably connected to the tilting shaft 82 to allow the fuselage 10 to rotate around the second axis 92 relative to the storage shaft 83 and tilt. It can be understood that the tilting shaft 82 in the previous embodiment is fixed to the storage shaft 83 and is rotatably connected to the steering bracket 12 of the fuselage 10. The tilting shaft 82 in this embodiment is rotatably connected to the storage shaft 83, and the tilting shaft 82 is fixedly connected to the steering bracket 12 to obtain the freedom of the fuselage 10 to rotate around the second axis 92 relative to the storage shaft 83. In other embodiments, the tilting shaft 82 may also be rotatably connected to the storage shaft 83 at one end and rotatably connected to the steering bracket 12 at the other end, so as to achieve the tilting of the fuselage 10.

[0090] For further information, please refer to Fig.15 and Fig.16The tilting bracket 20 is provided with a receiving shaft hole 203, the receiving shaft 83 is rotatably matched with the receiving shaft hole 203, the receiving shaft 83 is provided with a tilting shaft hole 202, and the tilting shaft 82 is rotatably matched with the tilting shaft hole 202. Specifically, there are two receiving shaft holes 203, the two receiving shaft holes 203 are arranged opposite to each other, and the two ends of the receiving shaft 83 are respectively accommodated in the two receiving shaft holes 203 for rotatable matching, so that the tilting bracket 20 can be rotated around the third axis 93 relative to the receiving shaft 83 and stored. One end of the tilting shaft 82 is fixed on the steering bracket 12, and the other end extends into the tilting shaft hole 202 for rotatable matching.

[0091] For further information, see Fig.17 , a third bearing 33 is provided in the tilting shaft hole 202, the outer ring of the third bearing 33 is fixed to the inner wall of the tilting shaft hole 202, and the inner ring of the third bearing 33 is fixed to the tilting shaft 82. Specifically, the outer peripheral surface of the outer ring of the third bearing 33 is in contact with and relatively fixed to the inner wall of the tilting shaft hole 202, and the inner peripheral surface of the inner ring of the third bearing 33 is in contact with and relatively fixed to the outer wall of the tilting shaft 82. Since a roller is provided between the outer ring and the inner ring, the outer ring and the inner ring of the third bearing 33 can rotate relative to each other in the circumferential direction, but are relatively fixed in the axial direction. By providing the third bearing 33, the friction between the storage shaft 83 and the tilting shaft 82 can be reduced, so as to facilitate the tilting of the fuselage 10. At the same time, the third bearing 33 can make the storage shaft 83 and the tilting shaft 82 relatively fixed in the direction of the second axis 92.

[0092] Optional, see Fig.18 , a fourth bearing 34 is arranged in the receiving shaft hole 203, the outer ring of the fourth bearing 34 is fitted and fixed with the inner wall of the receiving shaft hole 203, and the inner ring of the fourth bearing 34 is fitted and fixed with the outer peripheral surface of the receiving shaft 83. Specifically, the number of the fourth bearings 34 is two, and the two fourth bearings 34 are respectively arranged in the two receiving shaft holes 203. In other embodiments, the number of the fourth bearing 34 can also be one, which is arranged in any one of the receiving shaft holes 203. By setting the fourth bearing 34, on the one hand, the friction force can be greatly reduced. On the other hand, the fourth bearing 34 can be used to achieve the relative fixation of the tilting bracket 20 and the receiving shaft 83 on the third axis 93. In this embodiment, since the fourth bearing 34 needs to bear the gravity of the fuselage 10 after the tilting bracket 20 is installed in the fixture, the axial load bearing capacity of the fourth bearing 34 is required to be high, so the fourth bearing 34 is preferably a thrust ball bearing or a thrust roller bearing with better axial load bearing capacity.

[0093] In another embodiment of the present disclosure, please refer to Fig.19The propeller 100 further includes an adapter 40, which is disposed between the tilting shaft 82 and the storage shaft 83. The adapter 40 is rotatably connected to the fuselage 10 through the tilting shaft 82, and the adapter 40 is rotatably connected to the tilting bracket 20 through the storage shaft 83. It is understandable that different carriers have different shapes. After the tilting bracket 20 is installed on the carrier through the clamp, the distance between the fuselage 10 and the carrier is too small, the tilting angle of the fuselage 10 is limited, and the fuselage 10 cannot be tilted to a suitable angle. In this regard, the adapter 40 can increase the distance between the fuselage 10 and the carrier, thereby ensuring that the fuselage 10 can be fully tilted. In addition, due to the difference in the shapes of different carriers, there will also be a situation where the height of the fuselage 10 is too high or too low after the tilting bracket 20 is installed on the carrier through the clamp. If the fuselage 10 is too high, the propeller cannot fully contact the water, thereby failing to generate stable propulsion. If the fuselage 10 is too low, in relatively shallow waters, the fuselage 10 is likely to collide with reefs, or the propeller may get entangled with foreign objects such as aquatic plants, causing accidents. Therefore, by providing the adapter 40, the adapter 40 can change the relative position of the lifting shaft 82 and the storage shaft 83, thereby changing the relative distance between the fuselage 10 and the carrier, and the propeller 100 can better adapt to different carriers.

[0094] In one embodiment of this implementation, please continue to refer to Fig.19 , the adapter 40 is fixed to the tilting shaft 82. The storage shaft 83 is fixedly arranged on the adapter 40, and the tilting bracket 20 is provided with a storage shaft hole 203, and the storage shaft 83 is rotatably matched with the storage shaft hole 203. Specifically, the adapter 40 in this embodiment is rod-shaped and extends in a direction that is perpendicular to both the second axis 92 and the third axis 93. One end of the adapter 40 is fixedly connected to the tilting shaft 82, and the other end of the adapter 40 is fixedly connected to the top of the storage shaft 83. The bottom end of the adapter 40 passes through the storage shaft hole 203, and is sleeved with a threaded nut 61 to constrain the relative position of the tilting bracket 20 and the adapter 40 to prevent the tilting bracket 20 from separating from the adapter 40. The steering bracket 12 of the fuselage 10 is provided with a tilting shaft hole 202, and the end of the tilting shaft 82 away from the adapter 40 extends into the tilting shaft hole 202 for rotational cooperation. It can be understood that, in this embodiment, the distance between the lifting bracket 20 and the carrier is increased by disposing the adapter 40 , so as to ensure that the fuselage 10 is fully lifted.

[0095] In one embodiment, see Fig. 20Compared with the previous embodiment, the difference lies in the way of constraining the tilting bracket 20 and the adapter 40. In this embodiment, a fifth bearing 35 is provided in the storage shaft hole 203, the outer ring of the fifth bearing 35 is fitted and fixed to the inner wall of the storage shaft hole 203, and the inner ring of the fifth bearing 35 is fitted and fixed to the outer circumferential surface of the storage shaft 83, and the rollers between the outer ring and the inner ring are used to relatively fix the storage shaft 83 and the tilting bracket 20 in the direction of the third axis 93.

[0096] In one embodiment, see Fig.21 Compared with the previous embodiment, the difference lies in the arrangement of the storage shaft 83 and the storage shaft hole 203. In this embodiment, the adapter 40 is provided with a storage shaft hole 203, and the storage shaft 83 is fixedly arranged on the tilting bracket 20 and rotatably cooperates with the storage shaft hole 203. Specifically, one end of the storage shaft 83 is fixed on the tilting bracket 20, and the other end passes through the storage shaft hole 203 and is threadedly engaged with the nut 61 to constrain the relative position of the tilting bracket 20 and the adapter 40 to prevent the tilting bracket 20 and the adapter 40 from separating.

[0097] In one embodiment, see Fig. 22 Compared with the previous embodiment, the difference lies in the way of constraining the tilting bracket 20 and the adapter 40. In this embodiment, a sixth bearing 36 is provided in the storage shaft hole 203, and the outer ring of the sixth bearing 36 is fitted and fixed to the inner wall of the storage shaft hole 203, and the inner ring of the sixth bearing 36 is fitted and fixed to the outer circumferential surface of the storage shaft 83. The rollers between the outer ring and the inner ring are used to relatively fix the storage shaft 83 and the tilting bracket 20 in the direction of the third axis 93.

[0098] In one embodiment, see Fig.23 ,and Fig.19 Compared with the embodiment shown in the figure, the difference lies in the arrangement of the tilting shaft 82 and the tilting shaft hole 202. In this embodiment, the adapter 40 is rotatably connected to the tilting shaft 82. Specifically, the end of the adapter 40 away from the storage shaft 83 is provided with a tilting shaft hole 202, and the tilting shaft 82 is arranged on the fuselage 10 (the tilting shaft 82 can be fixed on the fuselage 10, or a slot can be provided on the fuselage 10, and the tilting shaft 82 extends into the slot for rotational cooperation, wherein the tilting shaft 82 is preferably fixed on the fuselage 10), and the tilting shaft 82 extends into the tilting shaft hole 202 for rotational cooperation.

[0099] In one embodiment, see Fig.24Compared with the previous embodiment, the difference lies in the arrangement of the storage shaft 83 and the storage shaft hole 203. In this embodiment, the adapter 40 is provided with a storage shaft hole 203, and the storage shaft 83 is fixedly arranged on the tilting bracket 20 and rotatably cooperates with the storage shaft hole 203. Specifically, one end of the storage shaft 83 is fixed on the tilting bracket 20, and the other end passes through the storage shaft hole 203 and is threadedly engaged with the nut 61 to constrain the relative position of the tilting bracket 20 and the adapter 40 to prevent the tilting bracket 20 and the adapter 40 from separating.

[0100] Understandably, Figures 19 to 24 In each of the embodiments shown, the third axis 93 of the storage shaft 83 is not in the same plane and is perpendicular to the second axis 92 of the tilting shaft 82. Fig.25 , the third axis 93 and the second axis 92 intersect and are perpendicular, the adapter 40 extends along the direction of the third axis 93, a storage shaft 83 is fixed at the bottom end of the adapter 40, the storage shaft 83 is rotatably matched with the storage shaft hole 203 on the tilting bracket 20, and a tilting shaft 82 is fixed at the top end of the adapter 40, the tilting shaft 82 is rotatably matched with the tilting shaft hole 202 on the fuselage 10, and the above arrangement increases the height of the fuselage 10 relative to the carrier, so as to prevent the fuselage 10 from wading too deep and being interfered with by debris. Of course, in order to reduce the height of the fuselage 10 relative to the carrier, so as to allow the fuselage 10 to fully wade and provide stable propulsion, the adapter 40 can also be configured to have a tilting shaft 82 fixed at the bottom and a storage shaft 83 fixed at the top.

[0101] Understandably, Figure 23 to Figure 25 In each of the illustrated embodiments, a nut 61 is sleeved on one end of the receiving shaft 83 away from the adapter 40 to constrain the relative positions of the lifting bracket 20 and the adapter 40 .

[0102] In one embodiment of the present disclosure, please refer to Fig.26 and Fig. 27A tilting shaft 82 is provided between the body 10 and the tilting bracket 20, and the body 10 is rotatably connected to the tilting bracket 20 through the tilting shaft 82, so that the body 10 can rotate relative to the tilting bracket 20 around the axis of the tilting shaft 82. The body 10 can slide relative to the tilting bracket 20, and after the tilting bracket 20 is separated from the clamp, the tilting bracket 20 can slide relative to the body 10 until it is folded with the body 10. Specifically, the sliding direction of the tilting bracket 20 relative to the body 10 is perpendicular to the second axis 92 of the tilting shaft 82. It can be understood that when in use, the body 10 can be tilted relative to the tilting bracket 20 using the tilting shaft 82. When not in use, after the tilting bracket 20 is removed from the clamp, the tilting bracket 20 can slide relative to the body 10 through the tilting shaft 82 to complete storage. The relative sliding of the tilting bracket 20 and the body 10 can be achieved by forming a sliding pair between the tilting shaft 82 and the tilting bracket 20, or by forming a sliding pair between the tilting shaft 82 and the body 10, or by separately setting a component between the tilting shaft 82 and the tilting bracket 20, forming a sliding pair between the component and the tilting bracket 20, and sliding the tilting bracket 20 relative to the component and the tilting shaft 82, or by separately setting a component between the tilting shaft 82 and the body 10, forming a sliding pair between the component and the body 10, and driving the tilting shaft 82 and the tilting bracket 20 to slide relative to the body 10. The tilting bracket 20 is stored by sliding, and the storage path of the tilting bracket 20 is short, the operation is simple, and the applicability is strong.

[0103] In one embodiment of this implementation, please continue to refer to Fig.26 and Fig. 27 , the tilting bracket 20 is provided with a slide groove 205, and the end of the tilting shaft 82 is slidably matched with the slide groove 205. Specifically, one end of the tilting shaft 82 is rotationally matched with the tilting shaft hole 202 of the steering bracket 12, and the other end of the tilting shaft 82 extends into the slide groove 205 for sliding cooperation. Preferably, when the tilting bracket 20 is installed on the clamp, the slide groove 205 extends in the horizontal direction and passes through the tilting bracket 20. By providing the slide groove 205 on the tilting bracket 20, the end of the tilting shaft 82 is slidably matched with the slide groove 205. After the tilting bracket 20 is separated from the clamp, the tilting bracket 20 can slide relative to the tilting shaft 82 to be stored on one side of the fuselage 10.

[0104] In order to prevent the relative sliding between the lifting shaft 82 and the lifting bracket 20 from affecting the lifting of the fuselage 10 when in use, a limiting structure 60 is provided between the lifting shaft 82 and the lifting bracket 20. The limiting structure 60 is used to limit the relative position of the lifting shaft 82 and the lifting bracket 20 after the lifting shaft 82 slides relative to the lifting bracket 20 in a direction away from the clamp. In this embodiment, a protrusion 65 is provided on the inner wall of the slide groove 205 at one end away from the fuselage body 11, and the protrusion 65 limits the lifting shaft 82 from the side of the slide groove 205. A first limiting hole 206 and a second limiting hole 207 are provided on the inner wall of the slide groove 205 at one end close to the fuselage body 11. When in use, the first limiting hole 206 is close to the fuselage body 11 relative to the second limiting hole 207. The limiting structure 60 includes a fixing screw 63 and a movable pin 64. The fixing screw 63 is installed and fixed on the tilting bracket 20 through the first limiting hole 206 and protrudes from the inner wall of the slide slot 205 to limit the tilting shaft 82 from being separated from the slide slot 205 from the right side. The movable pin 64 is arranged in the second limiting hole 207. A spring is also arranged between the movable pin 64 and the tilting bracket 20. One end of the spring is fixed to the outer wall of the tilting bracket 20, and the other end is fixed to the top of the movable pin 64 facing the surface of the outer wall of the tilting bracket 20. The spring provides the movable pin 64 with elastic force along the axis direction of the movable pin 64. When in use, the bottom end of the movable pin 64 protrudes from the inner wall of the slide slot 205 to limit the tilting shaft 82 between the movable pin 64 and the fixing screw 63 to prevent the tilting shaft 82 from sliding relative to the tilting bracket 20 and affecting the tilting of the fuselage 10. When not in use, the movable pin 64 can be pulled up so that the bottom end of the movable pin 64 no longer protrudes from the inner wall of the slide groove 205, and the tilting shaft 82 is no longer limited by the movable pin 64. The tilting bracket 20 can be stored by relative sliding with the tilting shaft 82. In addition, the setting of the spring can facilitate the resetting of the movable pin 64 to improve convenience. In this embodiment, a fixing screw 63 and a movable pin 64 are used to limit the tilting shaft 82 in the slide groove 205. In other embodiments, the positions of the protrusion 65 and the fixing screw 63 can also be swapped. The present disclosure does not limit the form of the limiting structure 60.

[0105] For further information, please refer to Fig.26 and Fig. 27, the slide 205 limits the tilting shaft 82 from rotating around the second axis 92 relative to the tilting bracket 20. Specifically, the end of the tilting shaft 82 includes two parallel mating surfaces 821, and the inner wall of the slide 205 includes two parallel guide sliding surfaces 2051. The two mating surfaces 821 are respectively in contact with the corresponding guide sliding surfaces 2051, and the mating surfaces 821 and the guide sliding surfaces 2051 are both perpendicular to the tilting surface of the fuselage 10. It can be understood that the tilting surface is a plane perpendicular to the second axis 92 of the tilting shaft 82, and the fuselage 10 rotates on the tilting surface to tilt. The two mating surfaces 821 are respectively located on the opposite sides of the end of the tilting shaft 82, and the two guide sliding surfaces 2051 are respectively the two opposite inner walls of the slide 205. Preferably, the slide 205 is a "T"-shaped groove, and the end of the tilting shaft 82 is "T"-shaped, so that the tilting shaft 82 can be clamped in the slide 205. By setting two matching surfaces 821 and two sliding guide surfaces 2051, the rotation of the tilting shaft 82 relative to the tilting bracket 20 can be better limited, that is, there is only sliding freedom but no rotation freedom between the tilting shaft 82 and the tilting bracket 20, avoiding affecting the storage of the tilting bracket 20.

[0106] In another embodiment of this embodiment, please refer to Fig.28 Compared with the previous embodiment, the difference lies in the way in which the tilting bracket 20 is slidably connected to the tilting shaft 82. In this embodiment, the tilting shaft 82 is provided with a slide groove 205, and the tilting bracket 20 is provided with a guide rail 21 that slidably cooperates with the slide groove 205. The slide groove 205 and the guide rail 21 both extend in a direction parallel to the tilting surface of the fuselage 10. Specifically, when in use, the extension direction of the slide groove 205 and the slide rail are both horizontal. Preferably, the cross-sectional shape of the slide rail is "T"-shaped, and the slide groove 205 is a "T"-shaped groove, so that the tilting bracket 20 can be clamped in the slide groove 205.

[0107] For further information, please refer to Figure 29 to Figure 32b In order to prevent the relative sliding between the lifting shaft 82 and the lifting bracket 20 from affecting the lifting of the fuselage when in use, a limiting hole is opened on the guide rail 21, and the lifting shaft 82 in use is constrained by a fixing screw or a movable pin.

[0108] For details, please refer to Fig.29 and Fig.30, the guide rail 21 is provided with two limiting holes (including a first limiting hole 206 and a second limiting hole 207), the limiting structure 60 includes two fixing screws (including a first fixing screw 63a and a second fixing screw 63b), the first fixing screw 63a extends into the first limiting hole 206 and protrudes from the surface of the guide rail 21, and the second fixing screw 63b extends into the second limiting hole 207 and protrudes from the surface of the guide rail 21, so as to constrain the tilting axis 82 between the first fixing screw 63a and the second fixing screw 63b. It can be understood that after the tilting bracket 20 is installed on the fixture, the fuselage needs to be tilted. If the tilting axis 82 slides relative to the tilting bracket 20, the tilting cannot be performed normally. Therefore, the first fixing screw 63a and the second fixing screw 63b are required to limit the tilting axis 82 from sliding relative to the tilting bracket to ensure that the tilting can be performed normally. In addition, after the tilting bracket 20 is removed from the clamp, when the tilting bracket 20 needs to be stored, the first fixing screw 63a can be removed from the first limiting hole 206 to restore the sliding freedom of the tilting shaft 82 relative to the tilting bracket 20, thereby facilitating storage.

[0109] Alternatively, see Figure 31 to Figure 32b The end of the lifting shaft 82 is provided with a first mounting hole 208a and a second mounting hole 208b. The limiting structure 60 includes a first movable pin 64a and a second movable pin 64b. The first movable pin 64a is fixedly mounted in the first mounting hole 208a, and the second movable pin 64b is fixedly mounted in the second mounting hole 208b. When not in use, the first movable pin 64a and the second movable pin 64b are elastically supported on the guide rail 21 (see Fig.32a ), the first movable pin 64a and the second movable pin 64b will not affect the sliding of the tilting shaft 82 relative to the tilting bracket. The guide rail 21 is provided with a first limiting hole 206 and a second limiting hole 207. When the tilting shaft 82 moves relative to the guide rail 21 to the end of the guide rail 21 away from the clamp through the slide groove 205, one end of the first movable pin 64a will extend into the first limiting hole 206, and one end of the second movable pin 64b will extend into the second limiting hole 207, so that the tilting shaft 82 and the tilting bracket 20 provided with the guide rail 21 are relatively fixed (see Figure 32b In other embodiments, the number of the movable pins 64 may be one or more than two, which can also form a constraint.

[0110] In another embodiment of this implementation mode, please refer to Fig.33a and Fig.33b , which is different from the previous embodiment (i.e. Fig. 27Compared with the embodiment provided in the embodiment, the difference lies in the different way of forming a revolute pair with the tilting shaft 82. In this embodiment, the tilting bracket 20 is provided with a slide groove 205, the tilting shaft 82 is fixed on the steering bracket 12, the end of the tilting shaft 82 is provided with a first matching structure, and the end of the slide groove 205 away from the clamp is provided with a second matching structure. When the end of the tilting shaft 82 slides to the end of the slide groove 205 away from the clamp, the first matching structure and the second matching structure cooperate to form a revolute pair. The fuselage 10 can be tilted relative to the tilting bracket 20 through the revolute pair.

[0111] For further information, please refer to Fig.33a and Fig.33b The first matching structure is a retractable pin 71 that can be retracted along the second axis 92 of the tilting shaft 82, and the second matching structure is a pin hole 72. When the end of the tilting shaft 82 slides to the end of the slide slot 205 away from the clamp, the retractable pin 71 extends into the pin hole 72 to rotate with the pin hole 72. Specifically, a first fixing hole 822 is opened at the end of the tilting shaft 82, and the retractable pin 71 is fixedly installed in the first fixing hole 822, and elastically abuts against the inner wall of the slide slot 205 when not in use (see Fig.33a When the lifting shaft 82 slides in the slide slot 205 to the end of the slide slot 205 away from the clamp, the telescopic pin 71 is aligned with the pin hole 72 and extends into the pin hole 72 under the elastic force, thereby rotating with the pin hole 72 (see Fig.33b ), forming a rotation pair between the tilting shaft 82 and the tilting bracket 20, and the fuselage 10 can be tilted by the rotation pair. At the same time, the cooperation between the telescopic pin 71 and the pin hole 72 can limit the tilting shaft 82 from sliding in the slide groove 205, so as to constrain the relative position of the tilting shaft 82 and the tilting bracket 20. In addition, when it is necessary to release the constraint of the tilting shaft 82 and the tilting bracket 20, a thrust can be provided to the telescopic pin 71 on the side of the limit hole facing away from the tilting shaft 82, so that the telescopic pin 71 leaves the pin hole 72, and the tilting shaft 82 and the tilting bracket 20 restore the freedom of relative sliding.

[0112] In another embodiment of this implementation mode, please refer to Fig.34a and Fig.34bCompared with the previous embodiment, the difference lies in the form of the first matching structure and the second matching structure. In this embodiment, the first matching structure is configured as a pin hole 72, and the second matching structure is configured as a telescopic pin 71 that can be telescoped along the second axis 92 of the tilting shaft 82. A second fixing hole 209 is provided on the tilting bracket 20, and the telescopic pin 71 is movably installed in the mounting hole 208. The telescopic pin 71 includes a pin head 711 and a pin rod 712, the pin rod 711 extends into the mounting hole 208 and is movably connected, the pin head 711 is connected to one end of the pin rod 712 and is located on the outer side of the tilting bracket 20 facing away from the tilting shaft 82, and the radial dimension of the pin head 711 is greater than the radial dimension of the pin rod 712. A spring is also provided between the pin head 711 and the tilting bracket 20, one end of the spring is fixed to the surface of the tilting bracket 20 opposite to the pin head 711, and the other end of the spring is fixed to the surface of the pin head 711 opposite to the tilting bracket 20, and under normal conditions, the pin rod 712 protrudes from the inner wall of the slide groove 205. When it is necessary to obtain the tilting freedom, the tilting shaft 82 can slide along the slide groove 205 relative to the tilting bracket 20 to the vicinity of the pin rod 712, and then apply a pulling force to the pin head 711, so that one end of the pin rod 712 no longer protrudes from the inner wall of the slide groove 205. The tilting shaft 82 can continue to slide and align the pin hole 72 with the pin rod 712, and then stop applying the pulling force to the pin head 711. When the spring restores its elastic deformation, the pin rod 712 protrudes from the inner wall of the slide groove 205 again under the drive of the spring, and extends into the pin hole 72 to rotate with the pin hole 72.

[0113] In yet another embodiment of this implementation mode, please refer to Fig.35 ,and Fig. 27 Compared with the embodiment provided, the difference lies in the different way of forming a rotation pair with the tilting shaft 82. In this embodiment, the tilting bracket 20 is provided with a slide groove 205, and the propeller 100 further includes a slider 22, the slider 22 is slidably matched with the slide groove 205, and the tilting shaft 82 is rotatably connected with the slider 22 to allow the tilting bracket 20 to rotate relative to the fuselage 10 around the second axis 92 of the tilting shaft 82. Specifically, the slider 22 is provided with a tilting shaft hole 202, one end of the tilting shaft 82 is fixed to the fuselage 10, and the other end is rotatably matched with the tilting shaft hole 202, and the tilting shaft 82 can rotate relative to the slider 22 around the second axis 92 of the tilting shaft 82.

[0114] The following is a detailed description of the detachable connection scheme of the lifting bracket 20 and the clamp 200 of the propeller 100 provided in the present disclosure.

[0115] The present disclosure provides a propulsion device 1000, see Figure 1a and Figure 1bThe propulsion device 1000 includes a clamp 200 and a propeller 100 provided in an embodiment of the present disclosure. The lifting bracket 20 of the propeller 100 is detachably connected to the clamp 200, and the clamp 200 is used to be fixed to a carrier. Specifically, the propulsion device 1000 includes a fuselage 10, a clamp 200 and a lifting bracket 20. The clamp 200 is used to be fixed to a carrier, and the lifting bracket 20 is detachably connected to the clamp 200. The fuselage 10 is rotatably connected to the lifting bracket 20 so as to be lifted relative to the clamp 200 through the lifting bracket 20. After the lifting bracket 20 is detached from the clamp 200, the lifting bracket 20 can move relative to the fuselage 10 until it is folded with the fuselage 10.

[0116] The tilting bracket 20 is arranged to be movable relative to the body 10 to be folded with the body 10 after being separated from the clamp 200, so as to complete the storage of the tilting bracket 20, thereby reducing the space occupied by the entire propeller 100. At the same time, the tilting bracket 20 and the clamp 200 are arranged to be detachably connected, so that the tilting bracket 20 and the clamp 200 are easy to disassemble and assemble before and after the propeller 100 is used, thereby improving convenience and being conducive to improving user experience.

[0117] For details, please refer to Fig.36 , the propeller of the embodiment of the figure is used for explanation, the tilting bracket 20 is provided with a first mounting portion 110, and the clamp 200 is provided with a second mounting portion 210. The first mounting portion 110 and the second mounting portion 210 are relatively fixed by the gravity of the tilting bracket 20 and the fuselage 10, and when the external force overcomes the gravity of the tilting bracket 20 and the fuselage 10, the first mounting portion 110 and the second mounting portion 210 can be separated, and the first mounting portion 110 can move relative to the fuselage 10 to fold with the fuselage 10. It can be understood that under the action of the gravity of the tilting bracket 20 and the fuselage 10, the first mounting portion 110 and the second mounting portion 210 are relatively fixed, that is, the tilting bracket 20 and the clamp 200 are relatively fixed. After the external force overcomes the gravity of the tilting bracket 20 and the fuselage 10, the first mounting portion 110 and the second mounting portion 210 can be separated, that is, the tilting bracket 20 and the clamp 200 are separated. By utilizing gravity to complete the installation of the lifting bracket 20 and the body 10, and overcoming gravity to complete the disassembly of the lifting bracket 20 and the clamp 200, the installation steps are simple and quick, with good convenience, which is conducive to improving user experience.

[0118] In one embodiment, see Figure 36 to Figure 38The tilting bracket 20 includes a first bracket 25 and a second bracket 26, which are respectively arranged on opposite sides of the fuselage 10 and are both rotatably connected to the fuselage 10. The fuselage 10 can be tilted relative to the first bracket 25 and the second bracket 26, and the first bracket 25 and the second bracket 26 are both provided with a first mounting portion 110. Specifically, the first bracket 25 and the second bracket 26 are respectively arranged on both sides of the steering bracket 12 and are both rotatably connected to the steering bracket 12. Preferably, the first bracket 25 and the second bracket 26 are roughly mirror-symmetrical about a certain surface, and the first bracket 25 and the second bracket 26 can be synchronously rotated relative to the steering bracket 12 to tilt the fuselage body 11, or to complete the storage of the first bracket 25 and the second bracket 26. By setting the first bracket 25 and the second bracket 26, the tilting bracket 20 has a higher structural strength, which can improve the stability of the connection between the tilting bracket 20 and the clamp 200.

[0119] For further information, see Figure 36 to Figure 38 , one of the first bracket 25 and the fuselage 10 is provided with a first tilting axis 82a, and the other is provided with a first tilting axis hole 202a. One of the second bracket 26 and the fuselage 10 is provided with a second tilting axis 82b, and the other is provided with a second tilting axis hole 202b. The axis of the first tilting axis 82a coincides with the axis of the second tilting axis 82b. The first tilting axis 82a and the first tilting axis hole 202a are rotationally matched, and the second tilting axis 82b and the second tilting axis hole 202b are rotationally matched to allow the fuselage 10 to tilt. In this embodiment, the first tilting axis 82a is fixed on the first bracket 25, the second tilting axis 82b is fixed on the second bracket 26, the first tilting axis hole 202a and the second tilting axis hole 202b are both opened on the steering bracket 12, and the first tilting axis hole 202a and the second tilting axis hole 202b are communicated. In other embodiments, the first tilting axis 82a may also be fixed on the steering bracket 12, and the first tilting axis hole 202a may be provided on the first bracket 25, and / or the second tilting axis 82b may be fixed on the steering bracket 12, and the second tilting axis hole 202b may be provided on the second bracket 26. By providing the first tilting axis 82a and the second tilting axis 82b, the fuselage 10 may be tilted relative to the tilting bracket 20 via the first tilting axis 82a and the second tilting axis 82b, and the first tilting axis 82a and the second tilting axis 82b may better support the fuselage 10 and support the tilting of the fuselage 10.

[0120] For further information, see Figure 36 to Figure 38, the lifting bracket 20 includes a limiting rod 27. One end of the limiting rod 27 is connected to the first bracket 25, and the other end of the limiting rod 27 is connected to the second bracket 26 to limit the first lifting shaft 82a from disengaging from the first lifting shaft hole 202a and limit the second lifting shaft 82b from disengaging from the second lifting shaft hole 202b. Specifically, the extending direction of the limiting rod 27 is parallel to the axes of the first lifting shaft 82a and the second lifting shaft 82b. The limiting rod 27 can be fixed to one of the first bracket 25 and the second bracket 26 by means of threaded connection and connected to the other by means of a jack, that is, the limiting rod 27 only needs to ensure that the first bracket 25 and the second bracket 26 can rotate relative to the fuselage 10 synchronously. Of course, one end of the limiting rod 27 can also be fixed to the first bracket 25 and the other end can be fixed to the second bracket 26. The present disclosure does not limit the connection manner between the limiting rod 27 and the first bracket 25 and the second bracket 26.

[0121] Further, please refer to Figure 36 to Figure 38 , a clamping groove 2101 is formed in the second mounting portion 210, and the clamping groove 2101 extends from the top end to the bottom end of the fixture 200. The first mounting portion 110 is provided with a clamping block 1101, and the clamping block 1101 extends into the clamping groove 2101 from the top side of the clamping groove 2101. Under the gravity of the lifting bracket 20 and the fuselage 10, the clamping block 1101 is fixed in the clamping groove 2101. In this embodiment, the cross section of the clamping block 1101 is square, and the clamping groove 2101 is a square groove capable of accommodating the entire clamping block 1101 or a "匚"-shaped groove for accommodating a part of the clamping block 1101. Preferably, the clamping groove 2101 extends in the vertical direction, and the clamping block 1101 can extend into the clamping groove 2101 in the vertical direction and be fixed in the clamping groove 2101 under the gravity of the lifting bracket 20 and the fuselage 10, so as to realize the relative fixation of the lifting bracket 20 and the fixture 200. It can be understood that the relative fixation of the lifting bracket 20 and the fixture 200 is realized by the cooperation of the clamping block 1101 and the clamping groove 2101 and the gravity of the lifting bracket 20 and the fuselage 10, and the structure and the installation method are relatively simple.

[0122] Further, please refer to Figure 36 to Figure 38, there are two card slots 2101, one of which is located inside the carrier and the other is located outside the carrier, and there are two card blocks 1101, which are respectively inserted into the two card slots 2101 from the top of the clamp 200. It can be understood that by setting the number of card slots 2101 to two, and the two card slots 2101 are respectively located inside and outside the carrier, the gravity of the fuselage 10 and the lifting bracket 20 can be better transmitted to the carrier through the clamp 200, the load distribution on the clamp 200 is relatively uniform, and the clamp 200 is not easily damaged. Of the two blocks 1101, the length of the block 1101 located inside the carrier is shorter than the length of the block 1101 located outside the carrier. It can be understood that the main stress point of the block 1101 located inside the carrier is the top end, so the block 1101 inside the carrier does not need to be designed to be too long for structural strength, while the main stress point of the block 1101 outside the carrier is the bottom end. In order to ensure sufficient structural strength, it needs to be designed to be relatively longer. Through this design, the space occupied by the lift bracket 20 can be reduced, which is conducive to storage.

[0123] For details, please refer to Figure 36 to Figure 38The clamp 200 includes a first mounting plate 231, a second mounting plate 232 and a crossbeam 233, one end of the crossbeam 233 is connected to the top of the first mounting plate 231, and the other end of the crossbeam is connected to the top of the second mounting plate 232. The first mounting plate 231 and / or the second mounting plate 232 are used to clamp with the carrier, wherein the first mounting plate 231 is located inside the carrier, and the second mounting plate 232 is located outside the carrier. In the use state, the side of the second mounting plate 232 facing away from the first mounting plate 231 will abut against the fuselage 10 to provide horizontal support for the fuselage 10. When the tilting bracket 20 includes the first bracket 25 and the second bracket 26, the number of the first mounting plates 231 and the number of the crossbeams 233 are both two, and the two first mounting plates 231 are respectively fixed to the second mounting plate 232 through the corresponding crossbeams 233, and correspond to the first bracket 25 and the second bracket 26 respectively. There are four card slots 2101, and the four card slots 2101 extend in the vertical direction, wherein two card slots 2101 are respectively arranged on two cross beams 233, and the other two card slots 2101 are arranged on the second mounting plate 232. There are four card blocks 1101, two card blocks 1101 are arranged on the first bracket 25, and the other two card blocks 1101 are arranged on the second bracket 26. The first bracket 25 and the second bracket 26 both include a connecting rod 120, and the two ends of the connecting rod 120 are respectively connected to the two card blocks 1101. The first tilting axis 82a is arranged at one end of the connecting rod 120 of the first bracket 25 away from the clamp 200, and facing away from the card block 1101. The second tilting axis 82b is arranged at one end of the connecting rod 120 of the second bracket 26 away from the clamp 200, and facing away from the card block 1101. Through the cooperation of multiple card blocks 1101 and multiple card slots 2101, the connection strength of the tilting bracket 20 and the clamp 200 can be greatly improved. In addition, the connecting rod 120 includes two bent parts, so that when it is installed on the clamp 200, there is a gap between the middle part of the connecting rod 120 and the cross beam 233 (see Figure 2 ), which can prevent the connecting rod 120 from colliding with the clamp 200 and generating noise. The clamp 200 also includes a chuck 220, and the number of the chucks 220 is two, and the two chucks 220 are respectively arranged on two first mounting plates 231. The chuck 220 is used to cooperate with the second mounting plate 232 to tighten and fix on the carrier after the clamp 200 is placed on the carrier. In other embodiments, the chuck 220 can also be arranged on the second mounting plate 232, and the present disclosure does not limit the form of the chuck 220.

[0124] In one embodiment, please refer to Fig.39, compared with the previous embodiment, the difference lies in the specific arrangement of the card block 1101 and the card slot 2101. In this embodiment, the first mounting portion 110 is provided with a card slot 2101, and the second mounting portion 210 is provided with a card block 1101. The card block 1101 extends from the top to the bottom of the clamp 200, and the first mounting portion 110 is inserted into the card block 1101 from the top side of the card block 1101 through the card slot 2101. Under the gravity of the tilting bracket 20 and the fuselage 10, the card block 1101 is fixed to the card slot 2101. Specifically, there are four card blocks 1101 in this embodiment, two of which are configured as part of the first mounting plate 231, and the other two card blocks 1101 are configured on the second mounting plate 232, that is, two card blocks 1101 are located inside the carrier, and two card blocks 1101 are located outside the carrier. There are four card slots 2101, two of which are arranged on the first bracket 25, and the other two card slots 2101 are arranged on the second bracket 26. Preferably, the card block 1101 extends in the vertical direction after the clamp 200 is installed on the carrier. It can be understood that the relative fixation of the tilting bracket 20 and the clamp 200 is achieved by using the card block 1101 and the card slot 2101 to achieve the relative fixation of the tilting bracket 20 and the fuselage 10, and the structure and installation method are relatively simple. In addition, the card block 1101 and the card slot 2101 cooperate simultaneously inside and outside the carrier, and the load distribution on the clamp 200 is relatively uniform, and the clamp 200 is not easily damaged.

[0125] Understandably, Fig.36 and Fig.39 The corresponding lifting bracket 20 in the embodiment includes a first bracket 25 and a second bracket 26, and the first bracket 25 and the second bracket 26 are both provided with a block 1101 or a slot 2101. In other embodiments, the block 1101 or the slot 2101 may be provided only on one of the first bracket 25 and the second bracket 26. The block 1101 or the slot 2101 may also be provided with Fig.36 and Fig.39 The corresponding embodiments have different other structures.

[0126] as well as, Fig.36 and Fig.39 In the corresponding embodiments, the tilting bracket 20 is stored by the tilting shaft 82. In other embodiments, the tilting bracket 20 and the body 10 can be stored by relative sliding, or the tilting bracket 20 can be stored by relative rotation with the body 10 through the storage shaft 83, which will not be described in detail here.

[0127] In one embodiment, see Fig.40 ,and Fig.36Compared with the corresponding embodiments, the difference lies in the specific settings of the card slot 2101 and the card block 1101. In this embodiment, the second mounting portion 210 is provided with a card slot 2101, and the card slot 2101 extends from the side of the clamp 200 facing the fuselage 10 to the side away from the fuselage 10. The first mounting portion 110 is provided with a card block 1101, and the card block 1101 extends into the card slot 2101 from the side of the card slot 2101 facing the fuselage 10. Under the gravity of the tilting bracket 20 and the fuselage 10, the card block 1101 forms a friction force with the inner wall of the card slot 2101 and is relatively fixed. Specifically, after the clamp 200 is fixed to the carrier, the card slot 2101 extends in the horizontal direction, and the card block 1101 can be inserted into the card slot 2101 in the horizontal direction. It is understandable that, in the use state, the tilting bracket 20 and the body 10 have a large gravity, and pressure will be generated between the block 1101 and the inner wall of the slot 2101, thereby forming a friction force, which is used to prevent the block 1101 from leaving the slot 2101, thereby achieving the relative fixation of the clamp 200 and the tilting bracket 20. And, in the non-use state, as long as the gravity of the tilting bracket 20 and the body 10 is overcome, the friction of the block 1101 will disappear, and then it can be separated from the clamp 200. By using gravity to complete the installation of the tilting bracket 20 and the body 10, and overcoming gravity to complete the disassembly of the tilting bracket 20 and the clamp 200, the installation steps are simple and quick, with good convenience, which is conducive to improving user experience.

[0128] For further information, please refer to Fig.40The end of the block 1101 away from the clamp 200 is rotatably connected to the body 10, so as to allow the block 1101 to rotate relative to the body 10 until it is folded with the body 10. Specifically, a tilting shaft 82 is provided between the body 10 and the block 1101, and the body 10 is tilted relative to the block 1101 around the axis of the tilting shaft 82 through the tilting shaft 82. A storage shaft 83 is provided between the tilting shaft 82 and the block 1101, and the block 1101 is rotated relative to the block 1101 around the third axis 93 of the storage shaft 83 through the storage shaft 83 until it is folded with the body 10, and the third axis 93 is perpendicular to the second axis 92 of the tilting shaft 82. Specifically, there are two blocks 1101, and the two blocks 1101 extend in the same direction, one of the blocks 1101 is fixed to one end of the storage shaft 83, and the other block 1101 is fixed to the other end of the storage shaft 83. The storage shaft 83 and the two blocks 1101 are an integrated structure, and the storage shaft 83 and the two blocks 1101 can move synchronously. The end of the lifting shaft 82 is plate-shaped and has a storage shaft hole 203. The part between the two ends of the storage shaft 83 rotates in the storage shaft hole 203, so that the lifting shaft 82 is confined between the two blocks 1101. The tilting bracket 20 includes a first bracket 25 and a second bracket 26, wherein the first bracket 25 and the second bracket 26 have the same structure, and the number of the storage shaft 83 and the tilting shaft 82 are both two. Each bracket includes two clamping blocks 1101, and both are rotatably connected to the corresponding storage shaft 83 for storage, and the body 10 can be tilted through the tilting shaft 82. When the first bracket 25 and the second bracket 26 are installed on the clamp 200, the first bracket 25 and the second bracket 26 are relatively fixed to the clamp 200, and the first bracket 25 and the second bracket 26 are relatively locked, and the first bracket 25 and the second bracket 26 cannot be rotated relative to the tilting shaft 82 through the degree of freedom provided by the corresponding storage shaft 83 for storage, but the degree of freedom provided by the tilting shaft 82 will not be constrained, and the body 11 can still be tilted.

[0129] Specifically, the card slot 2101 is disposed on the second mounting plate 232 of the clamp 200 and is a square hole that penetrates the second mounting plate 232. The number of the card slots 2101 corresponds to the number of the card blocks 1101, both of which are four, and the four card slots 2101 extend in the horizontal direction. It can be understood that Fig.40 In the corresponding embodiment, the tilting bracket 20 is stored by the storage shaft 83. In other embodiments, the tilting bracket 20 and the body 10 can be stored by relative sliding, or the tilting bracket 20 can be stored by relative rotation with the body 10 through the tilting shaft 82, which will not be described in detail here.

[0130] The present disclosure also provides a mobile device 2000 for use in water areas. Fig.41, the movable device 2000 in the water area includes a carrier 300 and a propulsion device 1000, and the clamp 200 of the propulsion device 1000 is fixed to the carrier 300. The movable device 2000 in the water area can be a water equipment such as a boat, a kayak, a bamboo raft, etc., which is not specifically limited. Specifically, the movable device 2000 in the water area also includes a tiller 400, which is installed on the fuselage 10 and is used to control the tilting of the fuselage 10 and control the orientation of the fuselage 10, thereby changing the course. By setting the tilting bracket 20 in the propeller 100 in the movable device 2000 in the water area to be able to move relative to the fuselage 10 to fold with the fuselage 10 after being separated from the clamp 200, the storage of the tilting bracket 20 is completed, so as to reduce the space occupied by the entire propeller 100. At the same time, the tilting bracket 20 and the clamp 200 are detachably connected, so that the disassembly and assembly between the tilting bracket 20 and the clamp 200 becomes easy before and after the propeller 100 is used, so as to improve the convenience and facilitate the user experience.

[0131] In the description of this specification, the description with reference to the terms "certain embodiments", "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

[0132] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present disclosure, the meaning of "plurality" is at least two, such as two, three, unless otherwise clearly and specifically defined.

[0133] Although the embodiments of the present disclosure have been shown and described above, it is to be understood that the above embodiments are illustrative and are not to be construed as limitations on the present disclosure. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present disclosure. The scope of the present disclosure is defined by the claims and their equivalents.

Claims

1. A propeller, characterized in that: include: body; A tilting bracket, the tilting bracket is used to be detachably connected to a clamp fixed on a carrier, the fuselage is rotatably connected to the tilting bracket, so that the tilting bracket is tilted relative to the clamp, and after the tilting bracket is separated from the clamp, the tilting bracket can move relative to the fuselage to be folded with the fuselage; A tilting shaft is provided between the fuselage and the tilting bracket, and the fuselage is rotatably connected to the tilting bracket through the tilting shaft to allow the fuselage to rotate relative to the tilting bracket around the axis of the tilting shaft; A storage shaft is provided between the tilting axis and the tilting bracket, and the tilting bracket is rotatably connected to the tilting axis through the storage shaft. After the tilting bracket is separated from the clamp, the tilting bracket can be rotated relative to the tilting axis around the axis of the storage shaft through the storage shaft until it is folded with the fuselage, and the axis of the storage shaft is perpendicular to the axis of the tilting axis.

2. The propeller according to claim 1, characterized in that The storage shaft is fixedly arranged on the tilting shaft, the tilting bracket is provided with a storage shaft hole, and the storage shaft is rotationally matched with the storage shaft hole.

3. The propeller according to claim 1, characterized in that The storage shaft is fixedly arranged on the tilting bracket, the tilting shaft is provided with a storage shaft hole, and the storage shaft is rotationally matched with the storage shaft hole.

4. The propeller according to claim 1, characterized in that: The storage shaft is rotatably connected to the tilting shaft to allow the body to rotate relative to the storage shaft around the axis of the tilting shaft. The storage shaft is rotatably connected to the tilting bracket to allow the tilting bracket to rotate relative to the storage shaft around the axis of the storage shaft until it is folded with the body.

5. The propeller according to claim 4, characterized in that The tilting bracket is provided with a storage shaft hole, the storage shaft is rotatably matched with the storage shaft hole, the storage shaft is provided with a tilting shaft hole, and the tilting shaft is rotatably matched with the tilting shaft hole.

6. The propeller according to claim 1, characterized in that The propeller also includes a conversion member, which is arranged between the tilting axis and the storage shaft, the conversion member is rotationally connected to the fuselage through the tilting axis, and the conversion member is rotationally connected to the tilting bracket through the storage shaft.

7. A propulsion device, characterized in that: It comprises a clamp and a propeller as described in any one of claims 1 to 6, wherein the lifting bracket of the propeller and the clamp are detachably connected, and the clamp is used to be fixed on a carrier.

8. The propulsion device according to claim 7, characterized in that: The fuselage is provided with a motor and a propeller, and the motor is connected to the propeller and is used to drive the propeller to rotate to generate propulsion; The clamp is used to be fixed on the carrier.

9. The propulsion device according to claim 8, characterized in that: The tilting bracket is provided with a first mounting part, and the clamp is provided with a second mounting part. The first mounting part and the second mounting part are relatively fixed by relying on the gravity of the tilting bracket and the fuselage. When an external force overcomes the gravity of the tilting bracket and the fuselage, the first mounting part and the second mounting part can be separated, and the first mounting part can move relative to the fuselage to be folded with the fuselage.

10. A movable device in water area, characterized in that: The invention comprises a carrier and a propulsion device as claimed in any one of claims 7 to 9, wherein a clamp of the propulsion device is fixed to the carrier.

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