Large-overload separable waterproof high-vibration-resistance machine arm module

Abstract

The utility model provides a large-overload separable waterproof high-vibration-resistance machine arm module, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a vehicle body end main shaft, a vehicle arm end main shaft, a vehicle body end connector, a vehicle arm end connector and a rotating shaft, the vehicle body end main shaft is detachably connected with the vehicle body end connector and connected with a vehicle body end sleeve, and the vehicle arm end main shaft is detachably connected with the vehicle arm end connector and connected with a vehicle arm end sleeve. The fuselage end main shaft and the arm end main shaft are detachably connected, the fuselage end connector and the arm end connector can be in butt joint in the connection state, and the rotating shaft is detachably connected with the fuselage end main shaft and the arm end main shaft and can lock the fuselage end main shaft and the arm end main shaft in the connection state. Due to the fact that the fuselage end main shaft and the arm end main shaft are detachably connected, the fuselage and the arms of the unmanned aerial vehicle can be disassembled and assembled more flexibly, the arms can be disassembled, moved and replaced, and the separable arm module design is achieved.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field especially is related to a big overload separable waterproof high anti vibration machine arm module. BACKGROUND

[0002] Unmanned aircraft is called unmanned plane, which is a kind of plane without people on board, and is controlled by radio remote control equipment and self-provided program control device, or is completely or intermittently operated by on-board computer.

[0003] The applicant finds that at least the following technical problems exist in the prior art: the fuselage and the arm of the existing unmanned plane are mostly designed in an integrated manner, and the two cannot be disassembled, so that the arm and other spare parts cannot be replaced in time when necessary, and the connector between the fuselage and the arm is also designed in an integrated manner and cannot be separated, so that it cannot be replaced when necessary. UTILITY MODEL CONTENT

[0004] The utility model discloses a big overload separable waterproof high anti vibration machine arm module to solve the technical problems existing in the prior art.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme:

[0006] A big overload separable waterproof high anti vibration machine arm module, comprising a fuselage end main shaft, an arm end main shaft, a fuselage end connector, an arm end connector and a rotating shaft, the fuselage end main shaft is detachably connected with the fuselage end connector and connected with a fuselage end sleeve, the arm end main shaft is detachably connected with the arm end connector and connected with an arm end sleeve, the fuselage end main shaft is detachably connected with the arm end main shaft and can be connected with the fuselage end connector and the arm end connector in the connected state, the rotating shaft is detachably connected with the fuselage end main shaft and the arm end main shaft and can lock the fuselage end main shaft and the arm end main shaft in the connected state.

[0007] Preferably, the outer wall of the connecting end of the fuselage end main shaft and the inner wall of the rotating shaft are provided with a plurality of segmented screw threads, and the corresponding segmented screw threads can be locked when the fuselage end main shaft is connected with the rotating shaft.

[0008] Preferably, the two ends of the segmented screw thread are provided with a lead angle structure.

[0009] Preferably, the outer wall of the connecting end of the fuselage end main shaft is provided with a first identification part and is sleeved with a first color identification ring, the outer wall of the connecting end of the arm end main shaft is provided with a second identification part, the outer wall of the rotating shaft is sleeved with a second color identification ring, the first identification part and the second identification part correspond to each other and match each other, and the first color identification ring and the second color identification ring on the corresponding connecting fuselage end main shaft and rotating shaft are of the same color.

[0010] Preferably, the connecting end of the fuselage end main shaft is provided with a first plug-in slot, and the connecting end of the arm end main shaft can be plugged into the first plug-in slot.

[0011] Preferably, the fuselage end main shaft is provided with a second plug-in slot located outside the first plug-in slot, and the end of the fuselage end sleeve can be plugged into the second plug-in slot.

[0012] The arm end main shaft is provided with a third plug-in slot, and the end of the arm end sleeve can be plugged into the third plug-in slot.

[0013] Preferably, the end of the first plug-in slot is circumferentially provided with a plurality of limiting buckles, the end of the connecting end of the arm end main shaft is circumferentially provided with a plurality of limiting buckle holes, the limiting buckles and the limiting buckle holes are the same in number and correspond in position, and the limiting buckles and the limiting buckle holes are clamped when the connecting end of the arm end main shaft is plugged into the first plug-in slot.

[0014] Preferably, the inner side wall of the first plug-in slot and the inner side wall of the connecting end of the arm end main shaft are both inclined to form a slope interference when connected.

[0015] Preferably, the rotating shaft comprises a shaft body and an elastic auxiliary part, the segmented screw thread is arranged on the inner wall of the shaft body, and the elastic auxiliary part is movably connected with the shaft body.

[0016] Preferably, a limiting ring is further connected to the arm end sleeve, and when the rotating shaft is unlocked and moves to contact the limiting ring, the fuselage end main shaft and the arm end main shaft can be disconnected.

[0017] The fuselage end connector and the arm end connector can be flexibly disassembled and replaced according to the actual use state and use requirements.

[0018] The detachable connection between the fuselage end main shaft and the arm end main shaft makes the fuselage and the arm more flexible in disassembly and assembly, and the arm can be disassembled, moved and replaced, realizing the detachable arm module design.

[0019] The additional technical features of the utility model can also produce the following beneficial effects: the multi-layer segmented screw thread is more convenient for the introduction of the initial thread, the lead angle structure at the end avoids the dead lock abnormal phenomenon of the ordinary screw thread, and under the radial tensile load, the multi-layer segmented screw thread has more excellent locking performance and can bear larger load.

[0020] The application of the first identification part and the second identification part can identify and prompt when the fuselage end main shaft and the arm end main shaft are connected, so that the fuselage end main shaft and the arm end main shaft can adjust the connection angle to make the positions of the first identification part and the second identification part correspond, thereby facilitating the assembly of the fuselage end main shaft and the arm end main shaft and the accurate connection of the fuselage end connector and the arm end connector.

[0021] The application of the first color identification ring and the second color identification ring can distinguish different arms by different color identification rings, and when the corresponding connected fuselage end main shaft and arm end main shaft are installed, the same color identification ring is used for identification and confirmation, so that the corresponding fuselage end main shaft and the corresponding rotating shaft and the arm end main shaft form corresponding connection, thereby ensuring the accurate installation and replacement of the arm and avoiding misinstallation. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or the prior art description, and obviously, the drawings in the following description are only some embodiments of the utility model, and for those skilled in the art, other drawings can also be obtained according to these drawings without creative labor.

[0023] Figure 1 It is the explosion structural drawing of the utility model;

[0024] Figure 2 It is the structure drawing of the locking state of the utility model;

[0025] Figure 3 It is the detail structure drawing of the fuselage end main shaft and the arm end main shaft of the utility model;

[0026] Figure 4 This is a detailed structural diagram of the rotating shaft of the present utility model;

[0027] Figure 5 This is a cross-sectional structural diagram of the utility model in a locked state;

[0028] Figure 6 This is a cross-sectional structural diagram of the main shaft at the fuselage end of the utility model;

[0029] Figure 7 This is a detailed structural diagram of the first color identification circle and the second color identification circle of the present invention;

[0030] In the figure, 1, main shaft at the fuselage end; 11, first identification portion; 12, first plug-in slot; 121, limit buckle; 13, second plug-in slot; 14, first color identification ring;

[0031] 2. Spindle at the arm end; 21. Second identification portion; 22. Third insertion slot; 23. Limiting hole;

[0032] 3. Body end connector;

[0033] 4. Arm end connector;

[0034] 5. Rotating shaft; 51. Shaft body; 52. Elastic auxiliary component; 53. Second color identification ring;

[0035] 6. Fuselage end casing;

[0036] 7. Arm end casing;

[0037] 8. Segmented screw thread;

[0038] 9. Limiting ring. DETAILED DESCRIPTION

[0039] To make the purpose, technical solution, and advantages of the present invention more clear, the technical solution of the present invention will be described in detail below. Obviously, the embodiments described are only some of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of the present invention.

[0040] In the description of the present invention, it should be understood that the terms "center", "lateral", "length", "width", "height", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "side" and the like indicate directions or positional relationships based on the attached Figure 1The orientation or positional relationship shown is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0041] It should also be noted that, in the description of this utility model, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; and direct or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of these terms in this utility model depending on the specific circumstances.

[0042] Reference Figures 1 to 7 The utility model provides a large overload detachable waterproof and high vibration resistant machine arm module, including a fuselage end main shaft 1, an arm end main shaft 2, a fuselage end connector 3, an arm end connector 4 and a rotating shaft 5.

[0043] The fuselage end main shaft 1 is tubular, and the fuselage end connector 3 is located inside the fuselage end main shaft 1 and is detachably connected to the fuselage end main shaft 1. In this embodiment, the two are preferably connected by bolts to make disassembly and assembly more convenient and quick;

[0044] The arm end spindle 2 is tubular, and the arm end connector 4 is located inside the arm end spindle 2 and is detachably connected to the arm end spindle 2. In this embodiment, the two are preferably connected by bolts to make disassembly and assembly more convenient and quick;

[0045] Since a detachable connection method is adopted between the body end main shaft 1 and the body end connector 3, as well as between the arm end main shaft 2 and the arm end connector 4, the body end connector 3 and the arm end connector 4 can be flexibly disassembled and replaced according to actual usage status and usage requirements.

[0046] The main shaft 1 at the fuselage end and the main shaft 2 at the arm end are detachably connected, and when the main shaft 1 at the fuselage end and the main shaft 2 at the arm end are in the connected state, the main shaft connector 3 and the arm end connector 4 can be connected to each other to achieve circuit connection and control connection between the fuselage and the arm;

[0047] The main shaft 1 on the fuselage side is connected to the main shaft sleeve 6, and the main shaft 2 on the arm side is connected to the arm sleeve 7. The main shaft sleeve 6 and the arm sleeve 7 are not part of this module, but are external structures of the client. The main shaft sleeve 6 is used to connect to the drone fuselage, and the arm sleeve 7 is used to connect to the drone arm.

[0048] The detachable connection between the fuselage end main shaft 1 and the arm end main shaft 2 makes the fuselage and the arm of the unmanned aerial vehicle more flexible to disassemble, and the arm can be disassembled, moved and replaced, realizing the detachable arm module design.

[0049] The rotating shaft 5 is detachably connected with the fuselage end main shaft 1 and the arm end main shaft 2, and the rotating shaft 5 can lock the fuselage end main shaft 1 and the arm end main shaft 2 to make the connection firm.

[0050] In the specific use process, after the fuselage end main shaft 1 and the arm end main shaft 2 are connected, the rotating shaft 5 is rotated clockwise to lock the fuselage end main shaft 1 and the arm end main shaft 2.

[0051] The rotating shaft 5 is rotated counterclockwise to unlock the fuselage end main shaft 1 and the arm end main shaft 2, and then the fuselage end main shaft 1 and the arm end main shaft 2 can be separated.

[0052] As an optional embodiment, the outer wall of the connecting end of the fuselage end main shaft 1 and the inner wall of the rotating shaft 5 are provided with a plurality of segmented screw threads 8, and the corresponding segmented screw threads 8 can be locked when the fuselage end main shaft 1 is connected with the rotating shaft 5.

[0053] In this embodiment, the plurality of segmented screw threads 8 are preferably uniformly arranged along the axial direction, and the structure state when the segmented screw threads 8 are two layers is preferably shown in the drawing, and all the segmented screw threads 8 adopt a segmented form, and the two ends of the segmented screw threads 8 are preferably provided with a lead angle structure.

[0054] In this way, compared with ordinary screw threads, the plurality of segmented screw threads 8 are more convenient for the introduction of initial threads, the end part adopts a lead angle structure to avoid the dead lock abnormal phenomenon of ordinary screw threads, and under radial tensile load, the plurality of segmented screw threads 8 have more excellent locking performance and can bear larger load. In addition, during use of the module, there may be a phenomenon that the assembly stroke between the fuselage end main shaft 1 and the arm end main shaft 2 is insufficient, that is, there is a large gap between the fuselage end main shaft 1 and the arm end main shaft 2 during initial assembly. By adopting the structure design of the plurality of segmented screw threads 8, the position can be forcibly guided and corrected, and the stroke correction range is not less than 25% of the total stroke.

[0055] As an optional embodiment, the outer wall of the connecting end of the fuselage end main shaft 1 is provided with a first identification part 11, and the outer wall of the connecting end of the arm end main shaft 2 is provided with a second identification part 21, and the positions of the first identification part 11 and the second identification part 21 correspond to each other and match with each other.

[0056] Through the application of the first identification part 11 and the second identification part 21, the identification prompting effect can be achieved when the fuselage end main shaft 1 and the arm end main shaft 2 are docked, so that the fuselage end main shaft 1 and the arm end main shaft 2 can adjust the docking angle to make the positions of the first identification part 11 and the second identification part 21 correspond, thereby facilitating the assembly between the fuselage end main shaft 1 and the arm end main shaft 2, and also facilitating the accurate docking between the fuselage end connector 3 and the arm end connector 4;

[0057] In addition, the outer wall of the connecting end of the fuselage end main shaft 1 is sleeved with a first color identification ring 14, the outer wall of the rotating shaft 5 is sleeved with a second color identification ring 53, and the colors of the first color identification ring 14 and the second color identification ring 53 on the corresponding connected fuselage end main shaft 1 and rotating shaft 5 are the same;

[0058] Through the application of the first color identification ring 14 and the second color identification ring 53, different arms or different connection parts can be distinguished by using identification rings of different colors. Since the rotating shaft 5 is connected with the arm end main shaft 2 as the same structure, it is equivalent to using identification rings of the same color to identify and confirm when installing the corresponding connected fuselage end main shaft 1 and arm end main shaft 2, thereby ensuring that the corresponding fuselage end main shaft 1 and the corresponding rotating shaft 5 and arm end main shaft 2 form corresponding connections, thereby ensuring accurate installation and replacement of the arm and avoiding mistakes.

[0059] As an optional implementation, the connecting end of the fuselage end main shaft 1 is provided with a first plug-in slot 12, and the connecting end of the arm end main shaft 2 can form a plug-in connection with the first plug-in slot 12. The plug-in structure can reduce the occupied space and shorten the overall size of the module.

[0060] The inner side wall of the first plug-in slot 12 and the inner side wall of the connecting end of the arm end main shaft 2 are both inclined, so that they can form a certain degree of slope interference when connected. By using the inner slope interference, a certain pull effect can be achieved, and the stress distribution is more uniform in a large load scenario, avoiding stress concentration on the module.

[0061] As an optional implementation, the fuselage end main shaft 1 is provided with a second plug-in slot 13 located outside the first plug-in slot 12, and the end of the fuselage end sleeve 6 can form a plug-in connection with the second plug-in slot 13. At least one side wall surface of the second plug-in slot 13 is provided as an uneven surface, which can increase the friction through the protruding wall surface structure to improve the connection strength and stability between the two.

[0062] The arm end main shaft 2 is provided with a third plug-in slot 22, and the end of the arm end sleeve 7 can form a plug-in connection with the third plug-in slot 22. At least one side wall surface of the third plug-in slot 22 is provided as an uneven surface, which can increase the friction through the protruding wall surface structure to improve the connection strength and stability between the two.

[0063] As an optional embodiment, a plurality of limit buckles 121 are circumferentially provided at the end of the first plug-in slot 12, and a plurality of limit buckles 23 are circumferentially provided at the end of the connecting end of the arm end main shaft 2. The limit buckles 121 and the limit buckles 23 are the same in number and correspond in position. When the connecting end of the arm end main shaft 2 is plugged into the first plug-in slot 12, each limit buckle 121 can be snapped into the corresponding limit buckle 23. Such a setting can further enhance the axial anti-torsion capability of the module. When the module is in use, if twisting occurs, the twisting can be reduced by relying on the limit buckles 121 and the limit buckles 23.

[0064] As an optional embodiment, the rotating shaft 5 includes a shaft body 51 and an elastic auxiliary member 52. The segmented screw thread 8 is provided on the inner wall of the shaft body 51. The elastic auxiliary member 52 is movably connected to the shaft body 51. The elastic auxiliary member 52 is provided with a spring mechanism and a limit mechanism.

[0065] When the rotating shaft 5 is in the locked state, the segmented screw thread 8 on the shaft body 51 forms a limit with the main shaft 1 at the fuselage end, and the limit mechanism of the elastic auxiliary part 52 can limit the main shaft 2 at the arm end. At the same time, the spring mechanism of the elastic auxiliary part 52 is in a force storage state.

[0066] When the rotating shaft 5 is in the unlocked state, the segmented screw thread 8 on the shaft body 51 can be separated from the main shaft 1 at the fuselage end by rotation, and the limiting mechanism of the elastic auxiliary part 52 no longer limits the main shaft 2 at the arm end. At the same time, the spring mechanism of the elastic auxiliary part 52 is in the released state.

[0067] In this embodiment, in order to better cooperate with the unlocking work of the rotating shaft 5, a limiting ring 9 is preferably included. The limiting ring 9 is connected to the arm end sleeve 7. When the rotating shaft 5 is unlocked and moves to contact the limiting ring 9, the main shaft 1 at the fuselage end and the main shaft 2 at the arm end can be disconnected;

[0068] When the rotating shaft 5 is used to lock the main shaft 1 at the fuselage end and the main shaft 2 at the arm end, the shaft body 51 can be rotated clockwise. After a certain angle is rotated, the shaft body 51 is locked with the main shaft 1 at the fuselage end, and the elastic auxiliary part 52 is locked with the main shaft 2 at the arm end, so that the main shaft 1 at the fuselage end and the main shaft 2 at the arm end are automatically locked. The assembled module has good structural strength and can effectively transfer impact force and leverage force to the sleeve 6 at the fuselage end and the sleeve 7 at the arm end.

[0069] When it is needed to unlock the rotating shaft 5, the elastic auxiliary part 52 can be pulled towards the direction of the limiting ring 9 first, the limiting of the elastic auxiliary part 52 to the arm end main shaft 2 is released, then the shaft body 51 is rotated in the counterclockwise rotation mode, a certain angle is rotated and then is in position, the unlocking is formed, then the rotating shaft 5 is continuously moved to contact with the limiting ring 9, which is equivalent to reach the limit position, at this time, the rotating shaft 5 no longer limits the fuselage end main shaft 1 and the arm end main shaft 2, linkage can be further formed, and the fuselage end main shaft 1 and the arm end main shaft 2 can be disconnected.

[0070] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited to this, any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A large overload detachable waterproof and high vibration resistance machine arm module, characterized in that: The invention comprises a body end main shaft (1), an arm end main shaft (2), a body end connector (3), an arm end connector (4) and a rotating shaft (5), wherein the body end main shaft (1) is detachably connected to the body end connector (3) and is connected to the body end sleeve (6), the arm end main shaft (2) is detachably connected to the arm end connector (4) and is connected to the arm end sleeve (7), the body end main shaft (1) is detachably connected to the arm end main shaft (2) and can make the body end connector (3) and the arm end connector (4) contact each other in a connected state, and the rotating shaft (5) is detachably connected to the body end main shaft (1) and the arm end main shaft (2) respectively and can lock the body end main shaft (1) and the arm end main shaft (2) in a connected state.

2. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 1 is characterized in that: The outer wall of the connection end of the main shaft (1) at the fuselage end and the inner wall of the rotating shaft (5) are both provided with multi-layer segmented screw threads (8), and the corresponding segmented screw threads (8) can form a locking when the main shaft (1) at the fuselage end is connected to the rotating shaft (5).

3. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 2 is characterized in that: Both ends of the segmented screw thread (8) are arranged as guide angle structures.

4. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 1 is characterized in that: The outer wall of the connection end of the main shaft (1) at the fuselage end is provided with a first identification portion (11) and is sleeved with a first color identification ring (14); the outer wall of the connection end of the main shaft (2) at the arm end is provided with a second identification portion (21); the outer wall of the rotating shaft (5) is sleeved with a second color identification ring (53); the positions of the first identification portion (11) and the second identification portion (21) correspond to and match each other; the colors of the first color identification ring (14) and the second color identification ring (53) on the correspondingly connected main shaft (1) and the rotating shaft (5) are the same.

5. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 1 is characterized in that: The connecting end of the main shaft (1) at the fuselage end is provided with a first plug-in slot (12), and the connecting end of the main shaft (2) at the arm end can be plugged into the first plug-in slot (12).

6. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 5, characterized in that: A second plug-in slot (13) is provided on the main shaft (1) at the fuselage end, the second plug-in slot (13) being located outside the first plug-in slot (12), and the end of the sleeve (6) at the fuselage end being capable of being plugged into the second plug-in slot (13); A third plug-in slot (22) is provided on the arm end main shaft (2), and the end of the arm end sleeve (7) can be plugged into the third plug-in slot (22).

7. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 5, characterized in that: The end of the first plug-in slot (12) is provided with a plurality of limiting buckles (121) along the circumferential direction, and the end of the connecting end of the arm end main shaft (2) is provided with a plurality of limiting clamping holes (23) along the circumferential direction. The limiting buckles (121) and the limiting clamping holes (23) are the same in number and have corresponding positions. When the connecting end of the arm end main shaft (2) is plugged into the first plug-in slot (12), the limiting buckles (121) and the limiting clamping holes (23) form a clamping connection.

8. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 5, characterized in that: The inner side wall of the first plug-in slot (12) and the inner side wall of the connecting end of the arm end main shaft (2) are both inclined so as to form a slope interference when the two are connected.

9. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 2, characterized in that: The rotating shaft (5) comprises a shaft body (51) and an elastic auxiliary component (52), the segmented screw thread (8) is arranged on the inner wall of the shaft body (51), and the elastic auxiliary component (52) is movably connected to the shaft body (51).

10. The large overload detachable waterproof and high vibration resistant machine arm module according to claim 1, characterized in that: It also includes a limiting ring (9), which is connected to the arm end sleeve (7). When the rotating shaft (5) is unlocked and moves to contact the limiting ring (9), the main shaft (1) at the fuselage end and the main shaft (2) at the arm end can be disconnected.

Images