Propeller base assembly, propeller quick release device and unmanned aerial vehicle

Abstract

The invention discloses a propeller base assembly, a propeller quick release device and an unmanned aerial vehicle. In the propeller base assembly, an extending groove is formed in the peripheral side of a propeller fixing seat, a lock catch piece is connected to the interior of the propeller fixing seat, and the lock catch piece is partially exposed through the extending groove and is configured to swing in the extending groove under the action of external force; and a limiting groove matched with the locking fastener is formed in the peripheral side of the mounting seat. When the propeller fixing seat is assembled on the mounting seat, the end part, extending out of the extending groove, of the locking fastener is clamped into the limiting groove to form circumferential limiting of relative rotation of the locking fastener and the limiting groove, so that the propeller fixing seat is effectively prevented from loosening or falling off in the flying process of the unmanned aerial vehicle, and the risk of propeller ejection is avoided. During disassembly, a user only needs to drive the locking fastener to be separated from the limiting groove through external force, and then the propeller fixing base can be taken down easily. Therefore, the propeller base assembly provided by the invention realizes tool-free quick disassembly and assembly of the rotor wing assembly, and has both operation convenience and connection reliability.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a propeller base assembly, a propeller quick-release device, and an UAV. Background Technology

[0002] Existing multi-rotor unmanned aerial vehicles (UAVs) typically use multiple rotors to provide lift, and adjust the speed difference between the individual motors to achieve pitch, roll, and yaw attitude control. To facilitate transport, storage, routine maintenance, blade replacement, or to meet air transport safety requirements, the rotors are usually designed with a detachable structure. However, traditional quick-release mechanisms suffer from problems in practical applications, such as insufficient installation reliability, loosening due to long-term vibration, and inconvenient disassembly operations. Especially under high-speed rotation conditions, there is a risk of "propeller ejection," affecting flight safety. Summary of the Invention

[0003] To overcome the shortcomings of the prior art, the present invention provides a propeller base assembly, which aims to enable quick assembly and disassembly of the rotor and improve the reliability of the connection between the rotor and the fuselage.

[0004] The first technical solution adopted by the present invention to solve its technical problem is: providing a propeller base assembly, which includes:

[0005] The propeller mounting base has protruding slots on its periphery;

[0006] The mounting base has a limiting groove on its periphery;

[0007] A locking element is connected to the propeller mounting base, with one end extending through the extension slot and configured to swing within the extension slot in response to an external force.

[0008] When the propeller mounting base is assembled with the mounting base, the end of the locking member extending out of the protrusion groove engages with the limiting groove and is configured to disengage from the limiting groove based on the swing.

[0009] As described above, in the propeller base assembly, the locking member is hinged within the propeller mounting base, and the non-hinged end of the locking member extends through the extension slot and is configured to oscillate about its hinge point within the extension slot in response to an external force.

[0010] When the propeller mounting base is assembled to the mounting base, the non-hinged end engages with the limiting groove, and the non-hinged end is configured to disengage from the limiting groove based on the swing.

[0011] The propeller base assembly described above also includes a resilient reset element;

[0012] The elastic reset member is disposed in the propeller mounting base and cooperates with the locking member to apply force to the locking member, so that the non-hinged end remains locked, so that the locking member automatically engages with the limiting groove when the propeller mounting base is assembled.

[0013] As described above, in the propeller base assembly, the protrusion slot includes a first protrusion slot and a second protrusion slot disposed opposite to each other;

[0014] The limiting groove includes a first limiting groove and a second limiting groove that are disposed opposite to each other;

[0015] The locking element includes a first locking element and a second locking element that are arranged opposite to each other and hinged at their ends. The first locking element and the second locking element are respectively configured to cooperate with the first protruding slot and the second protruding slot.

[0016] The elastic reset member cooperates with the first locking member and the second locking member respectively, so that when the propeller mounting base is assembled, the non-hinged ends of the first locking member and the second locking member are respectively engaged in the first limiting groove and the second limiting groove.

[0017] As described above, in the propeller base assembly, the propeller mounting bracket is provided with:

[0018] A first fixing block is provided with a first mounting groove;

[0019] The second fixing block has a second mounting groove on it;

[0020] A locking block is configured to cooperate with the first fixing block and the second fixing block; the hinged ends of the first locking member and the second locking member are inserted on a hinge shaft, and the locking block limits the two ends of the hinge shaft within the first mounting groove and the second mounting groove, respectively.

[0021] As described above, in the propeller base assembly, the hinge ends of the first locking member and the second locking member are provided with ear plates with shaft holes; after the ear plates of the first locking member and the second locking member are stacked, the hinge shaft passes through the shaft hole, so that the ear plates of the first locking member and the second locking member are hinged together to the hinge shaft.

[0022] As described above, in the propeller base assembly, the end of the lug plate has a rounded surface.

[0023] As described above, in the propeller base assembly, the first locking member and the second locking member are provided with a fixing groove in the middle, and one end of the elastic reset member abuts in the fixing groove.

[0024] In the propeller base assembly described above, the elastic reset element is a torsional elastic element;

[0025] The first and second working ends of the torsional elastic element abut against the fixing grooves of the first and second locking elements, respectively.

[0026] In the propeller base assembly described above, the torsional elastic element is a torsion spring, and the spring body of the torsion spring is sleeved on the hinge shaft.

[0027] In the propeller base assembly described above, the elastic reset member includes a first telescopic elastic member and a second telescopic elastic member;

[0028] One end of the first telescopic elastic member abuts against the fixing groove of the first locking member, and the other end abuts against the top inner wall of the propeller fixing seat;

[0029] One end of the second telescopic elastic member abuts against the fixing groove of the second locking member, and the other end abuts against the top inner wall of the propeller fixing seat.

[0030] As described above, in the propeller base assembly, the propeller mounting base is threadedly connected to the mounting base;

[0031] When the propeller mount and the mounting base are configured to rotate relative to each other in a predetermined direction, the connection between the propeller mount and the mounting base is released.

[0032] As described above, in the propeller base assembly, the propeller mounting base has an unlocking direction and a locking direction relative to the mounting base;

[0033] The non-hinged end is provided with a clearance slope. When the propeller fixing seat is rotated in the unlocking direction, the side wall of the limiting groove pushes the locking member through the clearance slope, causing it to leave the limiting groove.

[0034] As described above, in the propeller base assembly, the non-hinged end has a clearance groove on one side corresponding to the unlocking direction, and the clearance ramp is located in the clearance groove.

[0035] As described above, in the propeller base assembly, an elastic gasket is provided between the propeller mounting base and the mounting base to maintain a preload between the propeller mounting base and the mounting base when the propeller mounting base is assembled to the mounting base.

[0036] The second technical solution adopted by the present invention to solve its technical problem is: to provide a propeller quick-release device, which includes:

[0037] propeller;

[0038] And the propeller base assembly as described above; wherein the propeller is detachably mounted on the side of the propeller mounting base opposite to the mounting base.

[0039] The third technical solution adopted by the present invention to solve its technical problem is: to provide an unmanned aerial vehicle, which includes:

[0040] The fuselage; and the propeller quick-release device as described above; wherein the rotating part of the motor on the fuselage is fixedly connected to the mounting base.

[0041] The beneficial effects of this invention are as follows:

[0042] In the propeller base assembly of the present invention, the propeller mounting base is used to mount the rotor. It has an extension groove on its periphery and a locking member connected internally. The locking member is partially exposed through the extension groove and configured to swing within the extension groove in response to external force. The mounting base is connected to the propeller mounting base and has a limiting groove on its periphery that mates with the locking member. When the propeller mounting base is assembled onto the mounting base and in place, the end of the locking member extending from the extension groove engages with the limiting groove, forming a circumferential limit on the relative rotation of the two. This effectively prevents the propeller mounting base from loosening or falling off during unmanned aerial vehicle (UAV) flight, avoiding the risk of "propeller ejection." During disassembly, since the locking member is configured to disengage from the limiting groove based on the swing, the user only needs to use external force to swing the locking member away from the limiting groove to easily remove the propeller mounting base. This structure, through the cooperation of the locking member and the limiting groove, achieves tool-free quick assembly and disassembly of the rotor assembly, combining ease of operation with reliable connection. Attached Figure Description

[0043] The present invention will be further described below with reference to the accompanying drawings and embodiments;

[0044] Figure 1 This is a three-dimensional structural diagram of the propeller base assembly;

[0045] Figure 2 This is one of the cross-sectional views of an embodiment of the propeller base assembly in its assembled state;

[0046] Figure 3 This is a second cross-sectional view of one embodiment of the propeller base assembly in its assembled state.

[0047] Figure 4 This is an exploded view of one embodiment of the propeller base assembly;

[0048] Figure 5 A bottom view of a propeller mounting bracket, which is one embodiment of a propeller base assembly.

[0049] Figure 6 This is a side view of one embodiment of the propeller base assembly in its assembled state;

[0050] Figure 7This is a cross-sectional view of another embodiment of the propeller base assembly in its assembled state.

[0051] Figure 8 This is an exploded view of another embodiment of the propeller base assembly;

[0052] Figure 9 This is a bottom view of a propeller mount, which is another embodiment of the propeller base assembly.

[0053] Figure 10 This is an assembly diagram of the propeller quick-release device;

[0054] Figure 11 This is a structural diagram of an unmanned aerial vehicle.

[0055] The attached figures are labeled as follows:

[0056] Propeller base assembly 1000;

[0057] Propeller mounting base 1100, extension slot 1110, first extension slot 1111, second extension slot 1112;

[0058] Mounting base 1200, limiting groove 1210, first limiting groove 1211, second limiting groove 1212;

[0059] Locking fastener 1300, non-hinged end 13a, ear plate 13b, fixing groove 13c, clearance slope 13d, clearance groove 13e, first locking fastener 1310, second locking fastener 1320;

[0060] Elastic reset element 1400, torsional elastic element 1410, first working end 1411, second working end 1412, first telescopic elastic element 1420, second telescopic elastic element 1430;

[0061] First fixing block 1510, first mounting slot 1511, second fixing block 1520, second mounting slot 1521, locking block 1530;

[0062] Hinged shaft 1600; elastic washer 1700;

[0063] Propeller 2000, propeller rotation center 2100; motor 3000; fuselage 4000. Detailed Implementation

[0064] The present invention will be further described in detail below with reference to specific embodiments, but the implementation of the present invention is not limited thereto.

[0065] The following will clearly and completely describe the concept, specific structure, and technical effects of the present invention in conjunction with embodiments and accompanying drawings, so as to fully understand the purpose, features, and effects of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of them. Other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are all within the scope of protection of the present invention. Furthermore, all connection relationships involved in the patent do not simply refer to direct connection of components, but rather to the ability to form a better connection structure by adding or reducing connecting accessories according to specific implementation conditions. The various technical features in this invention can be combined interactively without contradicting each other.

[0066] Most existing unmanned aerial vehicles (UAVs) are multi-rotor UAVs. By controlling the differential speed of the motors of multiple rotors, they can achieve full attitude control, including pitch, roll, and yaw. However, the rotors (propellers) of multi-rotor UAVs are not always fixed to the fuselage. The rotors must be removed for transportation and storage, routine inspection and maintenance, replacement after failure or accident, upgrades and modifications, and to meet air transport regulations. This is to prevent damage from impacts, facilitate maintenance and upgrades, and ensure transportation safety.

[0067] However, existing quick-release structures generally suffer from problems such as poor installation stability, easy loosening after long-term use, and inconvenient disassembly, making it difficult to balance quick assembly and disassembly with high reliability requirements.

[0068] Therefore, how to balance the ease of rotor disassembly with the stability of installation is a research hotspot in the industry.

[0069] Reference Figure 1 The illustrated embodiment provides a propeller base assembly 1000, including a propeller mounting base 1100, a mounting base 1200, and a locking member 1300. A propeller 2000 is mounted on the propeller mounting base 1100. The propeller mounting base 1100 has a protrusion groove 1110 on its periphery. The mounting base 1200 has a limiting groove 1210 on its periphery. The locking member 1300 is connected to the propeller mounting base 1100, and one end of the locking member 1300 protrudes through the protrusion groove 1110 and is configured to swing within the protrusion groove 1110 in response to an external force. For example, the end of the locking member 1300 protruding from the protrusion groove 1110 has a degree of freedom to swing up and down; when an upward force is applied to this end, the end will swing upward in response to the force.

[0070] When the propeller mounting base 1100 is assembled onto the mounting base 1200 and in place, the end of the locking member 1300 extending out of the protrusion slot 1110 engages with the limiting slot 1210 and is configured to disengage from the limiting slot 1210 based on the swing.

[0071] The locking element 1300 uses its connection point within the propeller mounting base 1100 as a fulcrum, and its end embeds into the limiting groove 1210 of the mounting base 1200 to form a self-locking structure, thereby restricting the circumferential rotation of the propeller mounting base 1100 relative to the mounting base 1200 around its axis. This design ensures that during flight, the locking element 1300 can effectively engage in the limiting groove 1210, preventing the propeller from detaching from the mounting base 1100 at high speeds and thus avoiding a "propeller ejection" accident, thereby preventing the rotor from detaching from the unmanned aerial vehicle and ensuring flight safety.

[0072] When it is necessary to detach the rotor from the unmanned aerial vehicle, an external force is applied to the locking member 1300 to disengage it from the limiting groove 1210, thereby releasing the rotation restriction on the propeller mounting base 1100. Therefore, the propeller base assembly provided in this embodiment can not only reliably maintain the connection between the propeller mounting base 1100 and the mounting base 1200 when the rotor is running, but also disassembly is very convenient. After releasing the rotation restriction of the propeller mounting base 1100 by the locking member 1300, the propeller mounting base 1100 and the mounting base 1200 can be separated.

[0073] Furthermore, in this embodiment, the locking member 1300 is hinged within the propeller mounting base, and the non-hinged end of the locking member extends through the extension slot 1110 and is configured to swing about its hinge point within the extension slot 1110 in response to an external force.

[0074] When the propeller mounting base 1100 is assembled into the mounting base 1200 and in place, the non-hinged end of the locking member 1300 engages with the limiting groove 1210, and the non-hinged end of the locking member 1300 is configured to disengage from the limiting groove 1210 around its hinge point based on the swing.

[0075] The connection of the locking member 1300 within the propeller mounting base 1100 is a hinged connection. Therefore, when an external force is applied from bottom to top to the non-hinged end of the locking member 1300, the non-hinged end will respond to the external force and swing around the hinge point, thereby disengaging from the limiting groove 1210.

[0076] Based on this embodiment, the propeller base assembly 1000 may further include an elastic reset member. This elastic reset member is disposed within the propeller mounting base 1100 and cooperates with the locking member 1300. By applying force to the locking member 1300, the non-hinged end of the locking member 1300 tends to remain locked, so that when the propeller mounting base 1100 is assembled in place, the locking member 300 can automatically engage with the limiting groove 1210.

[0077] Thus, when the locking element 1300 disengages from the limiting groove 1210 under external force, the locking element 1300 causes the elastic reset element to deform and store elastic potential energy, at which point the propeller mounting base 1100 can separate relative to the mounting base 1200. When the propeller mounting base 1100 is assembled in place and the external force is removed, the elastic reset element returns to its natural state, driving the locking element 1300 to automatically engage with the limiting groove 1210. Therefore, the elastic reset element not only enhances the connection stability and reliability of the locking structure but also makes the disassembly of the propeller mounting base 1100 more convenient and labor-saving.

[0078] refer to Figures 2 to 4 The illustrated embodiment provides a propeller base assembly 1000. The protrusion slots include a first protrusion slot 1111 and a second protrusion slot 1112 disposed opposite to each other. The limiting slots include a first limiting slot 1211 and a second limiting slot 1212 disposed opposite to each other. The locking members include a first locking member 1310 and a second locking member 1320 disposed opposite to each other and hinged at their ends. The first locking member 1310 and the second locking member 1320 are respectively fitted into the first protrusion slot 1111 and the second protrusion slot 1112.

[0079] The elastic reset member 1400 cooperates with the first locking member 1310 and the second locking member 1320 respectively, so that when the propeller mounting base 1100 is assembled in place, the non-hinged ends of the first locking member 1310 and the second locking member 1320 are respectively engaged in the first limiting groove 1211 and the second limiting groove 1212.

[0080] For details, please refer to Figure 2 and Figure 3 The first locking member 1310 and the second locking member 1320 are provided with a fixing groove 13c in the middle. The elastic reset member 1400 includes a first telescopic elastic member 1420 and a second telescopic elastic member 1430. One end of the first telescopic elastic member 1420 abuts against the fixing groove 13c of the first locking member 1310, and the other end abuts against the top inner wall of the propeller mounting base 1100. One end of the second telescopic elastic member 1430 abuts against the fixing groove 13c of the second locking member 1320, and the other end abuts against the top inner wall of the propeller mounting base 1100.

[0081] exist Figure 2 In the process, since the first telescopic elastic member 1420 and the second telescopic elastic member 1430 are both in the extended state, the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 are respectively engaged in the first limiting groove 1211 and the second limiting groove 1212 to form a self-locking mechanism, thereby fixing the rotor to the unmanned aerial vehicle.

[0082] exist Figure 3In the process, as the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 swing around their hinge points under the action of external force, and compress the first telescopic elastic member 1420 and the second telescopic elastic member 1430 respectively, the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 disengage from the first limiting groove 1211 and the second limiting groove 1212 respectively, releasing the self-locking, and the rotor can be removed from the unmanned aerial vehicle.

[0083] In this embodiment, since the first locking member 1310 and the second locking member 1320 are coaxially arranged, when the propeller mounting base 1100 is rotated, the first locking member 1310 and the second locking member 1320 are subjected to forces in opposite directions, forming a force couple. This force couple action causes the applied force to be mainly converted into a torque that rotates the propeller mounting base 1100 relative to the mounting base 1200, without generating a translational force that pushes the propeller mounting base 1100 on the plane. Therefore, when the propeller mounting base 1100 and the mounting base 1200 are in a locked state, the operating force applied by the user can be efficiently concentrated on unlocking rotation, improving the efficiency of the unlocking operation. In addition, the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 protrude from the first protrusion groove 1111 and the second protrusion groove 1112, respectively. This protruding structure can also serve as a force application part, assisting the user to push the propeller mounting base 1100 to rotate more effortlessly.

[0084] Furthermore, in this embodiment, both the first telescopic elastic element 1420 and the second telescopic elastic element 1430 are springs. Of course, those skilled in the art can conceive of using other telescopic elastic elements besides springs to replace them.

[0085] Furthermore, in this embodiment, both the hinged ends of the first locking member 1310 and the second locking member 1320 are provided with ear plates 13b with shaft holes. After the ear plates 13b of the first locking member 1310 and the second locking member 1320 are stacked, the hinge shaft 1600 passes through the shaft hole on the ear plate 13b, so that the ear plates 13b of the first locking member 1310 and the second locking member 1320 are hinged together to the hinge shaft 1600.

[0086] Specifically, the ends of the ear plates 13b of the first locking member 1310 and the second locking member 1320 are arc-shaped, which facilitates the rotation of the first locking member 1310 and the second locking member 1320 around the hinge axis 1600.

[0087] refer to Figures 7 to 9The illustrated embodiment provides a propeller base assembly 1000. The extension slot 1110 includes a first extension slot 1111 and a second extension slot 1112 disposed opposite to each other. The limiting slot 1210 includes a first limiting slot 1211 and a second limiting slot 1212 disposed opposite to each other. The locking member 1300 includes a first locking member 1310 and a second locking member 1320 disposed opposite to each other and hinged at their ends. The first locking member 1310 and the second locking member 1320 are respectively fitted into the first extension slot 1111 and the second extension slot 1112.

[0088] The elastic reset member 1400 cooperates with the first locking member 1310 and the second locking member 1320 respectively, so that when the propeller mounting base 1100 is assembled in place, the non-hinged ends of the first locking member 1310 and the second locking member 1320 are respectively engaged in the first limiting groove 1211 and the second limiting groove 1212.

[0089] For details, please refer to Figure 7 and Figure 8 The first locking member 1310 and the second locking member 1320 are provided with a fixing groove 13c in the middle. The elastic reset member 1400 is a torsional elastic member 1410. The first working end 1411 and the second working end 1412 of the torsional elastic member 1410 respectively abut against the fixing groove 13c of the first locking member 1310 and the second locking member 1320.

[0090] Furthermore, in this embodiment, the torsional elastic element 1410 is a torsion spring. The spring body of the torsion spring is sleeved on the hinge shaft 1600. Thus, the hinge shaft 1600 limits the movement of the spring body of the torsion spring, thereby enhancing the stability and reliability of the locking structure. Of course, those skilled in the art can conceive of using other torsional elastic elements besides the torsion spring, such as a torsion spring sheet.

[0091] exist Figure 7 In the process, since the torsional elastic element 1410 (such as a torsion spring) is in a stretched state, the non-hinged ends 13a of the first locking element 1310 and the second locking element 1320 are respectively engaged in the first limiting groove 1211 and the second limiting groove 1212 to form a self-locking mechanism, thereby fixing the rotor to the unmanned aerial vehicle.

[0092] When the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 swing around their hinge points under the action of external force, the torsional elastic member 1410 will deform and store elastic potential energy, thereby causing the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 to disengage from the first limiting groove 1211 and the second limiting groove 1212 respectively, releasing the self-locking, and the rotor can be removed from the unmanned aerial vehicle.

[0093] In this embodiment, since the first locking member 1310 and the second locking member 1320 are coaxially arranged, when the propeller mounting base 1100 is rotated, the first locking member 1310 and the second locking member 1320 are subjected to forces in opposite directions, forming a force couple. This force couple action causes the applied force to be mainly converted into a torque that rotates the propeller mounting base 1100 relative to the mounting base 1200, without generating a translational force that pushes the propeller mounting base 1100 on the plane. Therefore, when the propeller mounting base 1100 and the mounting base 1200 are in a locked state, the operating force applied by the user can be efficiently concentrated on unlocking rotation, improving the efficiency of the unlocking operation. In addition, the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 protrude from the first protrusion groove 1111 and the second protrusion groove 1112, respectively. This protruding structure can also serve as a force application part, assisting the user to push the propeller mounting base 1100 to rotate more effortlessly.

[0094] Furthermore, in this embodiment, both the hinged ends of the first locking member 1310 and the second locking member 1320 are provided with ear plates 13b with shaft holes. After the ear plates 13b of the first locking member 1310 and the second locking member 1320 are stacked, the hinge shaft 1600 passes through the shaft hole on the ear plate 13b, so that the ear plates 13b of the first locking member 1310 and the second locking member 1320 are hinged together to the hinge shaft 1600.

[0095] Specifically, the ends of the ear plates 13b of the first locking member 1310 and the second locking member 1320 are arc-shaped, which facilitates the rotation of the first locking member 1310 and the second locking member 1320 around the hinge axis 1600.

[0096] Reference Figure 2 , Figure 3 , Figure 4 , Figure 7 and Figure 8 In the illustrated embodiment, the propeller mounting base 1100 and the mounting base 1200 are connected by a threaded connection. Of course, those skilled in the art will conceive of using other connection methods besides threaded connections, such as snap-fit ​​connections.

[0097] In this embodiment, an elastic washer 1700 is provided between the propeller mounting base 1100 and the mounting base 1200. The elastic washer 1700 is used to maintain a preload between the propeller mounting base 1100 and the mounting base 1200 when the propeller mounting base 1100 is assembled to the mounting base 1200. Based on this, after tightening the propeller mounting base 1100 and the mounting base 1200, the elastic washer 1700 will be compressed and generate a continuous rebound effect, thereby forming a preload. This preload can keep the threaded mating surfaces continuously pressed, thereby effectively preventing the propeller mounting base 1100 from rotating. This structure further reduces the risk of "propeller ejection" due to loose connections during the flight of the unmanned aerial vehicle, and avoids accidental rotor detachment.

[0098] Furthermore, in this embodiment, the elastic gasket 4 is made of a highly elastic rubber material, which generates a preload torque of 0.5-1.5 N·m after compression, effectively suppressing thread loosening. Of course, those skilled in the art can conceive of using other elastic materials besides highly elastic rubber.

[0099] Reference Figure 4 and Figure 8 In the illustrated embodiment, the propeller mounting base 1100 and the mounting base 1200 are connected by a thread. When the propeller mounting base 1100 and the mounting base 1200 rotate relative to each other, the connection between the propeller mounting base 1100 and the mounting base 1200 can be released.

[0100] When the propeller base assembly 1000 is mounted on the fuselage of the unmanned aerial vehicle (UAV), the mounting base 1200 is connected to the rotating part of the motor that drives the propeller on the fuselage, and the propeller 2000 is mounted on the propeller mounting base 1100. The power output from the motor is sequentially transmitted to the mounting base 1200, the propeller mounting base 1100, and the propeller 2000, causing them to rotate synchronously, thereby providing flight power for the UAV.

[0101] Therefore, in this embodiment, the screw tightening direction between the propeller mounting base 1100 and the mounting base 1200 can be set to be opposite to the rotation direction when the motor is working, so that the propeller mounting base 1100 can be further tightened by utilizing the rotation trend of the motor during flight, forming a dynamic self-locking and enhancing the tightness of the connection.

[0102] Furthermore, although there may sometimes be slight assembly gaps between the first locking member 1310 and the first limiting groove 1211, and between the second locking member 1320 and the second limiting groove 1212, after the motor starts, since the above-mentioned thread rotation direction is opposite to the motor rotation direction, the reverse torque generated by the motor will drive the propeller mounting base 1100 to continue to tighten, thus automatically eliminating the gaps, preventing loosening, and ensuring the reliability of the propeller base assembly during operation.

[0103] refer to Figure 4 and Figure 8 In the illustrated embodiment, a propeller rotation center 2100 is provided on the side of the propeller mounting base 1100 opposite to the mounting base 1200 for positioning the propeller 2000 during assembly.

[0104] The propeller rotation center 2100 ensures the stability and balance of the propeller 2000 during rotation, improving the flight performance and safety of the unmanned aerial vehicle (UAV). At the same time, the design of the propeller rotation center 2100 facilitates the installation and removal of the propeller, further enhancing the ease of maintenance for the UAV.

[0105] refer to Figures 5 to 6 In the illustrated embodiment, the propeller mounting base 1100 and the mounting base 1200 are connected by threads. When the propeller mounting base 1100 and the mounting base 1200 are configured to rotate relative to each other in a predetermined direction, the connection between the propeller mounting base 1100 and the mounting base 1200 can be released. That is, the propeller mounting base 1100 has an unlocking direction and a locking direction relative to the mounting base 1200.

[0106] The non-hinged end 13a is provided with a clearance slope 13d. When the propeller mounting base 1100 is rotated in the unlocking direction, the side wall of the first limiting groove 1211 pushes the non-hinged end 13a of the first locking member 1310 through the clearance slope 13d, causing the non-hinged end 13a to move upward away from the first limiting groove 1211. Similarly, the side wall of the second limiting groove 1212 pushes the non-hinged end 13a of the second locking member 1320 through the clearance slope 13d, causing the non-hinged end 13a to leave the second limiting groove 1212.

[0107] Therefore, when connecting the propeller mounting base 1100 and the mounting base 1200, when the propeller mounting base 1100 is rotated in the unlocking direction, the first limiting groove 1211 and the second limiting groove 1212 will respectively cooperate with the two clearance inclined surfaces 13d to push the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 upward, so that the two non-hinged ends 13a are respectively disengaged from the first limiting groove 1211 and the second limiting groove 1212 of the mounting base 1200, thereby allowing the propeller mounting base 1100 to be removed from the mounting base 1200, completing the quick disassembly of the propeller. When it is necessary to reinstall the propeller back onto the unmanned aerial vehicle, simply reinstall the propeller mounting bracket 1100 onto the mounting base 1200 and rotate the propeller mounting bracket 1100 in the locking direction. After rotation into place, the non-hinged ends 13a of the first locking member 1310 and the second locking member 1320 will automatically fall down and re-engage into the first limiting groove 1211 and the second limiting groove 1212 on the mounting base 1200, achieving rapid propeller installation. This design features automatic unlocking when loosened and automatic locking when tightened, which not only simplifies the propeller disassembly and assembly process and improves disassembly and assembly efficiency, but also ensures the stability and reliability of the locking structure.

[0108] Furthermore, in this embodiment, the non-hinged end 13a is provided with a clearance groove 13e on the side corresponding to the unlocking direction, and the clearance slope 13d is located in the clearance groove 13e. In this way, when the user pinches the non-hinged end 13a and applies force, the area in contact with the finger is larger, which can reduce the pressure of the locking element 1300 on the finger and improve the comfort during the unlocking process.

[0109] Reference Figure 5 In the illustrated embodiment, the propeller mounting base 1100 is provided with a first fixing block 1510, a second fixing block 1520 and a locking block 1530.

[0110] The first fixing block 1510 is provided with a first mounting groove 1511. The second fixing block 1520 is provided with a second mounting groove 1521. The locking block 1530 is configured to cooperate with the first fixing block 1510 and the second fixing block 1520. The hinged ends of the first locking member 1310 and the second locking member 1320 are inserted into a hinge shaft 1600. The locking block 1530 limits the two ends of the hinge shaft 1600 to be respectively within the first mounting groove 1511 and the second mounting groove 1521.

[0111] In this embodiment, the locking block 1530 ensures the stability of the hinge shaft 1600 on the first fixing block 1510 and the second fixing block 1520, preventing the hinge shaft 1600 from shaking or shifting during rotation, thus affecting the normal rotation of the first locking member 1310 and the second locking member 1320. Simultaneously, the design of the locking block 1530 facilitates the installation and removal of the hinge shaft 1600 by the user, improving the ease of maintenance of the unmanned aerial vehicle.

[0112] Furthermore, in order to enhance the structural strength of the propeller mounting base 1100, the first fixing block 1510 and the second fixing block 1520 can be firmly fixed to the propeller mounting base 1100 by welding, screw connection or other fixing methods, to ensure that the propeller mounting base 1100 can remain stable when rotating at high speed and to avoid loosening or falling off.

[0113] Reference Figures 8 to 9 In the illustrated embodiment, the propeller mounting base 1100 is provided with a first fixing block 1510, a second fixing block 1520 and a locking block 1530.

[0114] The first fixing block 1510 is provided with a first mounting groove 1511. The second fixing block 1520 is provided with a second mounting groove 1521. The locking block 1530 is configured to cooperate with the first fixing block 1510 and the second fixing block 1520. The hinged ends of the first locking member 1310 and the second locking member 1320 are inserted into a hinge shaft 1600. The locking block 1530 limits the two ends of the hinge shaft 1600 to be respectively within the first mounting groove 1511 and the second mounting groove 1521.

[0115] In this embodiment, the elastic reset member 1400 is a torsion spring. One end of the hinge shaft 1600 is limited within the second mounting groove 1521, and the portion of this end extending out of the second mounting groove 1521 passes into the spring body of the torsion spring, so that the torsion spring is fitted onto the hinge shaft 1600. Thus, while realizing the function of the locking member's rotation fulcrum, the hinge shaft 1600 also forms a radial limit on the spring body of the torsion spring, thereby improving the overall stability and reliability of the locking structure.

[0116] In addition, Figure 8 In the middle, the locking block 1530 has an adaptive clearance space designed for the position of the spring body near the torsion spring.

[0117] refer to Figure 10 In the illustrated embodiment, this embodiment provides a propeller quick-release device, which includes a propeller 2000 and a propeller base assembly provided in any embodiment of the present invention. The propeller 2000 is detachably mounted on the side of the propeller mounting base 1100 opposite to the mounting base 1200.

[0118] Based on this embodiment, refer to Figure 11 The present invention also provides an unmanned aerial vehicle, which includes a fuselage 4000 and a propeller quick-release device provided in this embodiment. The motor 3000 on the fuselage 4000 drives the propeller to rotate, and its rotating part is fixedly connected to the mounting base 1200.

[0119] The unmanned aerial vehicle of the present invention may include, but is not limited to, any one of the following: patrol / surveillance drones, agricultural drones, meteorological drones, exploration drones, surveying drones, reconnaissance drones, decoy drones, electronic warfare drones, and communication relay drones.

[0120] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A propeller mount assembly, characterized by, The propeller fixing base is provided with an extension slot on the peripheral side thereof; The mounting base is provided with a limiting slot on the peripheral side thereof; The lock piece is connected to the propeller fixing base, and one end thereof extends out of the extension slot and is configured to swing in response to an external force acting in the extension slot; When the propeller fixing base is assembled in the mounting base, the end of the lock piece extending out of the extension slot is clamped into the limiting slot, and is configured to be disengaged from the limiting slot based on the swinging. The lock piece is hinged in the propeller fixing base, and the non-hinged end of the lock piece extends out of the extension slot and is configured to swing in the extension slot around the hinge point thereof in response to an external force acting; 2. The propeller mount assembly of claim 1, wherein, When the propeller fixing base is assembled in the mounting base, the non-hinged end is clamped into the limiting slot, and the non-hinged end is configured to be disengaged from the limiting slot based on the swinging. Further comprising an elastic reset piece; 3. The propeller mount assembly of claim 2, wherein, The elastic reset piece is arranged in the propeller fixing base and cooperates with the lock piece to apply a force to the lock piece, so that the non-hinged end is kept in a locked state, so that the lock piece is automatically clamped into the limiting slot when the propeller fixing base is assembled. The extension slot comprises a first extension slot and a second extension slot arranged oppositely; 4. The propeller mount assembly of claim 3, wherein, The limiting slot comprises a first limiting slot and a second limiting slot arranged oppositely; The lock piece comprises a first lock piece and a second lock piece arranged oppositely and hinged at the ends thereof, and the first lock piece and the second lock piece are arranged in the first extension slot and the second extension slot respectively; The elastic reset piece cooperates with the first lock piece and the second lock piece respectively, so that the non-hinged ends of the first lock piece and the second lock piece are clamped into the first limiting slot and the second limiting slot respectively when the propeller fixing base is assembled. The propeller fixing base is provided with:

5. The propeller mount assembly of claim 4, wherein, A first fixing block provided with a first mounting slot thereon; A second fixing block provided with a second mounting slot thereon; A locking block configured to cooperate with the first fixing block and the second fixing block; the hinged ends of the first lock piece and the second lock piece are inserted on a hinge shaft, and the locking block limits the two ends of the hinge shaft in the first mounting slot and the second mounting slot respectively. The hinged ends of the first lock piece and the second lock piece are each provided with an ear plate with an axle hole; the ear plates of the first lock piece and the second lock piece are overlapped and the hinge shaft passes through the axle hole, so that the ear plates of the first lock piece and the second lock piece are hinged on the hinge shaft together.

6. The propeller mount assembly of claim 5, wherein, The end of the ear plate is a circular arc surface.

7. The propeller mount assembly of claim 6, wherein, The middle part of the first lock piece and the second lock piece is provided with a fixing groove, and one end of the elastic reset piece abuts in the fixing groove.

8. A propeller mount assembly according to any one of claims 5 to 7, wherein, The elastic reset piece is a torsional elastic piece; 9. The propeller mount assembly of claim 8, wherein, The first acting end and the second acting end of the torsional elastic piece abut in the fixing groove of the first lock piece and the second lock piece respectively. The torsional elastic piece is a torsional spring, and the spring body of the torsional spring is sleeved on the hinge shaft.

10. The propeller mount assembly of claim 9, wherein, The elastic reset piece comprises a first telescopic elastic piece and a second telescopic elastic piece; 11. The propeller mount assembly of claim 8, wherein, ​ One end of the first telescopic elastic member abuts against the fixed groove of the first locking member, and the other end abuts against the inner wall of the top of the propeller fixing base; One end of the second telescopic elastic member abuts against the fixed groove of the second locking member, and the other end abuts against the inner wall of the top of the propeller fixing base.

12. The propeller mount assembly of any one of claims 1-11, wherein, The propeller fixing base is threadedly connected with the mounting base; When the propeller fixing base and the mounting base are relatively rotated in a predetermined direction, the connection between the propeller fixing base and the mounting base is released.

13. The propeller mount assembly of claim 12, wherein, The propeller fixing base has an unlocking direction and a locking direction relative to the mounting base; The non-hinged end is provided with a clearance inclined surface, when the propeller fixing base is rotated towards the unlocking direction, the side wall of the limiting groove pushes the locking member away from the limiting groove through the clearance inclined surface.

14. The propeller mount assembly of claim 13, wherein, The non-hinged end is provided with a clearance groove corresponding to one side of the unlocking direction, and the clearance inclined surface is located in the clearance groove.

15. The propeller mount assembly of any one of claims 12-14, wherein, An elastic gasket is arranged between the propeller fixing base and the mounting base, so that the propeller fixing base and the mounting base are kept in pre-tightening force when the propeller fixing base is assembled in the mounting base.

16. A propeller quick release device characterized by, It comprises: a propeller; and the propeller base assembly according to any one of claims 1-15; wherein the propeller is detachably mounted on the side of the propeller fixing base away from the mounting base.

17. An unmanned aerial vehicle, comprising: It comprises: a fuselage; and the propeller quick release device according to claim 16; wherein the rotating part of the motor on the fuselage is fixedly connected with the mounting base.

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