A propeller quick disassembly and assembly structure and an aircraft equipped with the same

Abstract

The present invention discloses a propeller quick disassembly and assembly structure and an aircraft provided with the structure, which is characterized in that: a locking safety is provided with a first boss, a button is provided with a first groove, and the first boss matches the first groove; an upper inclined surface matches the upper mating surface of a propeller blade, and the upper inclined surface can press the corresponding upper mating surface of the blade during the disassembly and assembly of the blade; a lower inclined surface matches the lower mating surface of the propeller blade, and the lower inclined surface of the button can realize the function of the button being linked according to the lower mating surface through the up and down movement of the blade during the installation and ejection of the blade; the hub is in a long strip shape, and when the blade is pressed down and fitted to the base, the button presses the two ends of the blade hub through the corresponding upper inclined surface or lower inclined surface. The propeller quick disassembly and assembly structure disclosed by the present invention and the aircraft provided with the structure are simple to disassemble and assemble, have high insurance and safety levels, reduce wear, save costs, and increase product service life.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft propeller disassembly and assembly, and in particular to a propeller quick disassembly and assembly structure and an aircraft provided with the structure. Background Art

[0002] A propeller is a device that converts the engine's rotational power into propulsion by rotating the blades in the air or water. It may have two or more blades connected to the hub, and the rear side of the blade is a helical surface or a propeller similar to a helical surface. It is an important structure of helicopters and other aircraft. Generally, in addition to rotation, the propeller also has a forward speed. The application of propellers in helicopters and other aircraft is particularly important. Existing propellers generally have one or more of the following characteristics during use. The structure of the root of the blade is mostly a circular outer contour, which is suitable for small-sized blades. If it is to be used for large-sized blades, a lot of unnecessary structural weight needs to be added; the transition design between the root of the blade and the quick-release structure is not conducive to the local force on the root of the blade and cannot be used for large blades; for propellers made of plastic, the hub structure is too complicated, which increases the mold structure responsibility and mold production and maintenance costs for plastic injection molds, greatly reducing the service life of the mold; the quick-release contact surface is prone to wear; the processing error accuracy requirements are high, and the quick-release structure contact surface is prone to gaps, which will cause bumps and wear, and the gap will also cause vibration, which will affect the safety and life of the motor and even the aircraft or related carrier structure; there is a spring in the propeller quick-release structure, and the spring force is large The small size of the propeller creates a contradiction between the reliability of the structure and the amount of manual effort required during the installation process. The operation of the quick disassembly and assembly process is not convenient enough and does not really save much time. For most inexperienced users, it is easy to damage the quick-release structure due to misoperation. The concentric positioning of the propeller and the rotating shaft is not accurate enough, which affects the dynamic balance stability of the propeller during operation. The propeller is not parallel to the installation plane and the contact area is too small, which affects the aerodynamic balance of the propeller during operation. The propeller has to operate under complex working conditions with large vibrations, and most of the existing technical solutions lack insurance design to ensure that the quick-release structure will not accidentally loosen during vibration. In this intelligent era, the existing technical solutions all remain at the level of using primitive mechanical structures to solve problems, and have not fully utilized the new features of intelligence to comprehensively improve the safety of the quick-release structure. Summary of the invention

[0003] The purpose of the present invention is to overcome the deficiencies of the prior art, solve the problems existing in the prior art, and provide a propeller quick disassembly and assembly structure and an aircraft equipped with the structure, which solves one or more problems existing in the prior art and achieves better results.

[0004] The technical solution of the present invention is:

[0005] A propeller quick disassembly and assembly structure, characterized in that it includes a locking safety, a button, and a base, wherein the base can be installed on a motor front cover or integrated on the propeller motor front cover.

[0006] The locking safety is provided with a first boss, and the button is provided with a first groove, wherein the first boss matches the first groove;

[0007] An upper inclined surface and a lower inclined surface are provided on one side of the button. The upper inclined surface matches the upper mating surface of the propeller blade. The upper inclined surface can press the upper mating surface corresponding to the propeller blade during the process of disassembling and assembling the propeller blade. The lower inclined surface matches the lower mating surface of the propeller blade. During the process of installing and ejecting the propeller blade, the lower inclined surface of the button can realize the function of the button to be linked according to the lower mating surface through the up and down movement of the blade.

[0008] The propeller hub is in the shape of a long strip. When the button is pressed down by the propeller blade and fits into the base, the button is pressed against both ends of the propeller hub through the corresponding matching inclined surfaces.

[0009] A first rotating shaft hole is arranged on both sides of the base, and a button is arranged on both sides of the base. A second rotating shaft hole corresponding to the first rotating shaft hole is arranged on the button. The rotating shaft can pass through the first rotating shaft hole and the second rotating shaft hole. The button is limited on both sides of the base by the rotating shaft and can rotate freely within a set angle.

[0010] As a further improvement of the present scheme, the upper inclined surface and the upper mating surface of the propeller blade are low near the center and high away from the center; the lower inclined surface and the lower mating surface of the propeller blade are low near the center and high away from the center.

[0011] As a further improvement of this solution, the upper mating surface of the blade is pressed against the button, and a corresponding opening is reserved for the button to pass through. There is a circular hole in the middle for fixing and allowing the locking safety to rotate in the mating position. Four spherical grooves are set on the middle platform of the blade for positioning with the spherical protrusion at the bottom of the locking safety to achieve locking and unlocking positions.

[0012] As a further improvement of this solution, a part of the locking safety is inserted into the middle hole in the middle of the blade, and the locking safety and the blade are in an assembled state and will not be easily separated. When the blade and locking safety combination is pressed into the base, the middle hole inside the rod extending from the lower part of the locking safety will be positioned and matched with the cylindrical boss in the middle of the base to ensure that the blade assembly and the motor base assembly are concentrically aligned.

[0013] As a further improvement of the present invention, upward limiting bosses are provided on both sides of the base, and a downward limiting groove is provided in the middle of the blade, and the limiting bosses cooperate with the limiting groove in the middle of the blade.

[0014] As a further improvement of the present solution, the limiting boss is an oblong boss, and the limiting groove is an oblong hole groove.

[0015] As a further improvement of the present solution, a second boss is arranged near the center of the locking safety, and the blade is provided with a second groove matching the second boss, and the second boss can be locked in cooperation with the second groove.

[0016] As a further improvement of the present solution, a central circular boss is provided at the center of the base, and a central hole in the rod body matching the central circular boss is provided at the lower part of the locking safety.

[0017] As a further improvement of the present solution, a plane contact positioning device is installed on the bottom plane of the hub of the blade and the upper surface of the base.

[0018] As a further improvement of the present solution, the base is provided with a center hole facing downward, the groove is positioned and matched with the motor shaft, and the base is fixed to the motor by screws.

[0019] An aircraft provided with the aforementioned propeller quick disassembly and assembly structure, characterized in that: it comprises a propeller, a motor, and a propeller quick disassembly and assembly structure, the propeller comprises blades and a hub, the hub is in an elongated shape, and the length direction is consistent with the centerline direction of the propeller blades;

[0020] The propeller quick disassembly and assembly structure includes a locking safety, a button, and a base. The base can be installed on the motor front cover or integrated on the propeller motor front cover.

[0021] The propeller blade is provided with an upper mating surface and a lower mating surface near the propeller seat, the upper mating surface matches the upper inclined surface of the button, and the lower mating surface matches the lower inclined surface of the button.

[0022] A first rotating shaft hole and a limiting boss are provided on both sides of the base, a limiting groove facing downward is provided in the middle of the blade, and the limiting boss cooperates with the limiting groove in the middle of the blade. Buttons are provided on both sides of the base, and a second rotating shaft hole corresponding to the first rotating shaft hole is provided on the button. The rotating shaft can pass through the first rotating shaft hole and the second rotating shaft hole. The button is limited on both sides of the base by the rotating shaft and can rotate freely within a set angle. A second boss is provided near the center position of the locking safety, and the blade is provided with a second groove matching the second boss, and the second boss can be locked by matching with the second groove; a central circular boss is provided at the center of the base, and a middle hole in the rod body matching the central circular boss is provided at the lower part of the locking safety.

[0023] Advantages of the present invention:

[0024] The propeller quick disassembly and assembly structure and the aircraft provided with the structure disclosed in the present invention have simple disassembly and assembly operations, high insurance and safety levels, reduced wear and tear, saved costs, and increased product service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The present invention will be further described below in conjunction with the accompanying drawings and embodiments:

[0026] Figure 1 It is a schematic diagram of the installation of propeller blades and hub in the prior art.

[0027] Figure 2 It is a schematic diagram of the installation of propeller blades and a propeller hub of an aircraft provided with a propeller quick disassembly and assembly structure according to the present invention.

[0028] Figure 3 It is a schematic diagram of the propeller quick disassembly and assembly structure of the present invention.

[0029] Figure 4 It is a schematic cross-sectional view of the propeller quick disassembly and assembly structure of the present invention.

[0030] Figure 5 It is an exploded view schematic diagram of the installation of propeller blades of an aircraft provided with a propeller quick disassembly and assembly structure according to the present invention.

[0031] Figure 6 yes Figure 5 A partial enlarged view.

[0032] Figure 7 It is a schematic diagram of the installation and locking state of the propeller blades of the aircraft provided with the propeller quick disassembly and assembly structure according to the present invention.

[0033] Figure 8 The invention discloses a schematic diagram of a propeller blade unlocking state of an aircraft provided with a propeller quick disassembly and assembly structure.

[0034] Fig. 9 It is a schematic diagram of the state of pressing a button on a propeller blade of an aircraft provided with a propeller quick disassembly and assembly structure according to the present invention.

[0035] Fig.10 yes Fig. 9 A partial enlarged view.

[0036] Fig.11 It is a schematic diagram of the propeller blades of the aircraft provided with the propeller quick disassembly and assembly structure according to the present invention after the propeller blades have been completely disassembled.

[0037] Among them: 1, locking safety 101, first boss 102, second boss 2, blade 201, first groove 202, upper mating surface 203, lower mating surface 204, limiting groove 3, button 301, upper inclined surface 302, lower inclined surface 4, base 401, rotation center 402, limiting boss 5, rotating shaft 6, hub. DETAILED DESCRIPTION

[0038] The technical solution of the present invention is described in detail below in conjunction with the accompanying drawings and preferred embodiments.

[0039] like Figure 1-11 As shown, the present invention discloses a propeller quick disassembly and assembly structure, which includes a locking insurance 1, a button 3, and a base 4. The base 4 can be installed on the motor front cover or integrated on the motor front cover of the propeller. The locking insurance 1 is provided with a first boss 101, and the button 3 is provided with a first groove 201. The first boss 101 matches the first groove 201; an upper inclined surface 301 and a lower inclined surface 302 are provided on one side of the button 3. The upper inclined surface 301 matches the upper matching surface 202 of the propeller blade 2. The upper inclined surface 301 can press the upper matching surface 202 corresponding to the blade 2 during the disassembly and assembly of the blade 2, and the lower inclined surface 302 matches the lower matching surface 203 of the propeller blade 2. During the installation and ejection process of the blade 2, the lower inclined surface 302 of the button 3 can realize the button through the up and down movement of the blade 2. 3 According to the function of linkage with the lower mating surface 203, the hub 6 is in the shape of a long strip. When the blade 2 is pressed down and fitted to the base 4, the button 3 presses the two ends of the hub 6 of the blade 2 through the corresponding upper inclined surface and the lower inclined surface. The base 4 is provided with a first rotating shaft 5 hole and a limiting boss 402 on both sides. The button 3 is provided on both sides of the base 4. The button 3 is provided with a second rotating shaft 5 hole corresponding to the first rotating shaft 5 hole. The rotating shaft 5 can pass through the first rotating shaft 5 hole and the second rotating shaft 5 hole. The button 3 is limited on both sides of the base 4 through the rotating shaft 5 and can rotate freely within the set angle. Therefore, when pressing in or taking out the blade 2, it is not necessary to turn the button 3 by hand, because the button 3 will realize linkage with the upper and lower running of the blade 2 according to the lower mating surface 203 and rotate in the corresponding required direction, simplifying the complexity of the operation. The contact and sliding between the inclined surface of the blade 2 during the rotation process of the button 3 is not strong friction. Minimizing the relative sliding between the contact surfaces as much as possible also reduces the wear between the contact surfaces. The carefully designed upper and lower inclined surfaces 302 of the button 3 and the matching surface (inclined surface) of the blade 2 can realize that the blade 2 does not need to be directly touched or operated during installation and removal. Because of the matching of the inclined surfaces of the two and the rotational freedom of the button 3, when the blade 2 moves up and down, the button 3 will rotate synchronously, greatly reducing the complexity of the operation. When the blade 2 is pressed in to the bottom, the button 3 will naturally move to the pressing position through the lower inclined surface 302 to make the upper inclined surface 301 press the blade 2, and then the locking safety 1 is rotated to the locking position, and the blade 2 is quickly assembled.

[0040] As a further improvement of the present scheme, the upper inclined surface 301 and the upper mating surface 202 of the propeller blade 2 are lower near the center and higher away from the center; the lower inclined surface 302 and the lower mating surface 203 of the propeller blade 2 are lower near the center and higher away from the center. After the locking safety 1 is locked, it forms a complete and mutually balanced force transmission path with the buttons 3 on both sides and the upper inclined surface of the blade 2. Once the blade 2 rotates and generates a bending moment from both sides to the middle, it will squeeze the buttons 3 on both sides to rotate toward the middle through the inclined surface, and then both of them will press against the two ends of the locking safety 1. Therefore, the entire structure itself forms a self-locking mode in the working state, which is tighter than the assembled quick-release structure that is not in the working rotation state, and it is less likely to cause the middle locking safety 1 to accidentally loosen due to vibration factors. Moreover, the greater the pulling force of the blade 2, the greater the clamping force on the locking safety 1, the more secure the locking, and the less likely it will loosen due to vibration.

[0041] As a further improvement of the present solution, the upper mating surface 202 of the blade 2 is pressed against the button 3, and a corresponding opening is reserved for the button 3 to pass through. A circular hole is provided in the middle of the button 3 for fixing and allowing the locking safety 1 to rotate in the mating position. Four spherical grooves are provided on the middle platform of the blade 2 for positioning with the spherical protrusion at the bottom of the locking safety 1 in the locking and unlocking positions, thereby facilitating the locking and unlocking operations.

[0042] As a further improvement of the present scheme, a part of the locking safety 1 is inserted into the middle hole in the middle of the blade 2. The locking safety 1 and the blade 2 are in an assembled state and will not be easily separated. When the blade 2 and the locking safety 1 combination is pressed onto the base 4, the middle hole inside the rod extending from the lower part of the locking safety 1 will be positioned and matched with the cylindrical boss in the middle of the base 4 to ensure that the blade 2 combination and the motor-base 4 combination are concentrically aligned.

[0043] As a further improvement of the present solution, upward limiting bosses 402 are provided on both sides of the base 4, and a downward limiting groove 204 is provided in the middle of the blade 2. The limiting boss 402 cooperates with the limiting groove 204 in the middle of the blade 2 to position the blade 2. The limiting boss 402 cooperates with the limiting groove 204 to transmit the torque required by the blade 2.

[0044] As a further improvement of this solution, the limiting boss 402 is an oblong boss, and the limiting groove 204 is an oblong hole groove. The oblong groove on the lower surface of the hub 6 of the blade 2 cooperates with the oblong boss at the corresponding position of the base 4 for circumferential positioning, and at the same time, the cooperation can effectively transmit the torque load between the blade 2 and the base 4. The torque load and the tensile load to be mentioned later can be separated. Since the oblong groove and the boss are far away from the rotation center 401, the stress level of the matching structure when it is subjected to torque can be greatly improved, the structural reliability can be enhanced, and the service life can be extended.

[0045] As a further improvement of the present solution, the locking safety 1 is provided with a second boss 102 near the center position, and the blade 2 is provided with a second groove matching the second boss 102, and the second boss 102 can be locked with the second groove. The second groove can be an oblong groove, and the second boss 102 can be an oblong boss. The oblong groove on the lower surface of the hub 6 of the blade 2 cooperates with the oblong boss at the corresponding position of the base 4 for circumferential positioning, and the cooperation can also effectively transmit the torque load between the blade 2 and the base 4. The torque load and the tensile load to be mentioned later can be separated. Since the oblong groove and the boss are far away from the rotation center 401, the stress level of the matching structure when it is subjected to torque can be greatly improved, the structural reliability can be enhanced, and the service life can be extended.

[0046] As a further improvement of the present invention, a central circular boss is provided at the center of the base 4, and a rod body middle hole matching the central circular boss is provided at the lower part of the locking safety 1. The lower rod body middle hole of the locking safety 1 is concentrically aligned with the central circular boss on the base 4, so as to minimize the dynamic balance problem of the blade 2 caused by inaccurate positioning.

[0047] As a further improvement of this solution, a plane contact positioning device is installed on the bottom plane of the hub 6 of the blade 2 and the upper surface of the base 4. The plane contact positioning device can ensure that the blade 2 is installed in the correct position, the blade 2 is closely matched with the top plane of the motor, and the problem of pneumatic imbalance is minimized.

[0048] The contact and sliding between the button 3 and the inclined surface of the blade 2 during the rotation process is not a strong friction. Minimizing the relative sliding between the contact surfaces will also reduce the wear between the contact surfaces. Through the carefully designed upper and lower inclined surfaces 302 of the button 3 and the inclined surface of the blade 2, it is possible to implement the process of inserting and removing the blade 2 without directly touching or operating the button 3. Because of the coordination of the inclined surfaces of the two and the rotational freedom of the button 3, when the blade 2 moves up and down, the button 3 will rotate synchronously, greatly reducing the complexity of the operation. When the blade 2 is pressed in to the bottom, the button 3 will naturally move to the pressing position through the lower inclined surface 302 to make the upper inclined surface 301 press the blade 2, and then rotate the locking safety 1 to the locking position, and the blade 2 is quickly assembled.

[0049] As a further improvement of this solution, the base 4 is provided with a center hole facing downward, the groove is positioned and matched with the motor shaft, and the base 4 is fixed to the motor by screws. The base 4 is centrally positioned with the motor shaft through the center hole on the downward surface, and then tightened by fastening screws. Furthermore, the quick-release structure of the base 4 can be directly integrated into the front end cover of the motor, so that even the above-mentioned center positioning and screw fastening are omitted, and the entire structure can save a part of weight and processing cost.

[0050] An aircraft provided with the aforementioned propeller quick disassembly and assembly structure, which includes a propeller, a motor, and a propeller quick disassembly and assembly structure, wherein the propeller includes a blade 2 and a hub 6, wherein the hub 6 is in an elongated shape, and the length direction is consistent with the center line direction of the propeller blade 2; the propeller quick disassembly and assembly structure includes a locking insurance 1, a button 3, and a base 4, wherein the base 4 can be installed on the motor front cover or integrated on the motor front cover of the propeller, and the propeller blade 2 is provided with an upper mating surface 202 and a lower mating surface 203 near the propeller seat, the upper mating surface 202 matches the upper inclined surface 301 of the button 3, and the lower mating surface 203 matches the lower inclined surface 302 of the button 3, and the first rotating shaft 5 hole and the limiting boss 402 are provided on both sides of the base 4, and the propeller blade 2 is provided with a limiting groove 204 facing downward, and the limiting boss 402 cooperates with the limiting groove 204 in the middle of the blade 2. The button 3 is provided on both sides of the base 4. The button 3 is provided with a second shaft 5 hole corresponding to the first shaft 5 hole. The shaft 5 can pass through the first shaft 5 hole and the second shaft 5 hole. The button 3 is limited on both sides of the base 4 by the shaft 5 and can rotate freely within a set angle. The locking insurance 1 is provided with a second boss 102 near the center position, and the blade 2 is provided with a second groove matching the second boss 102. The second boss 102 can be locked by matching with the second groove; a central circular boss is provided at the center of the base 4, and a rod body middle hole matching the central circular boss is provided at the lower part of the locking insurance 1. The hub 6 at the root of the propeller of the prior art quick-detachable structure is a circular profile. If the size is to be enlarged, the plan must be made according to the diameter of the circle, which will increase a lot of unnecessary structural volume and weight. However, the present technical solution only needs to be lengthened when the hub 6 is strong enough. Even if the hub 6 is to be widened, it does not need to be increased too much, which can greatly improve the structural utilization rate. The transition position between the hub 6 and the root of the blade 2 determines the stress level at the root of the blade 2. This embodiment can ensure the structural quality of the hub 6 that is as small as possible in the transition area of ​​the blade 2 at the same spacing. The circular hub 6 in the middle of the prior art solution determines that if this transition area is to be expanded to both ends of the blade 2, it can only be expanded by increasing the circular diameter of the hub 6. However, this embodiment only needs to lengthen the long strip hub 6 to achieve the transition area moving to both sides and thus improve the stress level of the transition area at the root of the blade 2. The long strip hub 6 design is adopted. When the two buttons 3 that can rotate within a certain range are pressed against the base 4 under the blade 2, the buttons 3 are pressed against the two ends of the hub 6 of the blade 2 through the corresponding matching inclined surfaces.

[0051] like Figure 6-Figure 9 The figure shows the process of disassembling and assembling the propeller blade 2 of the aircraft provided with the propeller quick disassembly and assembly structure, which is a schematic diagram of the installation and locking state of the propeller blade 2 of the aircraft provided with the propeller quick disassembly and assembly structure according to the present invention, and is the working state after the propeller clamp is installed and locked, such as Figure 7-8As shown, by rotating the locking safety 1 90 degrees around the central axis by hand, the safety lock can be released. The safety lock and the rotating pressure block match the groove, which can be easily locked in the locking position during manual operation. The first groove 201 and the first protrusion have a certain interference fit to prevent the entire blade 2 assembly from loosening due to vibration during operation; press the top side of the button 3 near the center, the button 3 rotates around the steel axis and tilts up, and the button 3 and the lower matching surface 203 of the blade 2 will push the blade 2 upward. Figure 8 As shown, the hand grasps the main body of the blade 2 and moves upward until it is completely away from the base 4, and the blade 2 is disassembled. The locking safety 1 rotates to the locking position to lock the buttons 3 on both sides so that the buttons 3 on both sides are back to back in rigid contact and transmit force. The locking safety 1 is designed with optimized dimensional tolerances to ensure that after the safety is locked in place, the two ends of the safety can forcefully press the upper surfaces of the buttons 3 on both sides, thereby making the buttons 3 completely press the upper inclined surfaces on both sides of the blade 2.

[0052] The entire quick-release structure has three layers of security. The first and second layers of security are the protrusions at both ends of the locking safety 1 and the spherical protrusions on the lower surface, which respectively lock with the grooves at the head of the button 3 and the spherical grooves on the upper surface of the middle part of the blade 2. The third layer of security is the self-locking effect achieved by the aerodynamic force of the entire blade 2 in the working state. This is a triple security to ensure that the quick-release structure will not loosen due to vibration in the working state.

[0053] The contact and sliding between the button 3 and the inclined surface of the blade 2 during the rotation process is not a strong friction. Minimizing the relative sliding between the contact surfaces will also reduce the wear between the contact surfaces. Through the carefully designed upper and lower inclined surfaces 302 of the button 3 and the inclined surface of the blade 2, it is possible to implement the process of inserting and removing the blade 2 without directly touching or operating the button 3. Because of the coordination of the inclined surfaces of the two and the rotational freedom of the button 3, when the blade 2 moves up and down, the button 3 will rotate synchronously, greatly reducing the complexity of the operation. When the blade 2 is pressed in to the bottom, the button 3 will naturally move to the pressing position through the lower inclined surface 302 to make the upper inclined surface 301 press the blade 2, and then rotate the locking safety 1 to the locking position, and the blade 2 is quickly assembled.

[0054] After being locked, the locking safety 1 forms a complete and mutually balanced force transmission path with the buttons 3 on both sides and the inclined surface on the upper part of the blade 2. Once the blade 2 rotates and generates a bending moment toward the middle on both sides, it will squeeze the buttons 3 on both sides to rotate toward the middle through the inclined surface, and then press against the two ends of the locking safety 1. Therefore, the entire structure itself forms a self-locking mode in the working state, which is tighter than the assembled quick-release structure that is not in the working rotation state, and is less likely to cause the middle locking safety 1 to accidentally loosen due to vibration factors. The greater the pulling force of the blade 2, the greater the clamping force on the locking safety 1, the more secure the locking, and the less likely it is to loosen due to vibration.

[0055] The distance between the position where the blade 2 and the propeller quick disassembly and assembly structure transmit the pulling force and the rotation center 401 of the blade 2 can be farther than that of the prior art solution, and the contact area can be larger. Farther means that the stress concentration problem at the root of the blade 2 in the prior art solution is reduced as much as possible for the force on the root of the blade 2. The aerodynamic force generated by the same outer section of the blade 2 is the same, which is like the principle of a lever. Since a button 3 farther from the center position can be set to press the inclined surface of the blade 2, in order to overcome the same bending moment relative to the center, the longer the lever distance, the smaller the force required. This is the biggest and most groundbreaking improvement of the present invention compared to the prior art solution.

[0056] The present invention is described by preferred embodiments, and those skilled in the art will appreciate that various changes or equivalent substitutions may be made to these features and embodiments without departing from the spirit and scope of the present invention. The present invention is not limited to the specific embodiments disclosed herein, and other embodiments falling within the claims of this application are within the scope of protection of the present invention. The present invention also has a variety of implementation methods, and all technical solutions formed by equivalent transformation or equivalent transformation fall within the scope of protection of the present invention.

Claims

1. A propeller quick disassembly and assembly structure, Features: It includes a locking safety, blades, a propeller hub, a button, and a base. The base can be installed on the motor front cover or integrated on the motor front cover of the propeller. The locking safety is provided with a first boss, and the button is provided with a first groove, wherein the first boss matches the first groove; An upper inclined surface and a lower inclined surface are provided on one side of the button. The upper inclined surface matches the upper mating surface of the propeller blade. The upper inclined surface can press the corresponding upper mating surface of the blade during the disassembly and assembly of the blade. The lower inclined surface matches the lower mating surface of the propeller blade. During the installation and ejection of the blade, the lower inclined surface of the button can realize the function of the button to be linked according to the lower mating surface through the up and down movement of the blade. The propeller hub is in the shape of a long strip. When the propeller blade is pressed down and fits to the base, the button is pressed against both ends of the propeller hub through the corresponding upper inclined surface or the lower inclined surface. A first rotating shaft hole is arranged on both sides of the base, and a button is arranged on both sides of the base. A second rotating shaft hole corresponding to the first rotating shaft hole is arranged on the button. The rotating shaft can pass through the first rotating shaft hole and the second rotating shaft hole. The button is limited on both sides of the base by the rotating shaft and can rotate freely within a set angle.

2. The propeller quick disassembly and assembly structure according to claim 1, Features: The upper mating surface of the blade is pressed against the button, and a corresponding opening is reserved for the button to pass through. There is a circular hole in the middle of the blade for fixing and allowing the locking safety to rotate in the mating position. Four spherical grooves are set on the platform in the middle of the blade to realize the positioning of the locked and unlocked positions with the spherical protrusion at the bottom of the locking safety.

3. The propeller quick disassembly and assembly structure according to claim 1, Features: A part of the locking safety is inserted into the middle hole in the middle of the blade. The locking safety and the blade are in an assembled state and will not be easily separated. When the blade and locking safety assembly is pressed into the base, the middle hole inside the rod extending from the lower part of the locking safety will be positioned and matched with the cylindrical boss in the middle of the base to ensure that the blade assembly and the motor base assembly are concentrically aligned.

4. The propeller quick disassembly and assembly structure according to claim 1, Features: An upward limiting boss is arranged on both sides of the base, and a downward limiting groove is arranged in the middle of the blade, and the limiting boss cooperates with the limiting groove in the middle of the blade.

5. The propeller quick disassembly and assembly structure according to claim 4, Features: The limiting boss is an oblong boss, and the limiting groove is an oblong hole groove.

6. The propeller quick disassembly and assembly structure according to claim 1, Features: The locking safety device is provided with a second boss near the center, and the blade is provided with a second groove matching the second boss, and the second boss can be locked in cooperation with the second groove.

7. The propeller quick disassembly and assembly structure according to claim 1, Features: A central circular boss is arranged at the center of the base, and a rod body middle hole matching the central circular boss is arranged at the lower part of the locking safety.

8. The propeller quick disassembly and assembly structure according to claim 1, Features: A flat contact positioning device is installed on the bottom plane of the hub of the blade and the upper surface of the base.

9. An aircraft provided with the propeller quick disassembly and assembly structure according to any one of claims 1 to 8, Features: It includes a propeller, a motor, and a propeller quick disassembly and assembly structure. The propeller includes blades and a hub. The hub is in a long strip shape, and the length direction is consistent with the center line direction of the propeller blades. The propeller quick disassembly and assembly structure includes a locking safety, a button, and a base. The base can be installed on the motor front cover or integrated on the propeller motor front cover. The propeller blade is provided with an upper mating surface and a lower mating surface near the propeller seat. The upper mating surface matches the upper inclined surface of the button, and the lower mating surface matches the lower inclined surface of the button. A first rotating shaft hole and a limiting boss are provided on both sides of the base, a limiting groove facing downward is provided in the middle of the blade, and the limiting boss cooperates with the limiting groove in the middle of the blade. Buttons are provided on both sides of the base, and a second rotating shaft hole corresponding to the first rotating shaft hole is provided on the button. The rotating shaft can pass through the first rotating shaft hole and the second rotating shaft hole. The button is limited on both sides of the base by the rotating shaft and can rotate freely within a set angle. A second boss is provided near the center position of the locking safety, and the blade is provided with a second groove matching the second boss, and the second boss can be locked by matching with the second groove; a central circular boss is provided at the center of the base, and a middle hole in the rod body matching the central circular boss is provided at the lower part of the locking safety.

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