A propeller locking device and method for an engine

Abstract

The present application discloses a propeller locking device and method for an engine, which relates to the technical field of aircraft. The sleeve is fixedly connected to the side of the first mounting seat away from the engine, and a notch is provided on the side wall of the sleeve; the first mounting seat is provided with a first mounting hole penetrating through the sleeve; a groove is provided on the inner wall of the first mounting hole, and the support member is slidably connected in the groove and partially extends into the first mounting hole; one end of the limiting member extends into the sleeve and abuts against the top surface of the support member, and the other end is provided with a bolt hole; one end of the limiting bolt passes through the mounting hole of the propeller and is connected to the bolt hole; the clamping mechanism is detachably connected to the end face of the engine output shaft and passes through the notch to clamp the limiting member; the side of the support member away from the groove is connected to the clamping mechanism. The present application effectively prevents the unintentional swing of the propeller during transportation, thereby reducing the risk of collision between the propeller and the inner wall of the box body, and ensuring the overall safety and reliability of the drone.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and particularly to a propeller locking device and method for an engine. Background Art

[0002] In recent years, the rapid development of unmanned aerial vehicle (UAV) technology has demonstrated great application potential and value in multiple fields such as aerial photography, logistics transportation, and emergency rescue. With the continuous maturity of UAV technology and the continuous expansion of its application scope, the deployment efficiency and equipment reliability of UAVs have become key indicators for measuring their comprehensive performance. Especially in scenarios such as emergency rescue and rapid deployment, the rapid and safe launch of UAVs is crucial.

[0003] Most current UAV launch systems adopt an integrated design scheme of box storage and launch. This design compactly stores the UAV in the launch box, which not only protects the UAV from external environmental interference but also facilitates rapid launch.

[0004] However, most existing propellers adopt a freely movable structure, that is, the propellers can rotate relatively freely in the storage state. Although this design simplifies the storage and launch process of UAVs to a certain extent, it brings new problems. When the UAV encounters vibration during transportation or undergoes rapid ejection, the unlocked propellers are prone to random swinging. This swinging may not only cause rigid collisions between the propellers and the inner wall of the box, resulting in propeller breakage, but also affect the overall structural stability and launch safety of the UAV. Summary of the Invention

[0005] The embodiments of this application solve the problems raised in the background art by providing a propeller locking device and method for an engine.

[0006] In a first aspect, an embodiment of the present application provides a propeller locking device for an engine, including a limiting member, a sleeve, a first mounting seat, a support member, a clamping mechanism, and a limiting bolt; the first mounting seat is detachably connected to the end face of the engine output shaft; the sleeve is fixedly connected to the side of the first mounting seat away from the engine, and a notch is provided on the side wall of the sleeve; the first mounting seat is provided with a first mounting hole penetrating through the sleeve; a groove is provided on the inner wall of the first mounting hole, and the support member is slidably connected in the groove and partially extends into the first mounting hole; one end of the limiting member extends into the sleeve and abuts against the top surface of the support member, and the other end is provided with a bolt hole; wherein, the bolt hole is located above the sleeve, and the limiting member is made of a brittle fracture type material, and its tensile strength is lower than that of the sleeve and the first mounting seat; one end of the limiting bolt passes through the mounting hole of the propeller and is connected to the bolt hole; the clamping mechanism is detachably connected to the end face of the engine output shaft and clamps the limiting member through the notch; the side of the support member away from the groove is connected to the clamping mechanism.

[0007] In combination with the first aspect, in a possible implementation manner, the clamping mechanism includes a locking member, a push rod, a second mounting seat, and a support table; the second mounting seat is detachably connected to the end face of the engine output shaft; the support table is provided on the side of the second mounting seat away from the engine and is provided with a threaded hole; the push rod is provided with an external thread matching the threaded hole, and one end of it passes through the threaded hole and is connected to the locking member; the locking member is arranged corresponding to the notch and is used for clamping the limiting member; the side of the support member away from the groove is connected to the locking member.

[0008] In combination with the first aspect, in a possible implementation manner, the clamping mechanism further includes an elastic layer; the elastic layer is provided on the side of the locking member away from the push rod.

[0009] In combination with the first aspect, in a possible implementation manner, the propeller locking device of the engine further includes a pushing member and a connecting member; the bottom wall of the locking member is lower than the bottom wall of the limiting member; one end of the connecting member is connected to the side of the locking member away from the push rod, and the other end is connected to the pushing member; the support member is connected to the side of the pushing member away from the connecting member; the side of the pushing member facing the locking member is a downward inclined surface, and the projection of the pushing member and the locking member in the vertical plane overlaps; when the locking member clamps the limiting member, the pushing member is partially located inside the limiting member, and its projection in the horizontal plane is located within the projection of the limiting member in the horizontal plane; when the locking member unlocks the limiting member, the locking member drives the pushing member to move away from the first mounting seat, and the inclined surface of the pushing member squeezes the limiting member, causing it to move away from the support member.

[0010] In combination with the first aspect, in a possible implementation manner, the propeller locking device of the engine further includes an annular boss; the annular boss is disposed on the outer wall of the limiting member; the top wall of the sleeve abuts against the bottom wall of the annular boss.

[0011] In combination with the first aspect, in a possible implementation manner, a plurality of cracking holes are circumferentially provided on the side wall of the limiting member, and the cracking holes communicate with the bolt holes.

[0012] In combination with the first aspect, in a possible implementation manner, the longitudinal section of the cracking hole is a rectangular structure.

[0013] In a second aspect, an embodiment of the present application provides a propeller locking method for an engine, including the propeller locking device of the engine in the first aspect or possible implementation manners of the first aspect. The method includes:

[0014] Detachably mount the first mounting seat to the end face of the engine output shaft;

[0015] Fix the sleeve to the side of the first mounting seat away from the engine;

[0016] Insert the limiting member into the sleeve, and support the limiting member through the supporting member;

[0017] Clamp and fix the limiting member through the clamping mechanism via the notch;

[0018] Align the mounting hole of the propeller with the bolt hole of the limiting member, and pass one end of the limiting bolt through the mounting hole of the propeller and connect it to the bolt hole of the limiting member to achieve propeller locking of the engine;

[0019] When the engine speed reaches the threshold and the torque transmitted to the propeller exceeds the fracture strength of the limiting member, the limiting member undergoes brittle fracture to achieve automatic unlocking of the propeller.

[0020] In combination with the second aspect, in a possible implementation manner, the method further includes:

[0021] A plurality of cracking holes are circumferentially provided on the side wall of the limiting member, and the cracking holes communicate with the bolt holes;

[0022] When the torque transmitted by the engine to the propeller exceeds the fracture strength of the limiting member, stress concentration occurs at the cracking holes, causing the limiting member to break along the cracking holes to form a plurality of separated fragments, achieving automatic unlocking of the propeller.

[0023] In combination with the second aspect, in a possible implementation manner, a centering device is used to align the mounting hole of the propeller with the bolt hole of the limiting member.

[0024] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0025] The propeller locking device of the engine provided in the embodiment of the present application includes a limiter, a sleeve, a first mounting seat, a support member, a clamping mechanism and a limiter bolt. When the engine is in a stationary state, the limiter bolt tightly connects the propeller and the limiter to form a stable rigid structure. At the same time, the clamping mechanism cleverly uses the notch to clamp the limiter, which not only enhances the reliability and stability of the connection, but also drives the support member to slide along the groove through its design and accurately limits the position of the support member. The support member partially extends into the first mounting hole to provide support for the limiter. Such a design not only constructs a stable and efficient torque transmission path, but also effectively prevents the propeller from unintentionally swinging during transportation, thereby reducing the risk of collision between the propeller and the inner wall of the box, and ensuring the overall safety and reliability of the drone.

[0026] Specifically, the setting of the sleeve also provides an additional protective barrier for the limiter. The sleeve is located on the outer wall of the limiter, which can further protect the limiter located inside it. When the limiter is damaged under certain conditions, the sleeve can reduce the generation of fragments, thereby effectively reducing the possibility of these fragments causing destructive effects on the high-speed rotating propeller. At the same time, the sleeve can also play a positioning function for the limiter.

[0027] Before the drone is safely placed in the box and ready to be launched, the propeller of the engine must be locked to ensure safety. This step is crucial because it can prevent the propeller from being damaged by accidental startup or vibration during transportation, ensuring that the drone is in a safe state before launch. When the engine starts and outputs torque, and the torque exceeds the preset safety threshold, the limiter will preferentially undergo brittle fracture because its tensile strength is lower than that of the sleeve and the first mounting seat. This fracture process is extremely fast and accurate, and can instantly cut off the torque transmission path, thereby effectively protecting the engine and propeller from potential damage. At the same time, after the drone is launched out of the box, the system will automatically release the lock state in a very short time to ensure that the propeller can quickly enter the working state and provide sufficient power for the drone's flight. Through such a precise and efficient lock and unlock mechanism, the drone can achieve fast and stable takeoff and flight while ensuring safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present application. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 Schematic structural diagram of the propeller locking device of the engine provided by the embodiment of the present application;

[0030] Figure 2 Schematic structural diagram of the sleeve provided by the embodiment of the present application;

[0031] Figure 3 Schematic structural diagram of the clamping mechanism provided by the embodiment of the present application;

[0032] Figure 4 Schematic structural diagram of the limiting member provided by the embodiment of the present application;

[0033] Figure 5 Schematic structural diagram of the limiting bolt provided by the embodiment of the present application;

[0034] Figure 6 Schematic structural diagram of the elastic layer provided by the embodiment of the present application.

[0035] Reference numerals: 1 - limiting member; 11 - bolt hole; 12 - annular boss; 13 - cracking hole; 2 - sleeve; 21 - notch; 3 - first mounting seat; 31 - first mounting hole; 32 - groove; 4 - support member; 5 - clamping mechanism; 51 - locking member; 52 - push rod; 53 - second mounting seat; 54 - support platform; 55 - turntable; 56 - elastic layer; 6 - limiting bolt; 7 - pushing member; 8 - connecting member; 9 - engine; 10 - propeller. Detailed implementation manners

[0036] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0037] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the embodiments of the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application. The terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance. In addition, the terms "mounted", "connected", "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0038] The embodiments of the present application provide a propeller locking device for an engine, as Figures 1 to 6 shown. The propeller locking device of the engine includes a limiting member 1, a sleeve 2, a first mounting seat 3, a support member 4, a clamping mechanism 5, and a limiting bolt 6. The first mounting seat 3 is detachably connected to the end face of the output shaft of the engine 9. The first mounting seat 3 and the hole positions on the engine 9 itself are connected by fasteners.

[0039] The sleeve 2 is fixedly connected to the side of the first mounting seat 3 away from the engine 9. A notch 21 is provided on the side wall of the sleeve 2. The first mounting seat 3 is provided with a first mounting hole 31 communicating with the sleeve 2. A groove 32 is provided on the inner wall of the first mounting hole 31. The support member 4 is slidably connected in the groove 32 and partially extends into the first mounting hole 31. One end of the limiting member 1 extends into the sleeve 2 and abuts against the top surface of the support member 4, and the other end is provided with a bolt hole 11. Wherein, the bolt hole 11 is located above the sleeve 2, and the limiting member 1 is made of a brittle fracture type material, and its tensile strength is lower than that of the sleeve 2 and the first mounting seat 3 made of conventional metal materials.

[0040] One end of the limiting bolt 6 passes through the mounting hole of the propeller 10 and is connected to the bolt hole 11. The clamping mechanism 5 is detachably connected to the end face of the output shaft of the engine 9 and passes through the notch 21 to clamp the limiting member 1. The side of the support member 4 away from the groove 32 is connected to the clamping mechanism 5. The groove 32 and the clamping mechanism 5 of the present application are arranged oppositely.

[0041] Specifically, when manufacturing the limiting member 1, various processing methods can be adopted, such as machining, laser cutting, etc. In terms of material selection, the present application also has a wide selection space, including but not limited to nylon-based materials, metal-based materials, and nylon plus glass fiber composite materials, nylon plus carbon fiber composite materials, etc. added to enhance performance.

[0042] It should be noted that when the engine 9 is in a stationary state, the limit bolt 6 tightly connects the propeller 10 and the limit member 1 together to form a stable rigid structure. At the same time, the clamping mechanism 5 cleverly uses the notch 21 to clamp the limit member 1, which not only enhances the reliability and stability of the connection, but also drives the support member 4 to slide along the groove 32 through its design, and accurately limits the position of the support member 4. The support member 4 partially extends into the first mounting hole 31, providing support for the limit member 1. Such a design not only constructs a stable and efficient torque transmission path, but also effectively prevents the propeller 10 from unintentionally swinging during transportation, thereby reducing the risk of collision between the propeller 10 and the inner wall of the box, ensuring the overall safety and reliability of the drone.

[0043] Specifically, the setting of the sleeve 2 also provides an additional protective barrier for the stopper 1. The sleeve 2 is located on the outer wall of the stopper 1, which can further protect the stopper 1 located inside it. When the stopper 1 is damaged under certain conditions, the sleeve 2 can reduce the generation of fragments, thereby effectively reducing the possibility of these fragments causing destructive effects on the high-speed rotating propeller 10. At the same time, the sleeve 2 can also play a positioning function for the stopper 1.

[0044] Before the drone is safely placed in the box and ready to be launched, the propeller 10 of the engine 9 must be locked to ensure safety. This step is crucial because it can prevent the propeller 10 from being damaged by accidental startup or vibration during transportation, ensuring that the drone is in a safe state before launch. When the engine 9 starts and outputs torque, and the torque exceeds the preset safety threshold, the limiter 1 will preferentially undergo brittle fracture due to its lower tensile strength than the sleeve 2 and the first mounting seat 3. This fracture process is extremely rapid and accurate, and can instantly cut off the torque transmission path, thereby effectively protecting the engine 9 and propeller 10 from potential damage. At the same time, after the drone is launched out of the box, the system will automatically release the locked propeller state in a very short time to ensure that the propeller 10 can quickly enter the working state and provide sufficient power for the flight of the drone. Through such a precise and efficient locking and unlocking mechanism, the drone can achieve fast and stable take-off and flight while ensuring safety.

[0045] In the embodiment of the present application, the clamping mechanism 5 includes a locking member 51, a push rod 52, a second mounting seat 53, and a support table 54. The second mounting seat 53 is detachably connected to the end face of the output shaft of the engine 9. The support table 54 is arranged on the side of the second mounting seat 53 away from the engine 9 and is provided with a threaded hole. The push rod 52 is provided with an external thread matching the threaded hole, and one end of the push rod 52 passes through the threaded hole and is connected to the locking member 51. The locking member 51 is arranged corresponding to the notch 21 and is used for clamping the limiting member 1. One side of the support member 4 away from the groove 32 is connected to the locking member 51.

[0046] It should be noted that the second mounting seat 53 is detachably connected to the mounting hole on the end face of the output shaft of the engine 9 through fasteners to achieve rapid installation and disassembly; when the push rod 52 is rotated, the external thread meshes with the threaded hole of the support table 54 to drive the push rod 52 to move along its axial direction; the locking member 51 at the front end of the push rod 52 moves with the push rod 52, contacts the limiting member 1 through the notch 21 of the sleeve 2, and applies a radial clamping force. When the locking member 51 clamps the limiting member 1, the support member 4 is pulled by the locking member 51 and slides along the groove 32 of the first mounting seat 3, so that the support member 4 always extends into the first mounting hole 31 to form a two-way constraint on the limiting member 1.

[0047] In the embodiment of the present application, the clamping mechanism 5 further includes a turntable 55. The turntable 55 is arranged at the end of the push rod 52 away from the locking member 51.

[0048] It should be noted that the operator can adjust the clamping force by rotating the turntable 55.

[0049] In the embodiment of the present application, the clamping mechanism 5 further includes an elastic layer 56. The elastic layer 56 is arranged on the side of the locking member 51 away from the push rod 52.

[0050] It should be noted that during the clamping process, the elastic layer 56 can absorb part of the impact force and vibration to prevent the limiting member 1 from being damaged. In addition, the elastic layer 56 can also compensate for machining errors or installation errors to a certain extent to ensure that the clamping mechanism 5 can closely fit the limited member 1.

[0051] In the embodiment of the present application, the propeller locking device of the engine further includes a pushing member 7 and a connecting member 8. The bottom wall of the locking member 51 is lower than the bottom wall of the limiting member 1. One end of the connecting member 8 is connected to the side of the locking member 51 away from the push rod 52, and the other end thereof is connected to the pushing member 7. The supporting member 4 is connected to the side of the pushing member 7 away from the connecting member 8. The side of the pushing member 7 facing the locking member 51 is a downward inclined surface, and the projection of the pushing member 7 and the locking member 51 in the vertical plane overlaps. When the locking member 51 clamps the limiting member 1, the pushing member 7 is partially located within the limiting member 1, and its projection in the horizontal plane is located within the projection of the limiting member 1 in the horizontal plane. When the locking member 51 unlocks the limiting member 1, the locking member 51 drives the pushing member 7 to move away from the first mounting seat 3, and the inclined surface of the pushing member 7 presses the limiting member 1 to move it away from the supporting member 4.

[0052] It should be noted that the bottom wall of the locking member 51 is designed to be lower than the bottom wall of the limiting member 1. This ingenious structure enables the locking member 51 to provide more stable support when clamping the limiting member 1, enhancing the reliability of locking. At the same time, the connecting member 8 tightly connects the locking member 51 and the pushing member 7, forming a stable and efficient locking system, further improving the locking performance.

[0053] When it is necessary to unlock the limiting member 1, the locking member 51 will smoothly drive the pushing member 7 to move away from the first mounting seat 3 together. Since the side of the pushing member 7 facing the locking member 51 is carefully designed as a downward inclined surface, this unique design enables the pushing member 7 to smoothly press the limiting member 1 during movement, pushing it to move away from the supporting member 4. This process not only makes the unlocking process smoother but also facilitates the operator to take out the unbroken limiting member 1, improving the convenience and efficiency of the operation.

[0054] In addition, the pushing member 7 is ingeniously partially located within the limiting member 1 during locking, and its projection in the horizontal plane is completely located within the projection of the limiting member 1 in the horizontal plane. This compact and reasonable structural design enables the locking member 51 to move out a certain distance first during the unlocking process, and then the pushing member 7 presses the limiting member 1, realizing a more stable and controllable unlocking process.

[0055] In the embodiment of the present application, the propeller locking device of the engine further includes an annular boss 12. The annular boss 12 is provided on the outer wall of the limiting member 1. The top wall of the sleeve 2 abuts against the bottom wall of the annular boss 12.

[0056] It should be noted that the design of the annular boss 12 has dual functions. On the one hand, it can effectively divide the limiting member 1 into a damage area and a non-damage area. During the locking process, if it is necessary to unlock by damaging the limiting member 1, the annular boss 12 can ensure that the destructive force is concentrated in the damage area, thus protecting the non-damage area intact and ensuring the normal operation of other parts of the paddle locking device. On the other hand, the annular boss 12 provides additional stability and support for the limiting member 1 by tightly abutting against the top wall of the sleeve 2.

[0057] In the embodiment of the present application, a plurality of cracking holes 13 are circumferentially arranged on the side wall of the limiting member 1, and the cracking holes 13 communicate with the bolt holes 11.

[0058] It should be noted that the arrangement of the plurality of cracking holes 13 is designed to guide the damage to occur in a predetermined direction. When the external force or internal stress exceeds the bearing limit of the material, the damage will occur orderly along the path of the cracking holes 13 instead of spreading randomly. This design ensures that the damage is strictly limited to the designed damage area, thus effectively avoiding unnecessary damage to the non-damage area. The cracking holes 13 are connected to the bolt holes 11 to form a stress concentration area. When the stress reaches a certain level, damage will occur preferentially in these areas.

[0059] In the embodiment of the present application, the longitudinal section of the cracking hole 13 is a rectangular structure.

[0060] It should be noted that the cracking hole 13 adopts a rectangular structure. This design not only provides a larger damage area, accelerates the damage process, thereby improving the unlocking efficiency, but also shows higher processing feasibility and implementation convenience during the manufacturing process. The rectangular-structured cracking hole 13 is easier to process and implement during the manufacturing process. In addition, this design also makes it more convenient for maintenance and replacement of damaged parts because the damage area can be more easily identified and located.

[0061] The embodiment of the present application provides a paddle locking method for an engine, including the paddle locking device of the engine described above. The method includes the following steps:

[0062] S1: Detachably mount the first mounting seat 3 to the end face of the output shaft of the engine 9.

[0063] S2: Fix the sleeve 2 to the side of the first mounting seat 3 away from the engine 9.

[0064] S3: Insert the limiting member 1 into the sleeve 2 and support the limiting member 1 through the support member 4.

[0065] S4: Clamp and fix the limiting member 1 through the clamping mechanism 5 via the notch 21.

[0066] S5: Align the mounting holes of the propeller 10 with the bolt holes 11 of the limiting member 1, and pass one end of the limiting bolt 6 through the mounting holes of the propeller 10 and connect it to the bolt holes 11 of the limiting member 1 to lock the propeller of the engine 9.

[0067] S6: When the rotational speed of the engine 9 reaches the threshold and the torque transmitted to the propeller 10 exceeds the fracture strength of the limiting member 1, the limiting member 1 undergoes brittle fracture to achieve automatic unlocking of the propeller 10.

[0068] It should be noted that the installation design of this application makes excellent use of the existing characteristics of the engine 9 body structure and the propeller 10 mounting structure, ensuring the perfect integration of the propeller locking device with the engine 9 and the propeller 10. The propeller locking method is designed simply and clearly, with convenient operation and high reliability. Its core principle lies in the ingenious use of the brittle fracture characteristics of the limiting member 1. By precisely controlling the fracture strength of the limiting member 1, this propeller locking method realizes the flexible switching between the propeller locking and unlocking functions.

[0069] In addition, this propeller locking method has excellent versatility and adaptability, and can be widely applied to various types of engines 9 and propellers 10. In practical applications, only by adjusting the fracture strength of the limiting member 1 and the clamping force of the clamping mechanism 5 according to specific requirements, it is possible to easily meet the usage requirements in different scenarios, showing extremely high flexibility and practicality.

[0070] In the embodiment of this application, the method further includes the following steps:

[0071] S7: A plurality of cracking holes 13 are circumferentially arranged on the side wall of the limiting member 1, and the cracking holes 13 are communicated with the bolt holes 11.

[0072] When the torque transmitted from the engine 9 to the propeller 10 exceeds the fracture strength of the limiting member 1, stress concentration occurs at the cracking holes 13, causing the limiting member 1 to break along the cracking holes 13, forming a plurality of separated fragments. This process not only realizes the automatic unlocking of the propeller 10, but also effectively reduces the risk of having a destructive impact on the high-speed rotating propeller 10 during the fracture process.

[0073] It should be noted that the design of the cracking holes 13 enables the limiting member 1 to break quickly and accurately when reaching the fracture strength, thereby improving the unlocking efficiency of the propeller 10. By guiding the limiting member 1 to break along the cracking holes 13, the potential destructive impact of the fragments on the propeller 10 and surrounding components is reduced, protecting the overall structures of the engine 9 and the propeller 10.

[0074] In the embodiment of this application, a centering device is used to align the mounting holes of the propeller 10 with the bolt holes 11 of the limiting member 1.

[0075] Specifically, the centering device includes a first permanent magnet and a second permanent magnet. The first permanent magnet is placed on the top surface of the limiting member 1, and its magnetic field distribution presents an annular characteristic; while a second permanent magnet with a polarity opposite to that of the first permanent magnet is arranged around the mounting hole of the propeller 10. During the installation process, the first permanent magnet and the second permanent magnet automatically guide the propeller 10 to rotate to a position coaxial with the limiting member 1 by virtue of a strong magnetic attraction force, thereby realizing the precise automatic centering of the bolt hole 11. Once the mounting hole is perfectly centered with the bolt hole 11, the operator can easily remove the first permanent magnet and the second permanent magnet, facilitating the subsequent connection operation of the limiting bolt 6. This application cleverly uses magnetic force guiding technology to achieve automatic centering, significantly reducing the error of manual alignment and greatly improving the installation accuracy and reliability.

[0076] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, reference can be made to each other, and the key points of each embodiment are the differences from other embodiments.

[0077] The above embodiments are only used to illustrate the technical solutions of the present application, rather than limiting the present application; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. A propeller locking device for an engine, characterized in that: It comprises a limiting member (1), a sleeve (2), a first mounting seat (3), a supporting member (4), a clamping mechanism (5) and a limiting bolt (6); The first mounting seat (3) is detachably connected to the end face of the output shaft of the engine (9); The sleeve (2) is fixedly connected to a side of the first mounting seat (3) away from the engine (9), and a side wall of the sleeve (2) is provided with a notch (21); the first mounting seat (3) is provided with a first mounting hole (31) penetrating the sleeve (2); The inner wall of the first mounting hole (31) is provided with a groove (32), and the support member (4) is slidably connected in the groove (32) and partially extends into the first mounting hole (31); One end of the stopper (1) extends into the sleeve (2) and abuts against the top surface of the support member (4), and the other end is provided with a bolt hole (11); wherein the bolt hole (11) is located above the sleeve (2), and the stopper (1) is made of a brittle fracture type material, and its tensile strength is lower than the tensile strength of the sleeve (2) and the first mounting seat (3); One end of the limiting bolt (6) passes through the mounting hole of the propeller (10) and is connected to the bolt hole (11); The clamping mechanism (5) is detachably connected to the end surface of the output shaft of the engine (9), and passes through the notch (21) to clamp the limiting member (1); The side of the support member (4) away from the groove (32) is connected to the clamping mechanism (5).

2. The engine propeller locking device according to claim 1, characterized in that: The clamping mechanism (5) comprises a locking member (51), a push rod (52), a second mounting seat (53) and a support platform (54); The second mounting seat (53) is detachably connected to the end surface of the output shaft of the engine (9); The support platform (54) is arranged on a side of the second mounting seat (53) away from the engine (9), and is provided with a threaded hole; The push rod (52) is provided with an external thread matching the threaded hole, and one end thereof passes through the threaded hole and is connected to the locking member (51); The locking member (51) is arranged corresponding to the notch (21) and is used to clamp the limiting member (1); The side of the support member (4) away from the groove (32) is connected to the locking member (51).

3. The engine propeller locking device according to claim 2, characterized in that: The clamping mechanism (5) further comprises an elastic layer (56); The elastic layer (56) is arranged on a side of the locking member (51) away from the push rod (52).

4. The engine propeller locking device according to claim 2, characterized in that: It also includes a push piece (7) and a connecting piece (8); The bottom wall of the locking member (51) is lower than the bottom wall of the limiting member (1); One end of the connecting member (8) is connected to a side of the locking member (51) away from the push rod (52), and the other end is connected to the pushing member (7); The support member (4) is connected to a side of the pushing member (7) away from the connecting member (8); The side of the pushing member (7) facing the locking member (51) is a downwardly inclined surface, and the projections of the pushing member (7) and the locking member (51) on the vertical plane overlap; When the locking member (51) clamps the limiting member (1), the pushing member (7) is partially located inside the limiting member (1), and its projection on the horizontal plane is located inside the projection of the limiting member (1) on the horizontal plane; when the locking member (51) unlocks the limiting member (1), the locking member (51) moves the pushing member (7) in a direction away from the first mounting seat (3), and the inclined surface of the pushing member (7) presses the limiting member (1) to move it in a direction away from the supporting member (4).

5. The engine propeller locking device according to claim 1, characterized in that: Also includes an annular boss (12); The annular boss (12) is arranged on the outer wall of the limiting member (1); The top wall of the sleeve (2) abuts against the bottom wall of the annular boss (12).

6. The engine propeller locking device according to claim 1, characterized in that: A plurality of crack holes (13) are arranged in the circumferential direction of the side wall of the limiting member (1), and the crack holes (13) are connected to the bolt holes (11).

7. The propeller locking device of the engine according to claim 6, characterized in that: The longitudinal section of the crack hole (13) is a rectangular structure.

8. A method for locking a propeller of an engine, characterized in that: A propeller locking device for an engine comprising any one of claims 1 to 7, wherein the method comprises: Removably mounting the first mounting seat (3) on the end face of the output shaft of the engine (9); The sleeve (2) is fixedly connected to a side of the first mounting seat (3) away from the engine (9); Inserting the limiting member (1) into the sleeve (2), and supporting the limiting member (1) by means of a supporting member (4); The limiting member (1) is clamped and fixed via the notch (21) by means of a clamping mechanism (5); Align the mounting hole of the propeller (10) with the bolt hole (11) of the limiting member (1), and pass one end of the limiting bolt (6) through the mounting hole of the propeller (10) and connect it to the bolt hole (11) of the limiting member (1), so as to achieve the locking of the propeller of the engine (9); When the rotation speed of the engine (9) reaches a threshold value and the torque transmitted to the propeller (10) exceeds the fracture strength of the limiter (1), the limiter (1) undergoes brittle fracture, thereby achieving automatic unlocking of the propeller (10).

9. The engine propeller locking method according to claim 8, characterized in that: Also includes: A plurality of crack holes (13) are arranged in the circumferential direction of the side wall of the limiting member (1), and the crack holes (13) are connected to the bolt holes (11); When the torque transmitted from the engine (9) to the propeller (10) exceeds the breaking strength of the stopper (1), stress concentration is generated at the crack hole (13), causing the stopper (1) to break along the crack hole (13) to form a plurality of separated fragments, thereby achieving automatic unlocking of the propeller (10).

10. The engine propeller locking method according to claim 8, characterized in that: The mounting hole of the propeller (10) is aligned with the bolt hole (11) of the limiting member (1) using a centering device.

Images