Paddle locking device and method of engine

Abstract

The invention discloses a propeller locking device and method of an engine, and relates to the technical field of aircrafts. The sleeve is fixedly connected to the side, away from the engine, of the first mounting base, and a notch is formed in the side wall of the sleeve; the first mounting seat is provided with a first mounting hole communicated with the sleeve; a groove is formed in the inner wall of the first mounting hole, and the supporting piece is connected into the groove in a sliding mode and partially extends into the first mounting hole; one end of the limiting piece extends into the sleeve and abuts against the top face of the supporting piece, and a bolt hole is formed in the other end of the limiting piece. One end of the limiting bolt penetrates 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 output shaft of the engine and penetrates through the notch to clamp the limiting piece. The side, away from the groove, of the supporting piece is connected to the clamping mechanism. According to the unmanned aerial vehicle, unintentional swinging of the propeller in the transportation process is effectively prevented, so that the risk that the propeller collides with the inner wall of the box body is reduced, and the overall safety and reliability of the unmanned aerial vehicle are ensured.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to a propeller locking device and method for an engine. Background Art

[0002] In recent years, the rapid development of drone technology has enabled it to demonstrate great application potential and value in many fields such as aerial photography, logistics and transportation, and emergency rescue. As drone technology continues to mature and its application scope continues to expand, the deployment efficiency and equipment reliability of drones have become key indicators for measuring their comprehensive performance. In particular, in scenarios such as emergency rescue and rapid deployment, the rapid and safe launch of drones is crucial.

[0003] Most current drone launch systems use a box-type storage and launch integrated design. This design stores the drone compactly in the launch box, which not only protects the drone from interference from the external environment, but also facilitates rapid launch.

[0004] However, most existing propellers adopt a free-moving structure, that is, the propeller can rotate relatively freely in the storage state. Although this design simplifies the storage and launch process of the drone to a certain extent, it brings new problems. When the drone encounters vibration during transportation, or when it is ejected rapidly, the unlocked propeller is prone to random swinging. This swing may not only cause the propeller to rigidly collide with the inner wall of the box, thereby causing the propeller to break, but may also affect the overall structural stability and launch safety of the drone. Summary of the invention

[0005] The embodiments of the present application solve the problems raised by the background technology 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, comprising 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 a side of the first mounting seat away from the engine, and a notch is provided on a side wall of the sleeve; the first mounting seat is provided with a first mounting hole that passes through the sleeve; the inner wall of the first mounting hole is provided with a groove, and the support member is slidably connected to the groove and partially extends into the first mounting hole; One end of the limit 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 limit member is made of a brittle fracture type material, and its tensile strength is lower than the tensile strength of the sleeve and the first mounting seat; one end of the limit 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 limit member; 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, the clamping mechanism includes a locking piece, a push rod, a second mounting seat and a support platform; the second mounting seat is detachably connected to the end face of the engine output shaft; the support platform is arranged 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, one end of which passes through the threaded hole and is connected to the locking piece; the locking piece is arranged corresponding to the notch, and is used to clamp the limit piece; the side of the support piece away from the groove is connected to the locking piece.

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

[0009] In combination with the first aspect, in a possible implementation, the propeller locking device of the engine also includes a push piece and a connecting piece; the bottom wall of the locking piece is lower than the bottom wall of the limiting piece; one end of the connecting piece is connected to the side of the locking piece away from the push rod, and the other end thereof is connected to the push piece; the support piece is connected to the side of the push piece away from the connecting piece; the side of the push piece facing the locking piece is a downward inclined surface, and the projection of the push piece and the locking piece in the vertical plane overlap; when the locking piece clamps the limiting piece, the push piece is partially located in the limiting piece, and its projection in the horizontal plane is located in the projection of the limiting piece in the horizontal plane; when the locking piece unlocks the limiting piece, the locking piece moves with the push piece in the direction away from the first mounting seat, and the inclined surface of the push piece squeezes the limiting piece to make it move in the direction away from the support piece.

[0010] In combination with the first aspect, in a possible implementation, the propeller locking device of the engine also includes an annular boss; the annular boss is arranged on the outer wall of the limiting member; and 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 crack holes are provided in a circumferential direction of a side wall of the limiting member, and the crack holes are connected to the bolt holes.

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

[0013] In a second aspect, an embodiment of the present application provides a method for locking a propeller of an engine, including the engine locking propeller device in the first aspect or a possible implementation of the first aspect, the method comprising: Removably mounting the first mounting seat on the end face of the engine output shaft; The sleeve is fixedly connected to a side of the first mounting base away from the engine; Inserting the limiting member into the sleeve and supporting the limiting member by the supporting member; The limiting member is clamped and fixed through the notch by a clamping mechanism; 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; When the engine speed reaches a threshold and the torque transmitted to the propeller exceeds the fracture strength of the limiter, the limiter undergoes brittle fracture, thereby achieving automatic unlocking of the propeller.

[0014] In conjunction with the second aspect, in a possible implementation manner, the method further includes: A plurality of crack holes are arranged in the circumferential direction of the side wall of the limiting member, and the crack holes are connected with the bolt holes; When the torque transmitted from the engine to the propeller exceeds the breaking strength of the limiter, stress concentration occurs at the crack hole, causing the limiter to break along the crack hole to form multiple separated fragments, thereby achieving automatic unlocking of the propeller.

[0015] 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.

[0016] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects: 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.

[0017] 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.

[0018] 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

[0019] 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.

[0020] Figure 1A schematic diagram of the structure of a propeller locking device of an engine provided in an embodiment of the present application; Figure 2 A schematic diagram of the structure of the sleeve provided in an embodiment of the present application; Figure 3 A schematic diagram of the structure of the clamping mechanism provided in an embodiment of the present application; Figure 4 A schematic diagram of the structure of the limiter provided in the embodiment of the present application; Figure 5 A schematic diagram of the structure of the limit bolt provided in the embodiment of the present application; Figure 6 A schematic diagram of the structure of the elastic layer provided in an embodiment of the present application.

[0021] Icons: 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-thrust member; 8-connecting member; 9-engine; 10-propeller. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0023] In the description of the embodiments of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. is based on the orientation or positional relationship shown in the drawings, and 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, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" 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 a direct connection, or it can be indirectly connected through an intermediate medium, or it can be a connection between the 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 the specific circumstances.

[0024] The present application embodiment provides a propeller locking device for an engine, such as Figures 1 to 6 As shown. The propeller locking device of the engine includes a limiter 1, a sleeve 2, a first mounting seat 3, a support member 4, a clamping mechanism 5 and a limiter 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 is connected to the hole position on the engine 9 itself through a fastener.

[0025] The sleeve 2 is fixedly connected to the side of the first mounting seat 3 away from the engine 9, and the 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 that penetrates 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 limiter 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. Among them, the bolt hole 11 is located above the sleeve 2, and the limiter 1 is 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.

[0026] One end of the limit 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 limit 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 relative to each other.

[0027] Specifically, when manufacturing the stopper 1, a variety of processing methods can be used, such as machining, laser cutting, etc. In terms of material selection, the present application also has a wide range of choices, including but not limited to nylon materials, metal materials, and nylon plus glass fiber composite materials, nylon plus carbon fiber composite materials, etc. added to enhance performance.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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 platform 54. The second mounting seat 53 is detachably connected to the end face of the output shaft of the engine 9. The support platform 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, one end of which 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 limit member 1. The side of the support member 4 away from the groove 32 is connected to the locking member 51.

[0032] 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 by fasteners, so as to realize quick installation and disassembly; when the push rod 52 is rotated, the external thread engages with the threaded hole of the support platform 54, driving the push rod 52 to move along its axial direction; the locking piece 51 at the front end of the push rod 52 moves with the push rod 52, contacts the limit piece 1 through the notch 21 of the sleeve 2, and applies a radial clamping force. When the locking piece 51 clamps the limit piece 1, the support piece 4 is pulled by the locking piece 51 and slides along the groove 32 of the first mounting seat 3, so that the support piece 4 always extends into the first mounting hole 31, forming a bidirectional constraint on the limit piece 1.

[0033] In the embodiment of the present application, the clamping mechanism 5 further includes a turntable 55 . The turntable 55 is disposed at one end of the push rod 52 away from the locking member 51 .

[0034] It should be noted that the operator can adjust the clamping force by rotating the turntable 55 .

[0035] In the embodiment of the present application, the clamping mechanism 5 further includes an elastic layer 56. The elastic layer 56 is disposed on a side of the locking member 51 away from the push rod 52.

[0036] It should be noted that during the clamping process, the elastic layer 56 can absorb some impact and vibration to prevent damage to the stopper 1. In addition, the elastic layer 56 can also compensate for processing errors or installation errors to a certain extent to ensure that the clamping mechanism 5 can fit the stopper 1 tightly.

[0037] In the embodiment of the present application, the propeller locking device of the engine also includes a push 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 push member 7. The support member 4 is connected to the side of the push member 7 away from the connecting member 8. The side of the push member 7 facing the locking member 51 is a downward inclined surface, and the projections of the push member 7 and the locking member 51 on the vertical plane overlap. When the locking member 51 clamps the limiting member 1, the push member 7 is partially located in the limiting member 1, and its projection on the horizontal plane is located in 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 with the push member 7 in the direction away from the first mounting seat 3, and the inclined surface of the push member 7 squeezes the limiting member 1 to make it move in the direction away from the support member 4.

[0038] 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, thereby 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.

[0039] When the limiting member 1 needs to be unlocked, the locking member 51 will smoothly move the pushing member 7 together in the direction away from the first mounting seat 3. 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 squeeze the limiting member 1 during the movement process, pushing it to move in the direction 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, thereby improving the convenience and efficiency of the operation.

[0040] In addition, the push member 7 is partially located in the limiter 1 when locked, and its projection on the horizontal plane is completely located within the projection on the horizontal plane of the limiter 1. This compact and reasonable structural design allows the locking member 51 to move out a certain distance during the unlocking process, and then the push member 7 squeezes the limiter 1, achieving a more stable and controllable unlocking process.

[0041] 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 arranged on the outer wall of the stopper 1. The top wall of the sleeve 2 abuts against the bottom wall of the annular boss 12.

[0042] It should be noted that the design of the annular boss 12 has a dual function. On the one hand, it can effectively divide the limiter 1 into a destructive zone and a non-destructive zone. During the locking process, if it is necessary to unlock by destroying the limiter 1, the annular boss 12 can ensure that the destructive force is concentrated in the destructive zone, thereby protecting the non-destructive zone intact and ensuring the normal operation of other parts of the propeller locking device. On the other hand, the annular boss 12 provides additional stability and support for the limiter 1 by tightly abutting against the top wall of the sleeve 2.

[0043] In the embodiment of the present application, 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 .

[0044] It should be noted that the setting of multiple crack holes 13 is intended to guide the destruction in a predetermined direction. When the external force or internal stress exceeds the bearing limit of the material, the destruction will occur in an orderly manner along the path of the crack holes 13 rather than spreading randomly. This design ensures that the destruction is strictly limited to the designed destruction zone, thereby effectively avoiding unnecessary damage to the non-destructive zone. The crack holes 13 are connected to the bolt holes 11, forming a stress concentration area. When the stress reaches a certain level, these areas will be destroyed first.

[0045] In the embodiment of the present application, the longitudinal section of the crack hole 13 is a rectangular structure.

[0046] 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, and thus improves the unlocking efficiency, but also shows higher processing feasibility and convenience in the manufacturing process. The cracking hole 13 with a rectangular structure is easier to process and realize during the manufacturing process. In addition, this design also makes it more convenient to maintain and replace damaged parts because the damage area can be more easily identified and located.

[0047] The embodiment of the present application provides a method for locking a propeller of an engine, including the above-mentioned engine locking propeller device, and the method includes the following steps: S1: detachably mount the first mounting seat 3 to the end face of the output shaft of the engine 9 .

[0048] S2: The sleeve 2 is fixedly connected to a side of the first mounting seat 3 away from the engine 9 .

[0049] S3: insert the limiting member 1 into the sleeve 2 and support the limiting member 1 through the supporting member 4.

[0050] S4: The limiting member 1 is clamped and fixed through the notch 21 by the clamping mechanism 5 .

[0051] S5: 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 to achieve propeller locking of the engine 9.

[0052] S6: When the speed of the engine 9 reaches a threshold and the torque transmitted to the propeller 10 exceeds the fracture strength of the stopper 1, the stopper 1 undergoes brittle fracture, thereby achieving automatic unlocking of the propeller 10.

[0053] It should be noted that the installation design of the present application ingeniously maximizes the existing characteristics of the engine 9 body structure and the propeller 10 installation structure, ensuring the perfect integration of the propeller locking device with the engine 9 and the propeller 10. The propeller locking method is concise and clear in design, easy to operate, and highly reliable. Its core principle is to cleverly use the brittle fracture characteristics of the limiter 1. By accurately controlling the fracture strength of the limiter 1, the propeller locking method realizes the flexible switching of the propeller locking and unlocking functions.

[0054] In addition, the 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, it is only necessary to adjust the breaking strength of the limiter 1 and the clamping force of the clamping mechanism 5 according to specific needs, so as to easily meet the use requirements in different scenarios, showing extremely high flexibility and practicality.

[0055] In the embodiment of the present application, the method further comprises the following steps: S7: A plurality of crack holes 13 are provided in the circumferential direction of the side wall of the stopper 1 , and the crack holes 13 are connected to the bolt holes 11 .

[0056] When the torque transmitted from the engine 9 to the propeller 10 exceeds the fracture strength of the stopper 1, stress concentration occurs at the crack hole 13, causing the stopper 1 to break along the crack hole 13 to form a plurality of separated fragments. This process not only realizes the automatic unlocking of the propeller 10, but also effectively reduces the risk of destructive effects on the high-speed rotating propeller 10 during the fracture process.

[0057] It should be noted that the design of the crack hole 13 enables the stopper 1 to break quickly and accurately when the breaking strength is reached, thereby improving the unlocking efficiency of the propeller 10. By guiding the stopper 1 to break along the crack hole 13, the potential destructive effect of the fragments on the propeller 10 and surrounding components is reduced, and the overall structure of the engine 9 and the propeller 10 is protected.

[0058] In the embodiment of the present application, a centering device is used to align the mounting hole of the propeller 10 with the bolt hole 11 of the limiting member 1 .

[0059] 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 limiter 1, and its magnetic field distribution presents an annular characteristic; and 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 limiter 1 by virtue of their strong magnetic attraction, thereby realizing accurate automatic centering of the bolt hole 11. Once the mounting hole is perfectly aligned with the bolt hole 11, the operator can easily remove the first permanent magnet and the second permanent magnet, which facilitates the subsequent connection operation of the limit bolt 6. The present application cleverly uses magnetic guidance technology to achieve automatic centering, significantly reduces the error of manual alignment, and greatly improves the accuracy and reliability of installation.

[0060] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0061] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to 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 the 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.

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