Paddle locking device of engine

Abstract

The utility model discloses a propeller locking device of an engine, and relates to the technical field of aircrafts. The mounting seat is detachably connected to the engine, a first mounting hole is formed in the top of the mounting seat, a second mounting hole is formed in the side wall of the mounting seat, and a second bolt hole coaxially aligned with the second mounting hole is formed in the inner wall of the first mounting hole; one end of the sleeve extends into the first mounting hole, and a third mounting hole coaxially aligned with the second mounting hole is formed in the side wall of the sleeve; one end of the limiting piece extends into the sleeve, a fourth mounting hole coaxially aligned with the third mounting hole is formed in the side wall of the limiting piece, and a first bolt hole is formed in the other end of the limiting piece; and one end of the limiting bolt penetrates through the mounting hole of the propeller and is connected to the first bolt hole. The locking bolt forms a rigid connecting body through linkage constraint of the mounting base, the sleeve and the limiting piece, random swinging of the propeller in the transportation process is effectively avoided, the collision risk of the propeller and the inner wall of the box body is reduced, and the overall safety and reliability of the unmanned aerial vehicle are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a propeller locking device of an engine. BACKGROUND

[0002] In recent years, unmanned aerial vehicles (UAVs) have been widely used in aerial photography, logistics transportation, emergency rescue and other fields. With the expansion of its application range, the deployment efficiency and equipment reliability of the UAV have become key indicators to measure its performance.

[0003] Most of the current mainstream UAV launching systems adopt a design integrating box storage and launching. Under this design, the propeller of the UAV generally adopts a free-moving structure when the UAV is stored in the box. However, when the UAV encounters vibration or is rapidly launched during transportation, the unlocked propeller is prone to random swinging. Such swinging may cause the propeller to collide rigidly with the inner wall of the box, thereby causing the propeller to break. CONTENT OF THE UTILITY MODEL

[0004] The technical problem proposed in the background technology is solved by providing a propeller locking device of an engine.

[0005] The propeller locking device of the engine provided by the embodiment of the present application comprises a limiting piece, a sleeve, a mounting seat, a locking bolt and a limiting bolt. The mounting seat is detachably connected to the engine, the top of the mounting seat is provided with a first mounting hole, the side wall of the mounting seat is provided with a second mounting hole, the inner wall of the first mounting hole is provided with a second bolt hole coaxially aligned with the second mounting hole, one end of the sleeve extends into the first mounting hole, and the side wall of the sleeve is provided with a third mounting hole coaxially aligned with the second mounting hole. One end of the limiting piece extends into the sleeve, the side wall of the limiting piece is provided with a fourth mounting hole coaxially aligned with the third mounting hole, and the end of the limiting piece away from the mounting seat is provided with a first bolt hole. The first bolt hole is located above the sleeve, the limiting piece is made of a brittle fracture material, and the tensile strength of the limiting piece is lower than that of the sleeve and the mounting seat. One end of the limiting bolt passes through the mounting hole of the propeller and is connected to the first bolt hole. One end of the locking bolt passes through the second mounting hole, the third mounting hole and the fourth mounting hole in sequence and is threadedly connected to the second bolt hole. The part of the limiting piece extending out of the sleeve is a damage zone. When the engine speed reaches a preset threshold and the torque transmitted to the propeller exceeds the fracture strength of the limiting piece, the damage zone breaks in brittle fracture, thereby achieving automatic unlocking of the propeller.

[0006] In a possible implementation, the propeller locking device of the engine further comprises a pressing plate; a side wall of the mounting base is provided with a groove in communication with the first mounting hole; an outer wall of the pressing plate is provided with a second mounting hole, an inner wall of the pressing plate is provided with a first semicircular groove in abutment with an outer wall of the sleeve, and an inner wall of the first mounting hole is provided with a second semicircular groove matched with the first semicircular groove; and the pressing plate is in clearance fit with the groove.

[0007] In a possible implementation, a side wall of the limiting piece is provided with an annular boss; the damage zone is located above the annular boss in the axial direction; and a top wall of the sleeve is in abutment with a bottom wall of the annular boss.

[0008] In a possible implementation, the propeller locking device of the engine further comprises a plurality of fastening bolts; the engine is provided with a plurality of first connecting holes; the mounting base is provided with a plurality of second connecting holes corresponding to the first connecting holes; and one end of each of the fastening bolts sequentially passes through a corresponding second connecting hole and a first connecting hole.

[0009] In a possible implementation, a side wall of the damage zone is provided with a plurality of cracking holes in the circumferential direction, and the cracking holes are in communication with the first bolt hole.

[0010] In a possible implementation, a longitudinal section of the cracking hole is in a rectangular structure.

[0011] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0012] The propeller locking device of the engine provided by the application comprises a limiting piece, a sleeve, a mounting seat and a locking bolt. In the stationary state of the engine, the locking bolt is constrained through the linkage of the mounting seat, the sleeve and the limiting piece to form a rigid connection body, effectively avoiding the random swinging of the propeller during transportation. This not only reduces the risk of collision between the propeller and the inner wall of the box, but also significantly improves the overall safety and reliability of the unmanned aerial vehicle. The propeller locking device realizes the automation of locking and unlocking through a carefully designed linkage mechanism. After the engine starts, the output torque acts on the propeller through a specific path, and when the engine speed reaches a preset threshold, the limiting piece breaks under shear-torsional load, thereby releasing the locking constraint and allowing the propeller to enter a free rotation state. This process does not require human intervention, reducing the complexity of operation. Through the ingenious arrangement of the damage zone, the propeller locking device can effectively avoid damaging the high-speed rotating engine and propeller when the limiting piece is damaged. This design not only protects the key components of the unmanned aerial vehicle, but also prolongs the service life of the equipment. The propeller locking device does not require the intervention of an electric control system, thereby reducing the complexity of the system. This not only reduces the maintenance cost of the equipment, but also improves the overall reliability and stability. At the same time, since no additional electric control elements are required, the device has a significant advantage in cost. BRIEF DESCRIPTION OF DRAWINGS

[0013] In order to more clearly illustrate the technical solutions in the embodiments of the application, the following will briefly introduce the drawings needed to be used in the description of the embodiments of the application. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0014] Figure 1 The structure schematic diagram of the propeller locking device provided by the embodiments of the application is installed on the engine.

[0015] Figure 2 The structure schematic diagram of the propeller locking device provided by the embodiments of the application is installed on the engine.

[0016] Figure 3 The structure schematic diagram of the propeller locking device provided by the embodiments of the application is installed on the engine.

[0017] Figure 4 The structure schematic diagram of the propeller locking device provided by the embodiments of the application is installed on the engine.

[0018] Figure 5 The structure schematic diagram of the propeller locking device provided by the embodiments of the application is installed on the engine.

[0019] Figure 6 The structure schematic diagram of the propeller locking device provided by the embodiments of the application is installed on the engine.

[0020] Icon: 1-limiting piece; 11-first bolt hole; 12-fourth mounting hole; 13-crack hole; 2-sleeve; 21-third mounting hole; 3-mounting seat; 31-first mounting hole; 311-second bolt hole; 32-second mounting hole; 33-groove; 34-second connecting hole; 4-annular boss; 5-pressing piece; 6-engine; 7-propeller; 8-limiting bolt. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all 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 labor fall within the scope of protection of the present application.

[0022] In the description of the embodiments of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance. In addition, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication between 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.

[0023] The embodiments of the present application provide a propeller locking device of an engine, as shown in Figures 1 to 6As shown, the propeller locking device of the engine comprises a limiting piece 1, a sleeve 2, a mounting seat 3, a locking bolt and a limiting bolt 8. The mounting seat 3 is detachably connected to the engine 6, the top of which is provided with a first mounting hole 31, and the side wall of which is provided with a second mounting hole 32, and the inner wall of the first mounting hole 31 is provided with a second bolt hole 311 coaxially aligned with the second mounting hole 32. One end of the sleeve 2 extends into the first mounting hole 31, and the side wall of the sleeve 2 is provided with a third mounting hole 21 coaxially aligned with the second mounting hole 32. One end of the limiting piece 1 extends into the sleeve 2, and the side wall of the limiting piece 1 is provided with a fourth mounting hole 12 coaxially aligned with the third mounting hole 21, and the end of the limiting piece 1 away from the mounting seat 3 is provided with a first bolt hole 11. Among them, the first bolt hole 11 is located above the sleeve 2, the limiting piece 1 is a brittle fracture type material, and the tensile strength of the limiting piece 1 is lower than that of the sleeve 2 and the mounting seat 3. One end of the limiting bolt 8 passes through the mounting hole of the propeller 7 and is connected to the first bolt hole 11. One end of the locking bolt passes through the second mounting hole 32, the third mounting hole 21 and the fourth mounting hole 12 in sequence and is threadedly connected with the second bolt hole 311. The part of the limiting piece 1 extending out of the sleeve 2 is a damage zone, when the engine 6 reaches a preset threshold and the torque transmitted to the propeller 7 exceeds the fracture strength of the limiting piece 1, the damage zone occurs brittle fracture, realizing the automatic unlocking of the propeller 7.

[0024] The sleeve 2 also provides an additional protective barrier for the limiting piece 1. The sleeve 2 is located on the outer wall of the limiting piece 1, which can further protect the limiting piece 1 inside it. When the limiting piece 1 is damaged under certain conditions, the sleeve 2 can reduce the generation of debris, thereby effectively reducing the possibility of these fragments causing destructive effects on the high-speed rotating propeller 7. At the same time, the sleeve 2 can also play a positioning function for the limiting piece 1.

[0025] Specifically, in the manufacture of the limiting piece 1, various processing methods can be used, 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 materials, metal materials, and nylon plus glass fiber composite materials, nylon plus carbon fiber composite materials added for performance enhancement, etc.

[0026] It should be noted that in the engine 6 stationary state, the locking bolt is constrained through the linkage of the mounting seat 3, the sleeve 2 and the limiting piece 1, forming a rigid connection body, effectively avoiding the random swing of the propeller 7 during transportation. This not only reduces the risk of collision between the propeller 7 and the inner wall of the box, but also significantly improves the overall safety and reliability of the unmanned aerial vehicle. The propeller locking device realizes the automation of locking and unlocking through the carefully designed linkage mechanism. After the engine 6 starts, the output torque acts on the propeller 7 through a specific path, and when the engine 6 reaches the preset threshold, the limiting piece 1 breaks under shear-torsional load, thereby releasing the locking constraint and allowing the propeller 7 to enter the free rotation state. This process does not require human intervention, reducing the complexity of operation. Through the ingenious setting of the damage zone, the propeller locking device can effectively avoid damaging the high-speed rotating engine 6 and propeller 7 when the limiting piece 1 is damaged. This design not only protects the key components of the unmanned aerial vehicle, but also prolongs the service life of the equipment. The propeller locking device does not require the intervention of an electric control system, thereby reducing the complexity of the system. This not only reduces the maintenance cost of the equipment, but also improves the overall reliability and stability. At the same time, since no additional electric control elements are required, the device has a significant advantage in cost.

[0027] In the embodiments of the present application, the propeller locking device of the engine further includes a pressing piece 5. The side wall of the mounting seat 3 is provided with a groove 33 communicating with the first mounting hole 31. The outer wall of the pressing piece 5 is provided with a second mounting hole 32, the inner wall of the pressing piece 5 is provided with a first semicircular groove abutting the outer wall of the sleeve 2, and the inner wall of the first mounting hole 31 is provided with a second semicircular groove matched with the first semicircular groove. The pressing piece 5 is clearance fitted with the groove 33, and the pressing piece 5 is radially fixed with the sleeve 2 through the axial pressing force of the locking bolt. When the pressing piece 5 is installed in the groove 33, the clearance fit between the two ensures that the pressing piece 5 can stably press the sleeve 2, thereby enhancing the stability and reliability of the entire propeller locking device.

[0028] In the embodiments of the present application, the side wall of the limiting piece 1 is provided with an annular boss 4. The damage zone is located axially above the annular boss 4. The top wall of the sleeve 2 abuts the bottom wall of the annular boss 4.

[0029] Specifically, the annular boss 4 has a dual function. On the one hand, it can effectively divide the limiting piece 1 into a damage zone and a non-damage zone. During the locking process, if unlocking is required by damaging the limiting piece 1, the annular boss 4 can ensure that the damage force is concentrated in the damage zone, thereby protecting the non-damage zone intact and ensuring the normal operation of other parts of the propeller locking device. On the other hand, the annular boss 4 provides additional stability and support to the limiting piece 1 through close abutment with the top wall of the sleeve 2.

[0030] The application sets a layer of elastic material, such as rubber pad or spring sheet, between the bottom wall of the annular boss 4 and the top wall of the sleeve 2. This layer of elastic material can absorb vibration and impact force to a certain extent, further protecting the non-destructive area from damage.

[0031] In the embodiment of the application, the propeller locking device of the engine further comprises a plurality of fastening bolts. The engine 6 is provided with a plurality of first connecting holes. The mounting seat 3 is provided with a plurality of second connecting holes 34 corresponding to the first connecting holes. One end of the plurality of fastening bolts passes through the corresponding second connecting holes 34 and first connecting holes in sequence.

[0032] Specifically, the mounting seat 3 is provided with two second connecting holes 34, which perfectly match two corresponding first connecting holes on the engine 6. By passing one end of the fastening bolt through the two aligned second connecting holes 34 and first connecting holes, the engine 6 and the mounting seat 3 are firmly connected together.

[0033] In the embodiment of the application, the side wall of the destructive area is circumferentially provided with a plurality of cracking holes 13, which are in communication with the first bolt holes 11. The purpose of these cracking holes 13 is 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 orderly along the path of the cracking holes 13, rather than randomly spreading. This design ensures that the destruction is strictly limited within the designed destructive area, effectively avoiding unnecessary damage to the non-destructive area. The cracking holes 13 are in communication with the first bolt holes 11, forming a stress concentration area. When the stress reaches a certain degree, these areas will preferentially fail.

[0034] In the embodiment of the application, the longitudinal section of the cracking hole 13 is rectangular. The cracking hole 13 adopts a rectangular structure, which not only provides a larger failure area, accelerates the failure process, and thus improves the unlocking efficiency, but also exhibits higher processing feasibility and implementation convenience in the manufacturing process. The rectangular cracking hole 13 is easier to process and implement in the manufacturing process. In addition, this design also makes it more convenient to maintain and replace damaged parts, as the destructive area can be more easily identified and located.

[0035] The installation of the propeller locking device of the application can be extended to other types of power devices with propellers 7, such as small piston engines, clutch type piston engines and rotor engines.

[0036] Each embodiment in the specification is described in a progressive manner, and the same or similar parts between each embodiment can be referred to each other, and each embodiment mainly describes the difference from other embodiments.

[0037] The above examples are only used to illustrate the technical solutions of the present application, and are not intended to limit the present application; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that the technical solutions recorded in the foregoing examples can still be modified, or some or all of the technical features thereof can be replaced by equivalents; and 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 by The device comprises a limiting member (1), a sleeve (2), a mounting base (3), locking bolts and limiting bolts (8); The mounting base (3) is detachably connected to the engine (6), the top of which is provided with a first mounting hole (31), and the side wall of which is provided with a second mounting hole (32), the inner wall of the first mounting hole (31) is provided with a second bolt hole (311) coaxially aligned with the second mounting hole (32); One end of the sleeve (2) extends into the first mounting hole (31), and the side wall of the sleeve (2) is provided with a third mounting hole (21) coaxially aligned with the second mounting hole (32); One end of the limiting member (1) extends into the sleeve (2), and the side wall of the limiting member (1) is provided with a fourth mounting hole (12) coaxially aligned with the third mounting hole (21), and the end of the limiting member (1) away from the mounting base (3) is provided with a first bolt hole (11); wherein the first bolt hole (11) is located above the sleeve (2), the limiting member (1) is a brittle fracture type material, and the tensile strength of the limiting member (1) is lower than that of the sleeve (2) and the mounting base (3); One end of the limiting bolt (8) passes through the mounting hole of the propeller (7) and is connected to the first bolt hole (11); One end of the locking bolt passes through the second mounting hole (32), the third mounting hole (21), the fourth mounting hole (12) in sequence, and is threadedly connected with the second bolt hole (311); The part of the limiting member (1) extending out of the sleeve (2) is a damage zone, when the engine (6) reaches a preset threshold and the torque transmitted to the propeller (7) exceeds the fracture strength of the limiting member (1), the damage zone occurs brittle fracture, realizing the automatic unlocking of the propeller (7).

2. The lock propeller device of an engine according to claim 1, characterized by It also comprises a pressing plate (5); The side wall of the mounting base (3) is provided with a groove (33) in communication with the first mounting hole (31); The outer wall of the pressing plate (5) is provided with a second mounting hole (32), the inner wall of the pressing plate (5) is provided with a first semicircular groove matched with the outer wall of the sleeve (2), and the inner wall of the first mounting hole (31) is provided with a second semicircular groove matched with the first semicircular groove; The pressing plate (5) and the groove (33) are gap matched.

3. The lock propeller device of claim 1, wherein The side wall of the limiting member (1) is provided with an annular boss (4); The damage zone is located above the annular boss (4); The top wall of the sleeve (2) abuts against the bottom wall of the annular boss (4).

4. The lock propeller device of claim 1, wherein It also comprises a plurality of fastening bolts; The engine (6) is provided with a plurality of first connection holes; The mounting base (3) is provided with a plurality of second connection holes (34) corresponding to the first connection holes; One end of the plurality of fastening bolts passes through the corresponding second connection hole (34) and first connection hole in sequence.

5. The lock propeller device of claim 3, wherein A plurality of cracking holes (13) are arranged on the side wall of the damage zone in the circumferential direction, and the cracking holes (13) are in communication with the first bolt hole (11).

6. The lock propeller device of claim 5, wherein The longitudinal section of the cracking hole (13) is a rectangular structure.

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