A kind of tool for disassembling engine tappet of unmanned aerial vehicle

Abstract

This application discloses a tooling for disassembling drone engine tappets, relating to the field of drone technology. The tooling includes a valve compression assembly and a disassembly assembly. The valve compression assembly includes a compression plate for compressing valve springs, and the disassembly assembly includes a disassembly shaft for disassembling rocker arm shafts. The tooling for disassembling drone engine tappets can reduce the number of manual workers required to disassemble engine tappets and reduce disassembly time, thereby improving disassembly efficiency.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a tooling suitable for disassembling UAV engine tappets. Background Technology

[0002] Engine tappets (also known as valve lifters or tappets) are key components of the valve train in piston engines, responsible for transmitting the movement of the camshaft to the valves. Their working condition directly affects engine performance and lifespan. Removing engine tappets (valve lifters / tapered rods) is an important step in engine maintenance and requires careful handling to avoid damaging parts or affecting assembly accuracy.

[0003] In existing technologies, disassembling engine tappets requires multiple tools and the cooperation of multiple people, making the disassembly process time-consuming and labor-intensive, resulting in low production efficiency. Utility Model Content

[0004] The purpose of this application is to provide a tooling suitable for removing unmanned aerial vehicle (UAV) engine tappets, which enables convenient and quick removal of engine tappets.

[0005] To achieve the above objectives, this application provides a tooling for disassembling tappets of unmanned aerial vehicle engines, comprising: a valve compression assembly and a disassembly assembly;

[0006] The valve compression assembly includes a compression plate for compressing the valve springs of the engine.

[0007] The disassembly assembly includes a disassembly shaft for disassembling the rocker arm shaft.

[0008] In some embodiments, a first mounting base and a second mounting base are provided, the compression plate is disposed on the first mounting base, the rocker arm shaft is disposed on the second mounting base, and the first mounting base is connected to the second mounting base.

[0009] In some embodiments, a lead screw is provided between the compression plate and the first mounting base, the lead screw is threadedly engaged with the first mounting base, and the end of the lead screw is rotatably connected to the compression plate.

[0010] In some embodiments, the compression plate is provided with a slot that can engage with a protrusion of the engine valve spring.

[0011] In some embodiments, the second mounting base is provided with a connecting hole, and the first mounting base is provided with a through hole. A fixing screw is threaded into the through hole, and the fixing screw can extend into the connecting hole and threadedly engage with the connecting hole to achieve a detachable connection between the first mounting base and the second mounting base.

[0012] In some embodiments, the outer diameter of the fixing screw is the same as the inner diameter of the engine housing mounting hole, and the fixing screw can extend into the engine housing mounting hole.

[0013] In some embodiments, the end of the disassembly shaft is provided with a disassembly screw, the sidewall of the disassembly shaft is threaded, the disassembly shaft is threadedly engaged with the second mounting seat, and is movable relative to the second mounting seat along its axial direction.

[0014] In some embodiments, the second mounting base is provided with a hollowed-out groove.

[0015] In some embodiments, the lead screw is provided with a first limiting member, which can abut against the first mounting base.

[0016] In some embodiments, the disassembly shaft is provided with a second limiting member, which can abut against the second mounting base.

[0017] Compared to the aforementioned background technology, the present application provides a tooling for disassembling UAV engine tappets, including a valve compression assembly and a disassembly assembly. The valve compression assembly includes a compression plate for compressing the valve spring, and the disassembly assembly includes a disassembly shaft for disassembling the rocker arm shaft. During engine disassembly, the compression plate abuts against the engine's valve spring, compressing it and preventing contact between the engine tappet and the valve spring. This prevents interference from the valve spring during tappet disassembly. The disassembly shaft is inserted into the engine's rocker arm shaft, aligning its end with a locating pin. Rotating the disassembly shaft allows the locating pin to be unscrewed, thereby removing the rocker arm shaft. This disassembles the double-arm lever structure formed by the rocker arm shaft and allows the engine tappet to be removed. The present application's tooling for disassembling UAV engine tappets reduces the number of manual laborers required for tappet disassembly and also reduces disassembly time, thus improving disassembly efficiency. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the structure of a tooling for disassembling a drone engine tappet, according to an embodiment of this application.

[0020] Figure 2 This is a front view of a tooling for disassembling a drone engine tappet, according to an embodiment of this application.

[0021] Figure 3 This is a top view of a tooling for disassembling a drone engine tappet, according to an embodiment of this application.

[0022] Figure 4 This is a side view of a tooling for disassembling a drone engine tappet, according to an embodiment of this application.

[0023] in:

[0024] 1. Compression plate; 11. Slot; 2. Removal shaft; 21. Removal screw; 3. First mounting base; 4. Second mounting base; 41. Hollowed-out groove; 5. Lead screw; 6. Mounting block; 7. Fixing screw. Detailed Implementation

[0025] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] To enable those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0027] It should be noted that the directional terms such as "upper end," "lower end," "left side," and "right side" mentioned below are defined based on the accompanying drawings in the instruction manual.

[0028] like Figures 1 to 4 As shown in the embodiment of this application, the tooling for disassembling the tappet of a drone engine includes a valve compression assembly and a disassembly assembly. The valve compression assembly includes a compression plate 1, which is used to compress the valve spring. The disassembly assembly includes a disassembly shaft 2, which is used to disassemble the rocker arm shaft.

[0029] Understandably, during engine removal, the compression plate 1 is used to abut against the engine's valve springs. The compression plate 1 can compress the valve springs, thereby preventing the engine tappets from contacting the valve springs and preventing the valve springs from interfering with the engine tappets when removing them. The disassembly shaft 2 is inserted into the engine's rocker arm shaft and its end is aligned with the screw. Rotating the disassembly shaft 2 can unscrew the screw, thereby removing the rocker arm shaft. The double-arm lever structure composed of the rocker arm shaft is then disassembled, and the engine tappets can be removed.

[0030] The tooling for removing engine tappets of this application can reduce the number of manual workers required to remove engine tappets and reduce disassembly time, thereby improving disassembly efficiency.

[0031] In some embodiments, the fixture for disassembling the tappet of a drone engine is further provided with a first mounting base 3 and a second mounting base 4, a compression plate 1 is provided on the first mounting base 3, a disassembly shaft 2 is provided on the second mounting base 4, and the first mounting base 3 is connected to the second mounting base 4.

[0032] It is understandable that the first mounting base 3 and the second mounting base 4 are connected to form an integral structure. The compression plate 1 is set on the first mounting base 3 and the disassembly shaft 2 is set on the second mounting base 4. The positions of the compression plate 1 and the disassembly shaft 2 are fixed by the first mounting base 3 and the second mounting base 4, so that the compression plate 1 can be aligned with the valve spring of the engine and the disassembly shaft 2 can be aligned with the rocker arm shaft of the engine.

[0033] Based on the above embodiments, a lead screw 5 is provided between the compression plate 1 and the first mounting base 3. The lead screw 5 is threadedly engaged with the first mounting base 3, and the compression plate 1 is rotatably connected to the end of the lead screw 5.

[0034] It is understandable that when the lead screw 5 rotates, it can move relative to the first mounting base 3 along the axial direction of the lead screw 5. When the lead screw 5 rotates, the compression plate 1 moves synchronously with the lead screw 5, so that the compression plate 1 can move closer to or further away from the first mounting base 3 through the rotation of the lead screw 5, thereby adjusting the distance between the compression plate 1 and the first mounting base 3.

[0035] Preferably, the compression plate 1 is provided with a mounting block 6, which is a rectangular structure with a connecting groove in the center. A bearing is fixedly installed in the connecting groove, and the end of the lead screw 5 can be rotatably connected to the mounting block 6 through the bearing. Screw holes are provided on both sides of the connecting groove, and screws are threaded into the screw holes. The screws can extend into the compression plate 1 and engage with the threads of the compression plate 1, thereby achieving a fixed connection between the mounting block 6 and the compression plate 1. The mounting block 6 is located at the center of the compression plate 1.

[0036] Based on the above embodiments, the compression plate 1 is provided with a slot 11, which can engage with the protrusion of the engine valve spring.

[0037] It is understandable that when the compression plate 1 abuts against the valve spring of the engine, the slot 11 of the compression plate 1 can engage with the protrusion on the valve spring, thereby limiting the compression plate 1 and preventing the compression plate 1 from disengaging from the valve spring due to shaking during installation, thus preventing the valve spring from rebounding and causing safety hazards during installation.

[0038] Preferably, there are two slots 11, which are symmetrically distributed on both sides of the mounting block 6. The slots 11 are U-shaped slots with an opening at the upper end of the compression plate 1. The protrusion of the valve spring can slide and engage with the slot 11, and disengage from the opening of the slot 11, making it convenient for the compression plate 1 to be removed from the valve spring.

[0039] In some embodiments, the first mounting base 3 is provided with a connecting hole, and the second mounting base 4 is provided with a through hole. A fixing screw 7 is provided in the through hole. The fixing screw 7 is threadedly engaged with the through hole of the second mounting base 4. The fixing screw 7 can extend into the connecting hole and is threadedly engaged with the connecting hole.

[0040] Understandably, by fixing the screws 7 to the through holes of the second mounting base 4 and the connecting holes of the first mounting base 3 respectively, the first mounting base 3 and the second mounting base 4 can be fixedly connected to form a whole. Since the size and shape of different engine models are different, the positional relationship between the rocker arm shaft and the valve spring on different engines will also change. Therefore, it is necessary to install the corresponding second mounting base 4 to adjust the positional relationship between the disassembly shaft 2 and the compression plate 1, so that the disassembly tooling can be used for different engine models and improve versatility.

[0041] In some embodiments, the outer diameter of the fixing screw 7 is the same as the inner diameter of the engine housing mounting hole, and the fixing screw 7 can extend into the engine housing mounting hole.

[0042] Specifically, such as Figure 3 and Figure 4 As shown, the length of the fixing screw 7 is greater than the length of the through hole of the first mounting base 3. When the first mounting base 3 is fixedly connected to the second mounting base 4 by the thread engagement with the fixing screw 7, the end of the fixing screw 7 can protrude from the mounting hole of the second mounting base 4. The part of the fixing screw 7 that protrudes from the mounting hole of the second mounting base 4 can be inserted into the mounting hole of the engine housing, so that the first mounting base 3 and the second mounting base 4 can be fixed on the engine housing.

[0043] Understandably, by inserting the fixing screw 7 into the engine housing mounting hole, the disassembly tool can be positioned so that the compression plate 1 is aligned with the engine valve spring and the disassembly shaft 2 is aligned with the engine rocker arm shaft. At the same time, inserting the fixing screw 7 into the engine housing mounting hole can also fix the disassembly tool to the engine housing, avoiding the need for manual fixation of the disassembly tool during the disassembly process.

[0044] In some embodiments, the disassembly shaft 2 is provided with a disassembly screw 21 at its end, and the side wall of the disassembly shaft 2 is provided with threads. The disassembly shaft 2 is threadedly engaged with the second mounting seat 4 and can move relative to the second mounting seat 4 along its axial direction.

[0045] Specifically, the removal screw 21 has the same external dimensions as the locating pin inside the engine rocker arm shaft. The removal screw 21 can be inserted into the drive groove at the end of the locating pin and engage with the locating pin. By rotating, the locating pin can be unscrewed from the rocker arm shaft, thereby removing the rocker arm shaft.

[0046] It is understandable that by rotating the disassembly shaft 2, the disassembly shaft 2 can be moved axially relative to the second mounting seat 4 and gradually extended into the rocker arm shaft. When the disassembly screw 21 at the end of the disassembly shaft 2 is inserted into the drive groove of the positioning pin in the rocker arm shaft, the disassembly screw 21 is engaged with the positioning pin. At this time, the positioning pin can rotate synchronously with the disassembly screw 21. By rotating the disassembly shaft 2, the positioning pin can be unscrewed, thereby releasing the rocker arm shaft from the engine. The user can then remove the rocker arm shaft from the engine.

[0047] Preferably, the disassembly screw 21 has a regular hexagonal structure and is fixedly connected to the end of the disassembly shaft 2 by welding.

[0048] In other embodiments, the disassembly screw 21 may be a cross-shaped structure, a star-shaped structure, or other structures, and the structure of the disassembly screw 21 is consistent with the shape of the locating pin drive groove.

[0049] In some embodiments, the second mounting base 4 is provided with a hollowed-out groove 41.

[0050] It is understandable that by providing a hollowed-out groove 41 inside the second mounting base 4, the weight of the second mounting base 4 can be reduced, making it easier for users to carry and use.

[0051] In some embodiments, the lead screw 5 is provided with a first limiting member, which can abut against the first mounting base 3.

[0052] Specifically, the first limiting component is a nut, the diameter of which is larger than the diameter of the lead screw 5, and the first limiting component is fixedly installed at the end of the lead screw 5 by welding.

[0053] It is understandable that when the lead screw 5 moves to the point where the first limiting member abuts against the first mounting base 3, the first limiting member can limit the lead screw 5 to prevent it from continuing to move and causing it to detach from the first mounting base 3. At this time, the distance between the compression plate 1 and the first mounting base 3 is at its maximum.

[0054] In some embodiments, the disassembly shaft 2 is provided with a second limiting member, which can abut against the second mounting base 4.

[0055] Specifically, the second limiting member can be a nut, and the second limiting member can be welded to the end of the disassembly shaft 2.

[0056] It is understandable that when the disassembly shaft 2 moves to the point where the second limiting member abuts against the second mounting base 4, the second limiting member can limit the disassembly shaft 2 to prevent it from continuing to move and causing it to detach from the second mounting base 4.

[0057] In summary, the tooling for disassembling UAV engine tappets described in this application can be fixed to the engine housing. The compression plate 1 compresses the engine valve spring, releasing its restriction on the engine tappet. Then, the disassembly shaft 2 removes the locating pin in the engine rocker arm shaft, thereby removing the rocker arm shaft and disassembling its double-arm lever structure, thus completing the removal and disassembly of the tappet. The disassembly process requires only one person, reducing disassembly time and improving efficiency.

[0058] It should be noted that in this specification, relational terms such as first and second are used only to distinguish one entity from several other entities, and do not necessarily require or imply any such actual relationship or order between these entities.

[0059] The foregoing has provided a detailed description of the tooling for disassembling UAV engine tappets provided in this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the solution and core ideas of this application. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. A fixture for disassembling tappets of UAV engines, characterized in that, include: A valve compression assembly, the valve compression assembly including a compression plate (1) for compressing the valve springs of the engine; The disassembly assembly includes a disassembly shaft (2) for disassembling the rocker arm shaft.

2. The fixture for disassembling UAV engine tappets according to claim 1, characterized in that, It is also provided with a first mounting seat (3) and a second mounting seat (4), the compression plate (1) is provided on the first mounting seat (3), the rocker arm shaft is provided on the second mounting seat (4), and the first mounting seat (3) and the second mounting seat (4) are connected.

3. The fixture for disassembling UAV engine tappets according to claim 2, characterized in that, A lead screw (5) is provided between the compression plate (1) and the first mounting base (3). The lead screw (5) is threadedly engaged with the first mounting base (3), and the end of the lead screw (5) is rotatably connected to the compression plate (1).

4. The fixture for disassembling UAV engine tappets according to claim 2, characterized in that, The second mounting base (4) is provided with a hollowed-out groove (41).

5. The fixture for disassembling UAV engine tappets according to claim 3, characterized in that, The compression plate (1) is provided with a slot (11) which can engage with the protrusion of the engine valve spring.

6. The fixture for disassembling UAV engine tappets according to claim 5, characterized in that, The lead screw (5) is provided with a first limiting member, which can abut against the first mounting base (3).

7. The fixture for disassembling UAV engine tappets according to claim 2, characterized in that, The second mounting base (4) is provided with a connecting hole, and the first mounting base (3) is provided with a through hole. A fixing screw (7) is threaded into the through hole. The fixing screw (7) can extend into the connecting hole and threadedly engage with the connecting hole to achieve a detachable connection between the first mounting base (3) and the second mounting base (4).

8. The fixture for disassembling UAV engine tappets according to claim 7, characterized in that, The outer diameter of the fixing screw (7) is the same as the inner diameter of the engine housing mounting hole, and the fixing screw (7) can extend into the engine housing mounting hole.

9. The fixture for disassembling UAV engine tappets according to claim 2, characterized in that, The end of the disassembly shaft (2) is provided with a disassembly screw (21), the side wall of the disassembly shaft (2) is threaded, the disassembly shaft (2) is threadedly engaged with the second mounting seat (4), and can move relative to the second mounting seat (4) along its axial direction.

10. The fixture for disassembling UAV engine tappets according to claim 9, characterized in that, The disassembly shaft (2) is provided with a second limiting member, which can abut against the second mounting base (4).

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