Disassembling and assembling tool

Abstract

The utility model provides a dismounting tool, and relates to the technical field of aero-engines. The dismounting tool comprises a bottom plate, a driving mechanism used for adjusting the angle of the aero-engine and a mounting mechanism, the driving mechanism comprises a driving ring with a rotating function and a first limiting plate with a supporting function, and the outer surface of the driving ring is slidably connected with a limiting rod. According to the disassembling and assembling tool, a first electric telescopic rod is started, one end of the first electric telescopic rod drives a fixing block to slide towards the outer surface of an aero-engine body, then the outer surface of the fixing block is tightly attached to the outer surface of the aero-engine body, and then a first servo motor is started; the output shaft of the first servo motor drives the driving gear to rotate, the driving gear rotates to drive the driving ring to rotate, the driving ring rotates to drive the aero-engine body to rotate, and then different positions of the outer surface of the aero-engine body can be disassembled and assembled conveniently.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace engines, and in particular to a disassembly and assembly tool. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry. Every important change in human aviation history is closely related to the technological progress of aircraft engines.

[0003] Due to the large size of aircraft engines, when disassembling and assembling aircraft engines at high places, it is often necessary to use a ladder to perform the operation, so the disassembly and assembly is relatively cumbersome, and there is a problem that the aircraft engine cannot be disassembled and assembled at a lower place. Utility Model Content

[0004] 1. Technical issues to be resolved

[0005] In view of the deficiencies in the prior art, the present application provides a disassembly and assembly tool to solve the problems mentioned in the above background technology.

[0006] (II) Technical solution

[0007] To achieve the above objectives, the present application is implemented through the following technical solutions: a disassembly and assembly tool, including a base plate, a driving mechanism and an installation mechanism for adjusting the angle of an aircraft engine, the driving mechanism including a driving ring with a rotation function and a first limit plate with a supporting function, the outer surface of the driving ring is slidably connected to a limit rod, the lower surface of the limit rod is fixedly connected to the upper surface of the base plate, the installation mechanism includes a movable frame with a sliding function, and the outer surface of the movable frame is slidably connected to the outer surface of the base plate.

[0008] By adopting the above technical solution, the aircraft engine is driven to rotate by the rotation of the driving ring, thereby facilitating the disassembly, assembly and maintenance of the aircraft engine at a low location.

[0009] Preferably, grooves are provided on the side surfaces of the driving ring, and the outer surface of the driving ring is rotatably connected to multiple groups of first rotating shafts, the outer surface of the first rotating shaft is fixedly connected to a support rod, and the lower surface of the support rod is fixedly connected to the upper surface of the base plate.

[0010] By adopting the above technical solution, the first rotating shaft rolls on the side surface of the driving ring, which facilitates increasing the lubrication degree between the first rotating shaft and the driving ring. At the same time, multiple groups of support rods are used to support the outer surface of the aerospace engine, making it easier for staff to operate the aerospace engine.

[0011] Preferably, a plurality of first electric telescopic rods are embedded inside the driving circle, and one end of each three first electric telescopic rods pointing to the center of the driving circle is fixedly connected to the same group of fixing blocks, and the outer surface of the fixing blocks is in contact with the aircraft engine body.

[0012] By adopting the above technical solution, by starting the first electric telescopic rod, one end of the first electric telescopic rod drives the fixing block to move closer to the inside of the driving circle, thereby facilitating the clamping and fixing of aircraft engine bodies of different sizes.

[0013] Preferably, the outer surface of the driving ring is fixedly connected to an external gear, the outer surface of the external gear is meshingly connected to a driving gear, the outer surface of the driving gear is fixedly connected to an output shaft of a first servo motor, and the first servo motor is fixedly connected to the upper surface of the base plate.

[0014] By adopting the above technical solution, by starting the first servo motor, the output shaft of the first servo motor drives the driving gear to rotate, thereby causing the driving ring to rotate, thereby facilitating the rotation of the clamped aircraft engine body.

[0015] Preferably, the outer surface of the first limit plate is hinged with a second limit plate, the outer surfaces of the second limit plate and the first limit plate are both threaded with bolts, and the outer surface of the second limit plate is slidably connected to a support frame, the inner wall of the support frame is fixedly connected with a second rotating shaft, the second rotating shaft is slidably connected to the side surface of the second limit plate, and the support frame is fixedly connected to the upper surface of the movable frame.

[0016] By adopting the above technical solution, the first limit plate and the second limit plate are hinged, so that the aircraft engine body can be fixed between the first limit plate and the second limit plate. At the same time, the second rotating shaft allows the first limit plate and the second limit plate to slide on the outer surface of the support frame, so that the first limit plate and the second limit plate can rotate synchronously with the driving circle.

[0017] Preferably, a plurality of groups of second electric telescopic rods are fixedly connected to the inner side surface of the mobile frame, and a bearing plate is fixedly connected to the upper end of the second electric telescopic rod.

[0018] By adopting the above technical solution, by starting the second electric telescopic rod, the upper end of the second electric telescopic rod drives the supporting plate to move upward, so that the upper surface of the supporting plate and the outer surface of the aircraft engine body are in contact with each other, which is convenient for supporting the aircraft engine body.

[0019] Preferably, the mounting mechanism also includes a second servo motor, an outer surface of the second servo motor is fixedly connected to the lower surface of the base plate, and an output shaft of the second servo motor is fixedly connected to a threaded rod, an outer surface of the threaded rod is threadedly connected to an outer surface of the movable frame, and the other end of the threaded rod is rotatably connected to the outer surface of the base plate.

[0020] By adopting the above technical solution, by starting the second servo motor, the output shaft of the second servo motor drives the threaded rod to rotate, and then the threaded rod can drive the movable frame to slide along the outer surface of the base plate, making it easier to insert the other end of the aircraft engine body into the drive circle.

[0021] Preferably, a sliding rod is fixedly connected to the outer surface of the movable frame, and a lower surface of the sliding rod is slidably connected to an upper surface of the base plate.

[0022] By adopting the above technical solution, the movable frame is limited by the sliding rod, thereby preventing the movable frame from sliding down from the through hole opened on the upper surface of the bottom plate.

[0023] (III) Beneficial effects

[0024] The present application provides a disassembly and assembly tool. The beneficial effects are as follows:

[0025] 1. By starting the first electric telescopic rod, one end of the first electric telescopic rod drives the fixed block to slide toward the outer surface of the aircraft engine body, so that the outer surface of the fixed block is closely fitted with the outer surface of the aircraft engine body, and then the first servo motor is started, and the output shaft of the first servo motor drives the driving gear to rotate, the driving gear rotation drives the driving ring rotation, the driving ring rotation drives the aircraft engine body rotation, so as to facilitate the disassembly and assembly of different positions of the outer surface of the aircraft engine body.

[0026] 2. By starting the second servo motor, the output shaft of the second servo motor drives the threaded rod to rotate, and the rotation of the threaded rod drives the movable frame to slide along the upper surface of the base plate, thereby moving the aircraft engine body toward the center of the driving circle, which facilitates the movement and installation of the aircraft engine body to a certain extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the main structure of this application;

[0028] Figure 2 It is a schematic diagram of the cross-sectional structure of the driving ring in this application;

[0029] Figure 3 It is a schematic cross-sectional structure diagram of the mobile frame in this application;

[0030] Figure 4 For this application Figure 3 A schematic diagram of the enlarged structure at point A;

[0031] Figure 5 It is a schematic diagram of the connection structure between the support frame and the second rotating shaft in this application.

[0032] In the figure: 1. bottom plate; 2. driving mechanism; 201. limit rod; 202. external gear; 203. driving ring; 204. supporting rod; 205. first rotating shaft; 206. first limit plate; 207. bolt; 208. second limit plate; 209. driving gear; 210. first electric telescopic rod; 211. fixing block; 212. first servo motor; 213. supporting frame; 214. second rotating shaft; 3. aircraft engine body; 4. mounting mechanism; 401. moving frame; 402. bearing plate; 403. threaded rod; 404. second electric telescopic rod; 405. second servo motor; 406. sliding rod. DETAILED DESCRIPTION

[0033] The present application is further described in detail below through drawings and examples.

[0034] It should be noted that in the description of the embodiments of the present application, the terms "front, rear", "left, right", "up, down", etc. indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present application. The terms "install", "connect", 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 direct connection, or an indirect connection 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 present application can be understood according to specific circumstances.

[0035] Reference Figures 1 to 5 An embodiment of the present application provides a disassembly and assembly tool, including a base plate 1, a driving mechanism 2 for adjusting the angle of an aircraft engine, and an installation mechanism 4, wherein the driving mechanism 2 includes a driving ring 203 with a rotation function and a first limit plate 206 with a supporting function, the outer surface of the driving ring 203 is slidably connected to a limit rod 201, the lower surface of the limit rod 201 is fixedly connected to the upper surface of the base plate 1, and the installation mechanism 4 includes a moving frame 401 with a sliding function, and the outer surface of the moving frame 401 is slidably connected to the outer surface of the base plate 1.

[0036] Grooves are formed on the side surfaces of the driving ring 203 , and the outer surface of the driving ring 203 is rotatably connected to multiple sets of first rotating shafts 205 . The outer surface of the first rotating shaft 205 is fixedly connected to the support rod 204 , and the lower surface of the support rod 204 is fixedly connected to the upper surface of the bottom plate 1 .

[0037] Nine groups of first electric telescopic rods 210 are embedded inside the driving circle 203, and one end of each three groups of first electric telescopic rods 210 pointing to the center of the driving circle 203 is fixedly connected to the same group of fixed blocks 211, the outer surface of the fixed block 211 is in contact with the aircraft engine body 3, and the angle between the fixed blocks 211 is one hundred and twenty degrees.

[0038] The outer surface of the driving ring 203 is fixedly connected to the outer gear 202 , the outer surface of the outer gear 202 is meshedly connected to the driving gear 209 , the outer surface of the driving gear 209 is fixedly connected to the output shaft of the first servo motor 212 , and the first servo motor 212 is fixedly connected to the upper surface of the base plate 1 .

[0039] The outer surface of the first limit plate 206 is hinged with the second limit plate 208, and the outer surfaces of the second limit plate 208 and the first limit plate 206 are both threadedly connected with bolts 207, and the outer surface of the second limit plate 208 is slidably connected with the support frame 213, and the inner wall of the support frame 213 is fixedly connected with the second rotating shaft 214, and the second rotating shaft 214 is slidably connected to the side surface of the second limit plate 208, and the support frame 213 is fixedly connected to the upper surface of the mobile frame 401. Start the first electric telescopic rod 210, one end of the first electric telescopic rod 210 drives the fixed block 211 to slide toward the outer surface of the aircraft engine body 3, so that the outer surface of the fixed block 211 is closely attached to the outer surface of the aircraft engine body 3, and then start the first servo motor 212, the output shaft of the first servo motor 212 drives the driving gear 209 to rotate, the driving gear 209 rotates to drive the driving ring 203 to rotate, and the driving ring 203 rotates to drive the aircraft engine body 3.

[0040] Reference Figures 1 to 5 In one aspect of this embodiment, four groups of second electric telescopic rods 404 are fixedly connected to the inner side surface of the mobile frame 401, and the upper ends of the second electric telescopic rods 404 are fixedly connected to the bearing plate 402.

[0041] The mounting mechanism 4 also includes a second servo motor 405, the outer surface of which is fixedly connected to the lower surface of the base plate 1, and the output shaft of the second servo motor 405 is fixedly connected to a threaded rod 403, the outer surface of the threaded rod 403 is threadedly connected to the outer surface of the movable frame 401, and the other end of the threaded rod 403 is rotatably connected to the outer surface of the base plate 1.

[0042] The outer surface of the mobile frame 401 is fixedly connected with a sliding rod 406, and the lower surface of the sliding rod 406 is slidably connected with the upper surface of the bottom plate 1. The second servo motor 405 is started, and the output shaft of the second servo motor 405 drives the threaded rod 403 to rotate. The rotation of the threaded rod 403 drives the mobile frame 401 to slide along the upper surface of the bottom plate 1, thereby moving the aircraft engine body 3 toward the center of the driving circle 203.

[0043] All electrical equipment in this solution are powered by an external power supply.

[0044] Working principle: When in use, first place the aircraft engine body 3 on the upper surface of the bearing plate 402 and the second limit plate 208, then rotate the first limit plate 206 so that the outer surface of the first limit plate 206 fits with the outer surface of the second limit plate 208, and then use the bolt 207 to fix the first limit plate 206 and the second limit plate 208, then start the second servo motor 405, the output shaft of the second servo motor 405 drives the threaded rod 403 to rotate, and the rotation of the threaded rod 403 drives the moving frame 401 to slide along the upper surface of the bottom plate 1, thereby causing the aircraft engine body 3 to move toward the driving circle 203 is moved to the center, and then the first electric telescopic rod 210 is started. One end of the first electric telescopic rod 210 drives the fixed block 211 to slide toward the outer surface of the aircraft engine body 3, so that the outer surface of the fixed block 211 is tightly fitted with the outer surface of the aircraft engine body 3. Then the first servo motor 212 is started. The output shaft of the first servo motor 212 drives the driving gear 209 to rotate. The driving gear 209 rotates to drive the driving ring 203 to rotate. The driving ring 203 rotates to drive the aircraft engine body 3, so as to facilitate the disassembly and assembly of different positions of the outer surface of the aircraft engine body 3.

[0045] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0046] Although the embodiments of the present application have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A disassembly and assembly tool, comprising a base plate (1), a driving mechanism (2) for adjusting the angle of an aircraft engine, and a mounting mechanism (4), characterized in that: The driving mechanism (2) comprises a driving ring (203) having a rotating function and a first limiting plate (206) having a supporting function; the outer surface of the driving ring (203) is slidably connected to a limiting rod (201); the lower surface of the limiting rod (201) is fixedly connected to the upper surface of the base plate (1); and the mounting mechanism (4) comprises a moving frame (401) having a sliding function; the outer surface of the moving frame (401) is slidably connected to the outer surface of the base plate (1).

2. A disassembly and assembly tool according to claim 1, characterized in that: The side surfaces of the driving ring (203) are all provided with grooves, and the outer surface of the driving ring (203) is rotatably connected to multiple groups of first rotating shafts (205), the outer surface of the first rotating shaft (205) is fixedly connected to a support rod (204), and the lower surface of the support rod (204) is fixedly connected to the upper surface of the bottom plate (1).

3. A disassembly and assembly tool according to claim 1, characterized in that: A plurality of groups of first electric telescopic rods (210) are embedded inside the driving circle (203), and one end of each of the three groups of first electric telescopic rods (210) pointing toward the center of the driving circle (203) is fixedly connected to the same group of fixing blocks (211), and the outer surface of the fixing blocks (211) is in contact with the aircraft engine body (3).

4. A disassembly and assembly tool according to claim 1, characterized in that: The outer surface of the driving ring (203) is fixedly connected to an external gear (202), the outer surface of the external gear (202) is meshingly connected to a driving gear (209), the outer surface of the driving gear (209) is fixedly connected to an output shaft of a first servo motor (212), and the first servo motor (212) is fixedly connected to the upper surface of the base plate (1).

5. A disassembly and assembly tool according to claim 1, characterized in that: The outer surface of the first limiting plate (206) is hinged with a second limiting plate (208), the outer surfaces of the second limiting plate (208) and the first limiting plate (206) are both threadedly connected with bolts (207), and the outer surface of the second limiting plate (208) is slidably connected with a support frame (213), the inner wall of the support frame (213) is fixedly connected with a second rotating shaft (214), the second rotating shaft (214) is slidably connected to the side surface of the second limiting plate (208), and the support frame (213) is fixedly connected to the upper surface of the movable frame (401).

6. A disassembly and assembly tool according to claim 1, characterized in that: A plurality of groups of second electric telescopic rods (404) are fixedly connected to the inner side surface of the mobile frame (401), and a bearing plate (402) is fixedly connected to the upper end of the second electric telescopic rod (404).

7. A disassembly and assembly tool according to any one of claims 1 to 6, characterized in that: The mounting mechanism (4) further comprises a second servo motor (405), the outer surface of the second servo motor (405) being fixedly connected to the lower surface of the base plate (1), and the output shaft of the second servo motor (405) being fixedly connected to a threaded rod (403), the outer surface of the threaded rod (403) being threadedly connected to the outer surface of the movable frame (401), and the other end of the threaded rod (403) being rotatably connected to the outer surface of the base plate (1).

8. A disassembly and assembly tool according to claim 7, characterized in that: The outer surface of the movable frame (401) is fixedly connected with a sliding rod (406), and the lower surface of the sliding rod (406) is slidably connected to the upper surface of the bottom plate (1).

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