Pin inserting and pulling device for disassembling and assembling aircraft engine

Abstract

The utility model discloses an aircraft engine disassembly and assembly plug pin device, which relates to the technical field of aircraft engines, and comprises a side plate and a base, the side plate is connected with the base through a hexagon bolt, the base is connected with a nut, the nut is connected with a screw rod through a bolt, and a connecting shaft is arranged in the screw rod. An end cover is connected to the base through an inner hexagonal countersunk head screw, a needle roller thrust bearing is arranged in the base, the device is provided with a plug pin structure, a connector and a thrust pin are assembled and connected through threads by assembly and disassembly maintenance personnel, and then a left side plate and a right side plate which are symmetrical are fixedly connected with a fixed cabin plate in an engine mounting cabin through four quick-release pins. The nut is rotated through the ratchet wrench, the nut and the lead screw are in threaded transmission, the lead screw can do linear motion through the end cover limiting boss and the lead screw groove structure, the lead screw drives the connector to move, and therefore the aircraft engine thrust pin is driven to move in the axis direction to achieve assembling, disassembling, inserting and pulling work.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft engine disassembly and assembly, in particular to an aircraft engine disassembly and assembly pin insertion and extraction device. Background Art

[0002] The engine is the heart of the aircraft, the largest finished part in the aircraft assembly process, and an extremely important link in the aircraft manufacturing process. In the aviation field, the engine and its supporting parts have high manufacturing precision requirements and are high-value products. If improper operation occurs during the installation and disassembly process, it is easy to cause great losses. When installing the engine, after the engine enters the cabin and reaches the predetermined position, the engine main thrust pin is inserted into the end face of the engine connection to connect and fix it, so that the engine can be assembled in the cabin. When disassembling, the main thrust is pulled out from the engine, and the engine can be disassembled. The existing thrust pin assembly and disassembly space is small, and the process of inserting and removing the thrust pin is difficult, which can easily cause damage to the thrust pin and the engine, resulting in huge economic losses. The difficulties and problems existing in the insertion and removal of thrust pins in existing aircraft engines. It ensures that the aircraft engine is accurately controlled during assembly and disassembly in the cabin, and also solves the installation difficulties caused by the small installation space.

[0003] Therefore, we have proposed a kind of aircraft engine disassembly and assembly plug-in and pull-out pin device, in order to solve the problem raised in above-mentioned. Utility Model Content

[0004] The purpose of the utility model is to provide an aircraft engine disassembly and insertion pin device to solve the problems of the aircraft engine disassembly and insertion pin device currently on the market being inconvenient to use and having poor insertion and extraction effect, as mentioned in the above background art.

[0005] To achieve the above-mentioned purpose, the present utility model provides the following technical solutions: an aircraft engine disassembly and insertion pin device, comprising a side plate and a base;

[0006] The side panel is connected to the base through a hexagonal bolt, the base is connected to the nut, and the nut is connected to the screw rod through a bolt connection, and a connecting shaft is provided inside the screw rod, the base is connected to the end cover through a hexagonal countersunk screw, and a thrust needle roller bearing is provided inside the base, the side panel is connected to the fixed cabin plate through a quick-release pin, and the front end of the connecting shaft is connected to a connecting head.

[0007] The adoption of the above technical solution can make the plugging and unplugging effect of the latch better and more convenient to use.

[0008] As a preferred technical solution of the present invention, the side panels are symmetrically arranged about the center of the base, and the side panels are connected to the base via hexagonal bolts.

[0009] The above technical solution can achieve better fixing effect on the side panels.

[0010] As a preferred technical solution of the present invention, a ratchet wrench is sleeved on the nut, a through hole is opened inside the side plate, and the through hole is arranged at the center position of the side plate.

[0011] The adoption of the above technical solution can make the rotation of the nut better and the use of the handle more convenient.

[0012] As a preferred technical solution of the present invention, the fixed cabin plate is connected to the thrust pin, and the front end of the thrust pin is connected to one end of the connecting shaft.

[0013] The adoption of the above technical solution can achieve a better connection effect of the fixed cabin board.

[0014] As a preferred technical solution of the present invention, the hexagon socket countersunk screws are symmetrically arranged about the center of the end cover, and the hexagon socket countersunk screws are connected to the end cover through a threaded connection.

[0015] The adoption of the above technical solution can achieve a better fixing effect on the end cover.

[0016] As a preferred technical solution of the present invention, the quick-release pins are symmetrically arranged about the center of the side plate, and a pull ring is connected above the quick-release pins.

[0017] The adoption of the above technical solution can make the installation and disassembly of the quick-release pin more convenient.

[0018] As a preferred technical solution of the present invention, the side panels are connected to the fixed cabin panels via quick-release pins, and two thrust needle roller bearings are assembled in the structural space between the nut and the base.

[0019] Compared with the prior art, the beneficial effects of the present invention are:

[0020] 1. The device features a convenient, user-friendly structure. Two symmetrical side panels are designed on the left and right sides of the base, each secured with two hexagonal bolts. An end cap is designed on the inside of the base, secured with four hexagonal countersunk screws. A nut secures the screw, which in turn secures the thrust pin assembly. The assembly consists of a connector and a connecting shaft. The connector's outer surface is machined to match the thread size for connection with the thrust pin. The base is machined internally to accommodate the nut. Two thrust needle roller bearings are installed in the space between the nut and the base.

[0021] 2. The device is equipped with a plug-in pin structure. The loading and unloading maintenance personnel connect the connecting head and the thrust pin through threaded assembly, and then connect and fix the two symmetrical side panels on the left and right sides to the fixed panels in the engine installation compartment through four quick-release pins. The nut is rotated by a ratchet wrench, and there is a threaded transmission between the nut and the screw rod. Through the end cover limiting boss and the screw rod groove structure, the screw rod can move linearly, and the screw rod drives the connecting head to move, thereby driving the aircraft engine thrust pin to move along the axial direction to realize loading and unloading and plugging. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the three-dimensional structure of the connecting shaft of the utility model;

[0023] Figure 2 This is a schematic diagram of the main structure of the utility model;

[0024] Figure 3 This is a schematic diagram of the front structure of the utility model;

[0025] Figure 4 This is a rear view structural diagram of the utility model;

[0026] Figure 5 It is a schematic diagram of the top structure of the utility model.

[0027] In the figure: 1. Side panel; 2. Base; 3. Nut; 4. Screw; 5. Quick-release pin; 6. Hexagon bolt; 7. Ratchet wrench; 8. Thrust needle roller bearing; 9. Connecting shaft; 10. Connecting head; 11. End cover; 12. Hexagon socket countersunk screw; 13. Thrust pin; 14. Fixed cabin plate. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0029] See also Figure 1-5 The utility model provides a technical solution: an aircraft engine disassembly and insertion pin device, comprising a side panel 1 and a base 2, wherein the side panel 1 is symmetrically arranged about the center of the base 2, and the side panel 1 is connected to the base 2 by a hexagonal bolt 6;

[0030] First, when in use, the base 2 is designed with two symmetrical side panels 1 on the left and right sides. Each side panel 1 is assembled and fixed by two hexagonal bolts 6. The base 2 is designed with an end cover 11 on the inside, which is fixed by four hexagonal countersunk screws 12. The screw 4 is fixed inside the screw nut 3, and the thrust pin 13 is connected to the assembly. The connection assembly consists of a connector 10 and a connecting shaft 9. The outer surface of the connector 10 is machined to match the thread size and connects to the thrust pin 13. The base 2 is machined into a corresponding structure to accommodate the screw nut 3. Multiple thrust needle roller bearings 8 are installed in the structural space between the screw nut 3 and the base 2.

[0031] The side panel 1 is connected to the base 2 by a hexagonal bolt 6, and the hexagonal countersunk screw 12 is symmetrically arranged about the center of the end cover 11. Two thrust needle bearings 8 are assembled at the structural space inside the nut 3 and the base 2. A ratchet wrench 7 is sleeved on the nut 3. A through hole is opened inside the side panel 1, and the through hole is arranged at the center of the side panel 1. The base 2 and the nut 3 are connected, and the nut 3 is connected to the screw rod 4 by a bolt connection, and a connecting shaft 9 is arranged inside the screw rod 4. The base 2 is connected to the end cover by a hexagonal countersunk screw 12 11. The hexagon socket countersunk screw 12 is symmetrically arranged about the center of the end cover 11, and the hexagon socket countersunk screw 12 is connected to the end cover 11 through a threaded connection. A thrust needle roller bearing 8 is provided inside the base 2. The side plate 1 is connected to the fixed cabin plate 14 through a quick-release pin 5. The fixed cabin plate 14 is connected to the thrust pin 13, and the front end of the thrust pin 13 is connected to one end of the connecting shaft 9. The quick-release pin 5 is symmetrically arranged about the center of the side plate 1, and a pull ring is connected above the quick-release pin 5. The front end of the connecting shaft 9 is connected to the connector 10;

[0032] During use, the loading and unloading maintenance personnel connect the connecting head 10 and the thrust pin 13 through threaded assembly, and then connect and fix the left and right symmetrical side panels 1 to the fixed cabin plate 14 in the engine installation cabin through four quick-release pins 5. The nut 3 is rotated by the ratchet wrench 7. The threaded transmission between the nut 3 and the screw rod 4 is realized. Through the limiting boss of the end cover 11 and the groove structure of the screw rod 4, the screw rod 4 can move linearly. The screw rod 4 drives the connecting head 10 to move, thereby driving the aircraft engine thrust pin 13 to move along the axial direction to realize loading and unloading and plugging.

[0033] Working Principle: When using the aircraft engine pin removal and assembly device, first use the base 2, which is designed with two symmetrical side panels 1 on the left and right sides. Each side panel 1 is assembled and fixed by two hexagonal bolts 6. The base 2 is designed with an end cover 11 on the inside, which is fixed by four hexagonal countersunk screws 12. The nut 3 is inserted into the fixed screw 4, which is inserted into the thrust pin 13 to connect the assembly. The connection assembly consists of a connector 10 and a connecting shaft 9. The outer surface of the connector 10 is machined to match the thread size for connection with the thrust pin 13. The base 2 is machined into a corresponding structure to accommodate the nut 3. Multiple thrust needle roller bearings 8 are assembled in the structural space between the nut 3 and the base 2.

[0034] During use, the loading and unloading maintenance personnel connect the connecting head 10 and the thrust pin 13 through threaded assembly, and then connect and fix the left and right symmetrical side panels 1 to the fixed cabin plate 14 in the engine installation cabin through four quick-release pins 5. The nut 3 is rotated by the ratchet wrench 7. The threaded transmission between the nut 3 and the screw rod 4 is realized. Through the limiting boss of the end cover 11 and the groove structure of the screw rod 4, the screw rod 4 can move linearly. The screw rod 4 drives the connecting head 10 to move, thereby driving the aircraft engine thrust pin 13 to move along the axial direction to realize loading and unloading and plugging.

[0035] Thereby completing a series of tasks, the contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0036] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the present invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be encompassed within the present invention. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

Claims

1. An aircraft engine disassembly and assembly pin insertion and extraction device, comprising a side plate (1) and a base (2); Features: The side plate (1) is connected to the base (2) via a hexagonal bolt (6), the base (2) is connected to a nut (3), and the nut (3) is connected to a screw rod (4) via a bolt connection, and a connecting shaft (9) is arranged inside the screw rod (4), the base (2) is connected to an end cover (11) via a hexagon socket countersunk screw (12), and a thrust needle roller bearing (8) is arranged inside the base (2), the side plate (1) is connected to a fixed cabin plate (14) via a quick-release pin (5), and a connecting head (10) is connected to the front end of the connecting shaft (9).

2. The aircraft engine disassembly and assembly pin insertion and extraction device according to claim 1, characterized in that: The side plates (1) are arranged symmetrically about the center of the base (2), and the side plates (1) are connected to the base (2) via hexagonal bolts (6).

3. The aircraft engine disassembly and insertion pin device according to claim 1, characterized in that: A ratchet wrench (7) is sleeved on the nut (3), and a through hole is provided inside the side plate (1), and the through hole is arranged at the center of the side plate (1).

4. The aircraft engine disassembly and assembly pin insertion and extraction device according to claim 1, characterized in that: The fixed cabin plate (14) is connected to the thrust pin (13), and the front end of the thrust pin (13) is connected to one end of the connecting shaft (9).

5. The aircraft engine disassembly and assembly pin insertion and extraction device according to claim 1, characterized in that: The hexagon socket countersunk screw (12) is symmetrically arranged with respect to the center of the end cover (11), and the hexagon socket countersunk screw (12) is connected to the end cover (11) via a threaded connection.

6. The aircraft engine disassembly and insertion pin device according to claim 1, characterized in that: The quick-release pin (5) is symmetrically arranged about the center of the side plate (1), and a pull ring is connected above the quick-release pin (5).

7. The aircraft engine disassembly and assembly pin insertion and extraction device according to claim 1, characterized in that: The side plates (1) are connected to the fixed cabin plate (14) via quick-release pins (5), and two thrust needle roller bearings (8) are assembled at the structural space inside the nut (3) and the base (2).

Images