Hydraulic tool for disassembling and assembling multiple coaxial linings of aircraft engine hanger

Abstract

The utility model discloses a hydraulic tool for dismounting and mounting a plurality of coaxial linings of an aircraft engine suspension, which comprises a hydraulic actuating mechanism, a positioning frame, an adjustable push rod and a contact pressure head, the positioning frame can be connected onto the hydraulic actuating mechanism, the front end of the positioning frame extends forwards to the front of the hydraulic actuating mechanism and is provided with a top plate, and the adjustable push rod is connected with the contact pressure head. The top plate is used for abutting against the side face, away from the hydraulic executing mechanism, of a connecting plate of an aircraft engine hanger, the adjustable push rod is connected to the hydraulic executing mechanism, the hydraulic executing mechanism drives the adjustable push rod to advance forwards when the lining is disassembled and assembled, and the adjustable push rod can adjust the front-back position relative to the hydraulic executing mechanism. The contact pressure head is installed at the front end of the adjustable push rod and used for abutting against the lining, and the front portion of the contact pressure head can be embedded into the lining in a matched mode. According to the utility model, the bushing of the aircraft engine hanger can be more efficiently disassembled and assembled.

Description

Technical Field

[0001] This utility model relates to the field of aircraft engine mounting maintenance technology, specifically to a hydraulic tool for disassembling and assembling coaxial multi-bushings for aircraft engine mounting. Background Technology

[0002] In the aviation field, the maintenance and repair of aircraft engines are crucial to ensuring flight safety and reliability. The maintenance and repair of aircraft engines often involves the removal and installation of bushings 6.3 on the engine pylon 6.

[0003] The aircraft engine mount 6 is typically composed of a multi-axis assembly, with multiple bushings 6.3 on each axis (usually four bushings per axis). The bushings 6.3 are coaxially and tightly installed in bushing holes 6.2, which are located on the connecting plate 6.1 of the aircraft engine mount 6. The multiple coaxial bushings 6.3 are close together, and the operating space is limited. Therefore, the disassembly and assembly of the bushings 6.3 is an important and challenging task.

[0004] Currently, the tool for disassembling bushing 6.3 involves pressing the head of a push rod against bushing 6.3 and then manually applying pressure to push bushing 6.3 out of bushing hole 6.2 or squeeze bushing 6.3 into bushing hole 6.2 to complete the disassembly and assembly. However, this method is inefficient, inconvenient to operate, and prone to damaging components, making it difficult to meet the needs of high-quality and high-efficiency maintenance. Utility Model Content

[0005] The purpose of this invention is to provide a hydraulic tool for disassembling and assembling coaxial multiple bushings for aircraft engine mounting, which can more efficiently disassemble and assemble the bushings of aircraft engine mounting.

[0006] The objective of this utility model is achieved through the following technical solution:

[0007] A hydraulic tool for disassembling and assembling coaxial multi-shields for aircraft engine mounting is characterized by comprising a hydraulic actuator, a positioning frame, an adjustable push rod, and a contact head. The positioning frame is connected to the hydraulic actuator, and its front end extends forward to the front of the hydraulic actuator and is provided with a top plate. The top plate is used to abut against the side of the connecting plate of the aircraft engine mounting away from the hydraulic actuator. The adjustable push rod is connected to the hydraulic actuator, and is driven forward by the hydraulic actuator during bushing disassembly and assembly. The adjustable push rod can be adjusted in front and back position relative to the hydraulic actuator. The contact head is installed at the front end of the adjustable push rod and is used to abut against the bushing. The front part of the contact head can be fitted into the bushing.

[0008] A further technical solution of this utility model is as follows: the hydraulic actuator includes a hydraulic cylinder, a piston, and a return spring. The hydraulic cylinder is provided with an oil port. The piston and the return spring are fitted inside the hydraulic cylinder. The return spring provides the force required for the piston to return to its original position. The piston is provided with a threaded through hole in the middle. An adjustable push rod passes through the middle of the hydraulic cylinder. A portion of the adjustable push rod located inside the hydraulic cylinder is provided with an external thread. The adjustable push rod is threadedly connected to the threaded through hole of the piston through the external thread.

[0009] A further technical solution of this utility model is as follows: the front and rear ends of the hydraulic cylinder are respectively provided with through holes, and a bushing is threadedly connected to the through hole, and an adjustable push rod passes through the bushing.

[0010] A further technical solution of this utility model is as follows: a guide sleeve is provided at the inner end of one of the perforations, and a connecting tube is provided in the middle of the piston. The connecting tube is fitted into the guide sleeve, and the middle of the connecting tube is a threaded through hole.

[0011] A further technical solution of this utility model is: a limiting boss that matches the central hole of the bushing is provided on the front of the contact pressure head.

[0012] A further technical solution of this utility model is: the contact head includes a contact head for disassembly and a contact head for installation.

[0013] A further technical solution of this utility model is as follows: the positioning frame is provided with a limiting rear plate and a limiting front plate located on the same side, the limiting rear plate and the limiting front plate are respectively clamped on the front and rear end faces of the hydraulic cylinder, and the ends of the limiting rear plate and the limiting front plate are respectively provided with semi-circular slots, which are engaged with the bushing.

[0014] A further technical solution of this utility model is: a semi-circular notch is provided at the end of the top plate, and the semi-circular notch is located outside the bushing hole when the bushing is disassembled or assembled.

[0015] A further technical solution of this utility model is as follows: the hydraulic tool also includes a hydraulic pump and a hydraulic pipeline, the hydraulic pump is provided with an oil storage chamber, and the hydraulic pump is connected to the oil port of the hydraulic cylinder through the hydraulic pipeline.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. This utility model uses a hydraulically driven hydraulic actuator to provide powerful and stable power, which can quickly and efficiently complete the disassembly and assembly of the bushing on the aircraft engine, greatly improving maintenance efficiency and significantly shortening maintenance time.

[0018] 2. This utility model restricts the position by cooperating with the positioning frame and the contact pressure head, ensuring the accuracy and stability of the disassembly and assembly operations, improving the precision and quality of disassembly and assembly, reducing damage to engine components, and effectively reducing the risk of component damage.

[0019] 3. This utility model is easy to operate, reduces the workload of maintenance personnel, and improves the convenience and safety of operation. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of the hydraulic tool according to an embodiment of the present invention;

[0021] Figure 2 This is a front view schematic diagram of the hydraulic tool removing the hydraulic pipeline and hydraulic pump according to an embodiment of the present utility model;

[0022] Figure 3 yes Figure 2 Schematic diagram of the cross section at point AA;

[0023] Figure 4 This is a schematic diagram of the positioning frame according to an embodiment of the present utility model;

[0024] Figure 5 This is a schematic diagram of the contact pressure head according to an embodiment of the present invention;

[0025] Figure 6 This is a schematic diagram of the structure of the bushing for disassembling an aircraft engine mounting according to this utility model;

[0026] Figure 7 This is a front view schematic diagram of the process of disassembling the bushing of the aircraft engine mounting according to this utility model;

[0027] Figure 8 yes Figure 7 Schematic diagram of the cross section at point BB;

[0028] Figure 9 This is a structural schematic diagram of the installation of the bushing for the aircraft engine mounting according to this utility model;

[0029] Figure 10 This is a front view schematic diagram of the installation of the bushing for the aircraft engine mounting according to this utility model;

[0030] Figure 11 yes Figure 10 A cross-sectional view at point CC.

[0031] Meaning of the labels in the attached diagram:

[0032] 1-Hydraulic actuator; 1.1-Oil port; 1.2-Shaft sleeve; 1.3-Return spring; 1.4-Hydraulic cylinder; 1.4.1-Guide sleeve; 1.5-Piston; 1.5.1-Connecting pipe; 2-Adjustable push rod; 2.1-Contact head for disassembly; 2.2-Contact head for installation; 2.3-Connecting end; 2.4-Hexagonal head; 2.5-Limiting boss; 3-Positioning frame; 3.1-Top plate; 3.2-Limiting rear plate; 3.3-Bearing plate; 3.4-Limiting front plate; 3.5-Reinforcing rib; 3.6-Semi-circular groove; 3.7-Semi-circular notch; 4-Hydraulic pipeline; 5-Hydraulic pump; 5.1-Oil reservoir; 5.2-Pressure supply and release control knob; 6-Aircraft engine mount; 6.1-Connecting plate; 6.2-Bushing hole; 6.3-Bushing. Detailed Implementation

[0033] The present invention will be further described below with reference to embodiments.

[0034] In the description of this utility model, it should be understood that the directional descriptions, such as up, down, front, back, left, right, etc., indicate the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0035] In the description of this utility model, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. If "first" or "second" is used in the description, it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0036] In the description of this utility model, unless otherwise explicitly defined, terms such as "setting," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0037] Example:

[0038] like Figures 1 to 5 The hydraulic tool shown in this embodiment is used for assembling and disassembling coaxial bushings for aircraft engines. It includes a hydraulic actuator 1, a positioning frame 3, an adjustable push rod 2, a contact pressure head, a hydraulic pump 5, and hydraulic lines 4.

[0039] The hydraulic actuator 1 includes a hydraulic cylinder 1.4, a piston 1.5, and a return spring 1.3. The hydraulic cylinder 1.4 has an oil port 1.1 near its rear end. The piston 1.5 and the return spring 1.3 are fitted together inside the hydraulic cylinder 1.4. The piston 1.5 can move within the hydraulic cylinder 1.4. The return spring 1.3 is located on the side of the piston 1.5 away from the oil port 1.1, and provides the force required for the piston 1.5 to return to its original position.

[0040] The piston 1.5 has a rearwardly extending connecting pipe 1.5.1 in the middle, with a threaded through hole in the middle. The hydraulic cylinder 1.4 has through holes at both ends, with bushings 1.2 at each through hole. The bushings 1.2 are threadedly connected to the through holes, with their heads protruding beyond the end face of the hydraulic cylinder 1.4. A guide sleeve 1.4.1 is located inside the through hole at the rear end. The connecting pipe 1.5.1 in the middle of the piston 1.5 fits into the guide sleeve 1.4.1. The sliding fit between the guide sleeve 1.4.1 and the connecting pipe 1.5.1 makes the movement of the piston 1.5 more stable.

[0041] The adjustable push rod 2 passes through the bushing 1.2. A portion of the adjustable push rod 2 located inside the hydraulic cylinder 1.4 has external threads. The adjustable push rod 2 is threadedly connected to the threaded through hole of the piston 1.5 via these external threads. The forward and backward position can be adjusted by rotating the adjustable push rod 2. In this embodiment, the rear end of the adjustable push rod 2 has a hexagonal square head 2.4, allowing the operator to better rotate the adjustable push rod 2 by gripping the hexagonal square head 2.4.

[0042] Of course, conventional sealing rings should also be designed at each connection point of the hydraulic cylinder 1.4 to ensure that the hydraulic oil does not leak.

[0043] Hydraulic pump 5 and hydraulic pipeline 4 are both conventional components in hydraulic drive. Hydraulic pump 5 has an oil storage chamber 5.1. Hydraulic pump 5 is connected to the oil port 1.1 of hydraulic cylinder 1.4 through hydraulic pipeline 4. Hydraulic pump 5 is equipped with pressure supply and pressure release operation knob 5.2 for convenient operation and control by the operator.

[0044] The adjustable push rod 2 has a threaded connection end 2.3 at its front end. The rear of the contact head is threadedly connected to the connection end 2.3 of the adjustable push rod 2 through a threaded hole. The front of the contact head has a limiting boss 2.5. The outer diameter of the limiting boss 2.5 is equal to the diameter of the central hole of the bushing 6.3. The limiting boss 2.5 can fit into the bushing 6.3, thereby limiting the position between the contact head and the bushing 6.3 and preventing loosening or slippage during operation. In this embodiment, the contact head includes a disassembly contact head 2.1 and an installation contact head 2.2. The disassembly contact head 2.1 is used when disassembling the bushing 6.3, and the installation contact head 2.2 is used when installing the bushing 6.3. The limiting bosses 2.5 of the disassembly contact head 2.1 and the installation contact head 2.2 are the same size. The difference lies in the overall outer diameter. The outer diameter of the installation contact head 2.2 is larger than that of the disassembly contact head 2.1. The outer diameter of the disassembly contact head 2.1 must be smaller than the diameter of the bushing hole 6.2 of the aircraft engine mounting.

[0045] like Figure 4 As shown, the positioning frame 3 in this embodiment is provided with a support plate 3.3, a limiting rear plate 3.2, a limiting front plate 3.4, and a top plate 3.1. The limiting rear plate 3.2 is located at the rear end of the support plate 3.3, and the limiting front plate 3.4 is located near the rear end of the support plate 3.3. The ends of the limiting rear plate 3.2 and the limiting front plate 3.4 are respectively provided with semi-circular slots 3.6. In use, the limiting rear plate 3.2 and the limiting front plate 3.4 are respectively clamped on the front and rear end faces of the hydraulic cylinder 1.4, and the semi-circular slots 3.6 are engaged with the bushing 1.2. At this time, the front end of the positioning frame 3 extends forward to the front of the hydraulic actuator 1. The top plate 3.1 is located at the front end of the load-bearing plate 3.3. The end of the top plate 3.1 is provided with a semi-circular notch 3.7. When the bushing 6.3 is disassembled or assembled, the top plate 3.1 abuts against the side of the connecting plate 6.1 of the aircraft engine sling 6 away from the hydraulic actuator 1. The semi-circular notch 3.7 is located outside the bushing hole 6.2.

[0046] In this embodiment, reinforcing ribs 3.5 are provided at the connection positions of the limiting front plate 3.4 and the load-bearing plate 3.3, and at the connection positions of the top plate 3.1 and the load-bearing plate 3.3, respectively, to strengthen the structure.

[0047] The method of using the hydraulic tool for assembling and disassembling coaxial multiple bushings for aircraft engines in this embodiment is as follows:

[0048] like Figures 6 to 8As shown, when disassembling bushing 6.3, first align the positioning frame 3 with the position of the bushing 6.3 to be disassembled on the aircraft engine mount 6. Connect the disassembly contact head 2.1 to the front end of the adjustable push rod 2. The disassembly contact head 2.1 will approach the bushing 6.3 to be disassembled. Then rotate the adjustable push rod 2 so that the disassembly contact head 2.1 abuts against the bushing 6.3 to be disassembled. The limiting boss 2.5 of the disassembly contact head 2.1 is embedded in the bushing 6.3 to lock the position. Then operate the pressure supply and pressure release operation knob 5.2 to the pressure supply position. The oil in the oil reservoir 5.1 supplies pressure to the hydraulic cylinder 1.4 through the hydraulic pump 5 and hydraulic pipeline 4. Under the action of hydraulic pressure, the piston 1.5 overcomes the action of the return spring 1.3, causing the adjustable push rod 2 to slowly and steadily push the bushing 6.3, and finally push the bushing 6.3 out of the bushing hole 6.2, completing the disassembly work. After the work is completed, operate the pressure supply and release control knob 5.2 to the release position, and the piston 1.5 will be reset under the action of the return spring 1.3.

[0049] like Figures 9 to 11 As shown, when installing bushing 6.3, the installation contact head 2.2 is selected. The operation process is similar to the disassembly process of bushing 6.3. The adjustable push rod 2 is pushed by hydraulic pressure, and then the bushing 6.3 is pushed into bushing hole 6.2 by the installation contact head 2.2 to complete the installation.

[0050] The above embodiments of this utility model are not intended to limit the scope of protection of this utility model. The implementation of this utility model is not limited thereto. All other modifications, substitutions or alterations made to the above structure of this utility model based on the above content of this utility model and in accordance with the common technical knowledge and conventional means in the field, without departing from the basic technical idea of ​​this utility model, shall fall within the scope of protection of this utility model.

Claims

1. A hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines, characterized in that: The device includes a hydraulic actuator, a positioning frame, an adjustable push rod, and a contact head. The positioning frame is connected to the hydraulic actuator, and its front end extends forward to the front of the hydraulic actuator and is provided with a top plate. The top plate is used to abut against the side of the connecting plate of the aircraft engine mount away from the hydraulic actuator. The adjustable push rod is connected to the hydraulic actuator and is driven forward by the hydraulic actuator when the bushing is installed or removed. The adjustable push rod can be adjusted in front and back position relative to the hydraulic actuator. The contact head is installed at the front end of the adjustable push rod and is used to abut against the bushing. The front part of the contact head can be fitted into the bushing.

2. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 1, characterized in that: The hydraulic actuator includes a hydraulic cylinder, a piston, and a return spring. The hydraulic cylinder has an oil port. The piston and the return spring are fitted inside the hydraulic cylinder. The return spring provides the force required for the piston to return to its original position. The piston has a threaded through hole in the middle. The adjustable push rod passes through the middle of the hydraulic cylinder. A portion of the adjustable push rod located inside the hydraulic cylinder has an external thread. The adjustable push rod is threadedly connected to the threaded through hole of the piston through the external thread.

3. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 2, characterized in that: The hydraulic cylinder has through holes at the front and rear ends, and bushings are threaded into the through holes. The adjustable push rod passes through the bushings.

4. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 3, characterized in that: One of the perforations has a guide sleeve at its inner end, and the piston has a connecting tube in the middle. The connecting tube is fitted into the guide sleeve, and the middle of the connecting tube is the threaded through hole.

5. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 1, characterized in that: The front of the contact head is provided with a limiting boss that matches the central hole of the bushing.

6. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 1, characterized in that: The contact head includes a disassembly contact head and an installation contact head.

7. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 3, characterized in that: The positioning frame is provided with a limiting rear plate and a limiting front plate located on the same side. The limiting rear plate and the limiting front plate are respectively clamped on the front and rear end faces of the hydraulic cylinder. The ends of the limiting rear plate and the limiting front plate are respectively provided with semi-circular slots, which are engaged with the bushing.

8. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 1, characterized in that: The top plate has a semi-circular notch at its end, and the semi-circular notch is located outside the bushing hole when the bushing is installed or removed.

9. The hydraulic tool for assembling and disassembling coaxial multi-bushings for aircraft engines according to claim 2, characterized in that: The hydraulic tool also includes a hydraulic pump and hydraulic lines. The hydraulic pump has an oil storage chamber and is connected to the oil port of the hydraulic cylinder through the hydraulic lines.

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