Lifting device for aircraft engine maintenance

Abstract

A lifting device for aircraft engine maintenance belongs to the field of aircraft maintenance equipment and comprises a base and an adjusting platform, a magnetic lifting assembly is fixedly arranged in the middle of the base, the top end of the magnetic lifting assembly is detachably connected with the adjusting platform, and a plurality of positioning supports are mounted on the adjusting platform; the magnetic attraction lifting assembly comprises a first lifting unit fixedly arranged on the base, a first magnetic attraction unit is fixedly installed at the top end of the first lifting unit and used for being fixed to the bottom of the adjusting platform in a magnetic attraction mode, the height of the adjusting platform can be controlled through the first lifting unit, and the height of the adjusting platform can be adjusted through the arrangement of the first magnetic attraction unit. The base and the adjusting platform are rapidly disassembled and assembled, the aircraft engine can be hoisted to the adjusting platform in advance, the modular replacement effect is achieved, the overhaul and maintenance time is greatly shortened, and the working efficiency is improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance equipment technology, and in particular to a lifting device for aircraft engine maintenance. Background Technology

[0002] The aircraft engine is the heart of an aircraft. When the parts of the aircraft engine are damaged or malfunction, the engine needs to be inspected and repaired. During the inspection and repair of the aircraft engine, it is necessary to raise the aircraft engine using a lifting device to facilitate a comprehensive inspection of the aircraft engine, thereby facilitating subsequent maintenance.

[0003] Currently, lifting devices for aircraft engine maintenance have been developed. These devices typically consist of a base, a lifting drive unit, and a support base. The support base has a support section for supporting the aircraft engine. The support base is connected to the base via the lifting drive unit, which allows the height of the support base to be changed under the action of the lifting drive unit, thereby lifting the aircraft engine to facilitate maintenance.

[0004] However, the existing aircraft engine maintenance lifting device has its support base, lifting drive unit and base connected as one unit. Only after the aircraft engine on the support base has been inspected and lifted away can other aircraft engines to be inspected be lifted onto the support base. Since the aircraft engine needs to be positioned and supported when lifted onto the support base, the process of installing and positioning the aircraft engine on the support base takes a long time, which makes the entire inspection process of the aircraft engine take a long time and seriously affects work efficiency. Utility Model Content

[0005] To address the technical problem in the existing aircraft engine maintenance lifting devices mentioned above, where the installation and positioning process of the aircraft engine on the support is time-consuming, resulting in a long maintenance process and seriously affecting work efficiency, this utility model provides an aircraft engine maintenance lifting device.

[0006] The technical solution of this utility model is as follows:

[0007] This utility model provides a lifting device for aircraft engine maintenance, including a base and an adjustment platform. A magnetic lifting assembly is fixedly installed in the middle of the base, and the top of the magnetic lifting assembly is detachably connected to the adjustment platform. Several positioning brackets are installed on the adjustment platform. The magnetic lifting assembly includes a first lifting unit fixedly installed on the base, and a first magnetic unit is fixedly installed at the top of the first lifting unit. The first magnetic unit is used to magnetically fix to the bottom of the adjustment platform. The first magnetic unit enables a detachable connection between the adjustment platform and the magnetic lifting assembly. In conjunction with the first lifting unit, it can also drive the adjustment platform to adjust its height to meet the needs of aircraft engine maintenance. At the same time, the detachable connection between the adjustment platform and the magnetic lifting assembly allows the aircraft engine to be hoisted onto the adjustment platform in advance. After the maintenance of one aircraft engine is completed, the adjustment platform on the base and the aircraft engine above it can be hoisted away as a whole, and the other engine to be maintained and the adjustment platform below it can be hoisted onto the base as a whole, achieving a modular replacement effect, greatly reducing maintenance time and improving work efficiency.

[0008] Preferably, several lifting rings are fixed on both sides of the upper surface of the adjustment platform, which facilitates the use of lifting equipment to lift the adjustment platform and the aircraft engine on it as a whole. The engine to be repaired can be quickly lifted to the adjustment platform, and it can also be quickly lifted away after the repair is completed. This further improves the convenience of modular replacement, saves time, and improves work efficiency.

[0009] Preferably, a constraint groove is provided on each side of the upper surface of the adjustment platform, and the constraint groove runs through the adjustment platform. Several positioning guide mechanisms are fixed on the base. The top of the positioning guide mechanism is inserted into the constraint groove. The positioning guide mechanism cooperates with the constraint groove to play a role in precise positioning when the adjustment platform is placed on the base, preventing the adjustment platform from shifting on the base, ensuring that its installation position is accurate, providing a stable foundation for subsequent aircraft engine maintenance work, ensuring the smooth progress of the maintenance process, reducing the extra adjustment time caused by inaccurate installation of the adjustment platform, and improving work efficiency.

[0010] Preferably, the positioning and guiding mechanism includes a second lifting unit fixedly mounted on the base. A guide plate is fixedly installed at the telescopic end of the second lifting unit and inserted into the constraint groove. The second lifting unit can adjust the height of the guide plate according to actual needs. When the adjustment platform is not placed, the guide plate can be lowered without affecting other operations. When the adjustment platform is placed, the guide plate is raised to facilitate its insertion into the constraint groove, increasing the flexibility of the device, adapting to different working scenarios and operational needs, further optimizing the installation and positioning process of the adjustment platform, saving installation time, and improving work efficiency.

[0011] Preferably, the guide plate is a long strip-shaped structure, with a length greater than the thickness of the adjustment platform and a thickness not greater than the width of the constraint groove. The top of the guide plate is a conical structure with two inclined surfaces, which can provide sufficient support and guidance range for the adjustment platform, ensuring the stability of the adjustment platform during installation. The conical inclined surface structure at the top can play a guiding role, making it easy for the guide plate to slide quickly and accurately into the constraint groove when the adjustment platform is close to the base, reducing the alignment time during installation and improving installation efficiency.

[0012] Preferably, two support seats are installed on the adjustment platform. One support seat is fixedly connected to the adjustment platform, and the other support seat is slidably connected to the adjustment platform. The two support seats are connected by a spacing adjustment component. The positioning bracket is fixedly installed on the support seats. The spacing between the two support seats can be flexibly adjusted according to different needs, so that the positioning bracket can better adapt to the support and positioning needs of various aircraft engines.

[0013] Preferably, the spacing adjustment assembly includes a first connecting rod and a second connecting rod. The first connecting rod is fixedly installed on the side wall of one support base, and the second connecting rod is fixedly installed on the side wall of another support base. Both the first and second connecting rods are provided with several mounting holes. The first connecting rod has a hollow structure, and the second connecting rod is inserted into the first connecting rod. The first and second connecting rods are connected and limited by a positioning pin. By using the insertion and positioning pin limiting method, the operation is convenient and quick, greatly shortening the adjustment time, improving work efficiency, and also reducing equipment costs and maintenance difficulty.

[0014] Preferably, a support plate is fixed at each end of the base. The support plates are vertically arranged, and the sides of the support plates are fixedly connected to the base through reinforcing frame plates. The vertically arranged support plates increase the stability of the adjustment platform in the initial stage of installation, and the reinforcing frame plates further enhance the connection strength between the support plates and the base, thereby improving the structural stability of the entire device.

[0015] Preferably, a guide cylinder is fixedly mounted on the base, and a magnetic support rod is slidably connected inside the guide cylinder. A second magnetic unit is located at the top of the magnetic support rod, and a return spring is fixedly connected between the magnetic support rod and the guide cylinder. When the adjustment platform is placed on the base, the magnetic support rod can magnetically attract the bottom of the adjustment platform through the second magnetic unit, providing additional auxiliary support. The return spring allows the magnetic support rod to automatically return to its original position when the adjustment platform is removed. This not only enhances the stability of the connection between the adjustment platform and the base but also provides a buffering effect to some extent, protecting the adjustment platform and aircraft engine from damage during installation and disassembly. It also reduces the operational difficulty during installation and disassembly, saves time, and improves work efficiency.

[0016] Preferably, the positioning bracket includes a frame, and an arc-shaped pad is fixedly provided on the top of the frame. The arc-shaped pad is used to increase the contact support area with the aircraft engine to improve the support stability effect.

[0017] As can be seen from the above technical solutions, the advantages of this utility model are:

[0018] 1. The base is detachably connected to the adjustment platform via a magnetic lifting assembly. The first magnetic unit enables a detachable connection between the adjustment platform and the magnetic lifting assembly. In conjunction with the first lifting unit, it also allows for height adjustment of the adjustment platform to meet the needs of aircraft engine maintenance. Furthermore, the detachable connection between the adjustment platform and the magnetic lifting assembly allows the aircraft engine to be pre-installed on the adjustment platform. After one aircraft engine has been maintained, the adjustment platform and the aircraft engine on top of it can be lifted away as a whole, and the other engine to be maintained and its adjustment platform below it can be lifted onto the base. This modular replacement significantly reduces maintenance time and improves work efficiency.

[0019] 2. The adjustment platform is equipped with a constraint groove, and the base is equipped with a positioning guide mechanism. Through the cooperation of the positioning guide mechanism and the constraint groove, the adjustment platform can be accurately positioned when it is placed on the base, preventing the adjustment platform from shifting on the base and ensuring that its installation position is accurate. This provides a stable foundation for subsequent aircraft engine maintenance work, ensures the smooth progress of the maintenance process, reduces the extra adjustment time caused by inaccurate installation of the adjustment platform, and improves work efficiency. Attached Figure Description

[0020] To more clearly illustrate the technical solution of this utility model, the drawings used in the description will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the overall structure of the lifting device for aircraft engine maintenance according to one or more embodiments of the present invention.

[0022] Figure 2 This is a front view structural schematic diagram of a lifting device for aircraft engine maintenance according to one or more embodiments of the present invention.

[0023] Figure 3 This is a top view schematic diagram of the lifting device for aircraft engine maintenance according to one or more embodiments of the present invention;

[0024] Figure 4This is a structural diagram of the base position according to one or more embodiments of the present invention;

[0025] Figure 5 This is a cross-sectional structural schematic diagram of the support mechanism according to one or more embodiments of the present invention;

[0026] Figure 6 for Figure 1 A partially enlarged structural diagram of location A in the diagram;

[0027] The components represented by the various reference numerals in the diagram are:

[0028] 1. Base; 2. Adjustment platform; 3. Support base; 4. Positioning bracket; 41. Frame; 42. Arc-shaped pad; 5. Magnetic lifting assembly; 51. First lifting unit; 52. First magnetic unit; 6. Guide cylinder; 7. Magnetic support rod; 71. Rod body; 72. Second magnetic unit; 73. Return spring; 8. Lifting ring; 9. Spacing adjustment assembly; 91. First connecting rod; 92. Second connecting rod; 93. Mounting hole; 94. Positioning pin; 10. Slide rail; 11. Constraint groove; 12. Positioning guide mechanism; 121. Second lifting unit; 122. Guide plate; 13. Support plate; 14. Reinforcing frame plate. Detailed Implementation

[0029] To make the objectives, features, and advantages of this utility model more apparent and understandable, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this patent, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this patent.

[0030] Example 1

[0031] In a typical embodiment of this utility model, such as Figures 1-6As shown, a lifting device for aircraft engine maintenance is proposed, comprising: a base 1, an adjustment platform 2, a positioning bracket 4, a magnetic lifting assembly 5, and a support mechanism. The magnetic lifting assembly 5 is vertically arranged and fixedly installed in the middle position of the base 1 for detachable connection with the adjustment platform 2 and for driving the adjustment platform 2 to rise and fall. Several positioning brackets 4 are provided and installed on the adjustment platform 2 for supporting and positioning the aircraft engine. The positioning bracket 4 includes a frame 41 and an arc-shaped pad 42 fixedly installed on the top of the frame 41. The arc-shaped pad 42 is used to increase the contact support area with the aircraft engine to improve the support stability effect. Several support mechanisms are provided and vertically fixedly installed on the base 1, and distributed on both sides of the magnetic lifting assembly 5 for auxiliary support of the adjustment platform 2 and to improve the support stability of the adjustment platform 2 during the assembly process.

[0032] like Figure 4 As shown, the magnetic lifting assembly 5 includes a first lifting unit 51 and a first magnetic unit 52. The first lifting unit 51 is vertically fixed at the center of the base 1. In this embodiment, the first lifting unit 51 is a hydraulic telescopic cylinder structure, and the first magnetic unit 52 is an electromagnet structure. The first magnetic unit 52 is fixedly installed on the telescopic end of the first lifting unit 51 by welding, bolt connection, flange connection, etc. The first magnetic unit 52 is used to magnetically fix to the bottom of the adjustment platform 2. The first lifting unit 51 can drive the first magnetic unit 52 to rise and fall, so as to change the height position of the first magnetic unit 52, thereby driving the adjustment platform 2 to rise and fall to meet different working needs.

[0033] The first magnetic suction unit 52 enables a detachable connection between the adjustment platform 2 and the magnetic lifting assembly 5. In conjunction with the first lifting unit 51, it also allows the adjustment platform 2 to be adjusted in height to meet the needs of aircraft engine maintenance. At the same time, the detachable connection between the adjustment platform 2 and the magnetic lifting assembly 5 allows the aircraft engine to be hoisted onto the adjustment platform 2 in advance. After the maintenance of one aircraft engine is completed, the adjustment platform 2 on the base 1 and the aircraft engine above it can be hoisted away as a whole, and the other engine to be maintained and the adjustment platform 2 below it can be hoisted onto the base 1 as a whole, achieving a modular replacement effect, greatly reducing maintenance time and improving work efficiency.

[0034] The support mechanism includes a guide cylinder 6 and a magnetic support rod 7. The guide cylinder 6 is vertically fixed on the base 1. The bottom end of the magnetic support rod 7 is inserted into the guide cylinder 6, and the magnetic support rod 7 and the guide cylinder 6 are slidably connected. The top end of the magnetic support rod 7 is used to magnetically connect with the bottom of the adjustment platform 2, thereby providing auxiliary support for the adjustment platform 2, increasing the support points, improving support stability, and preventing the adjustment platform 2 from tilting when it is hoisted onto the base 1.

[0035] like Figure 5 As shown, the magnetic support rod 7 includes a rod body 71 and a second magnetic unit 72. The rod body 71 is hollow inside and is slidably disposed inside the guide cylinder 6. The second magnetic unit 72 is an electromagnet structure and is fixedly installed at the top of the rod body 71 for magnetic connection with the adjustment platform 2, thereby improving the connection stability between the adjustment platform 2 and the magnetic support rod 7. A return spring 73 is installed inside the rod body 71. One end of the return spring 73 is fixedly connected to the inside of the rod body 71, and the other end of the return spring 73 is fixedly connected to the base 1. Thus, when the raised adjustment platform 2 is separated from the magnetic lifting assembly 5, the rod body 71 can be driven to self-reset under the action of the return spring 73.

[0036] Several lifting rings 8 are fixed on both sides of the upper surface of the adjustment platform 2 for lifting the adjustment platform 2 and the aircraft engine placed on the adjustment platform 2. Figure 3 As shown, a constraint groove 11 is provided on each side of the upper surface of the adjustment platform 2. The two constraint grooves 11 are parallel to each other and extend along the length of the adjustment platform 2. The constraint groove 11 penetrates the adjustment platform 2 to cooperate with the positioning guide mechanism 12 to realize the installation positioning of the adjustment platform 2 and ensure the installation accuracy and stability of the adjustment platform 2.

[0037] In this embodiment, four positioning guide mechanisms 12 are provided. The positioning guide mechanisms 12 are vertically fixed on the base 1, and the four positioning guide mechanisms 12 are arranged in a four-corner arrangement. The four positioning guide mechanisms 12 are distributed on both sides of the upper surface of the base 1. The positioning guide mechanisms 12 are used to insert into the constraint groove 11 of the adjustment platform 2 to guide and position the adjustment platform 2.

[0038] like Figure 4As shown, the positioning and guiding mechanism 12 includes a second lifting unit 121 and a guide plate 122. In this embodiment, the second lifting unit 121 is a hydraulic telescopic cylinder structure. The second lifting unit 121 is vertically fixed on the base 1 and is located below the corresponding constraint groove 11. The guide plate 122 is vertically fixed on the telescopic end of the second lifting unit 121. The guide plate 122 is a long strip structure. The length of the guide plate 122 is greater than the thickness of the adjusting platform 2, and the thickness of the guide plate 122 is not greater than the width of the constraint groove 11. The top of the guide plate 122 is a conical structure with two inclined surfaces to serve as a guide, facilitating the insertion of the guide plate 122 and its passage through the constraint groove 11. The corners of the guide plate 122 are rounded to avoid scratching the adjustment platform 2. Specifically, when the adjustment platform 2 is hoisted onto the base 1 for installation, the guide plate 122 on the positioning guide mechanism 12 is inserted into the corresponding constraint groove 11, thereby using the guide plate 122 to position and constrain the position of the adjustment platform 2, ensuring the assembly and docking accuracy between the adjustment platform 2 and the base 1.

[0039] like Figure 1 As shown, a support base 3 is installed on the adjustment platform 2, and a positioning bracket 4 is fixedly installed on the support base 3. There are two support bases 3, which are arranged opposite to each other on the adjustment platform 2. One support base 3 is fixedly connected to the adjustment platform 2, and the other support base 3 is slidably connected to the adjustment platform 2. This allows the position between the two support bases 3 to be adjusted according to the needs of aircraft engines of different lengths.

[0040] Specifically, a slide rail 10 is fixedly installed on the upper surface of the adjustment platform 2. One support 3 is slidably connected to the slide rail 10, and another support 3 is fixedly installed on the upper surface of the adjustment platform 2. The two support 3s are connected by a spacing adjustment component 9, thereby allowing the relative position between the two support 3s to be adjusted and positioned as needed. Figure 6 As shown, the spacing adjustment assembly 9 includes a first connecting rod 91, a second connecting rod 92, mounting holes 93, and a positioning pin 94. The first connecting rod 91 is fixedly installed on the side wall of the sliding support 3, and the second connecting rod 92 is fixedly installed on the side wall of the fixed support 3. The first connecting rod 91 and the second connecting rod 92 are parallel to the slide rail 10. The first connecting rod 91 has several mounting holes 93 spaced apart along its length, and the second connecting rod 92 has at least two mounting holes 93. The first connecting rod 91 has a hollow structure, and one end of the second connecting rod 92 is inserted into the first connecting rod 91. The first connecting rod 91 and the second connecting rod 92 are connected and limited by the positioning pin 94. The positioning pin 94 is inserted into the coaxial mounting hole 93, so that the relative position of the two support 3 can be fixed after the relative position of the support 3 is adjusted.

[0041] It is understood that in other embodiments, the first connecting rod 91 can also be fixedly installed on the side wall of the fixed support 3, and the second connecting rod 92 can be fixedly installed on the side wall of the sliding support 3. In actual use, the positioning pin 94 can also be replaced by bolts or other structures. The specific choice can be made according to actual needs, and no further restrictions are imposed here.

[0042] In other embodiments, rope mounting parts can be provided on both sides of the support base 3 or the adjustment platform 2. The rope mounting parts are on the same side as the lifting ring 8 to fix the installation of the rope, thereby using the rope to limit the engine and improve the safety of use. It is understood that the specific structure and shape of the rope mounting parts can be determined according to the actual design requirements, such as a ring structure, etc. No further restrictions are imposed here.

[0043] A support plate 13 is fixed to each end of the base 1. The support plate 13 is vertically arranged and is at the same height as the magnetic lifting assembly 5 when not in operation, so as to provide auxiliary support for the bottom of the adjustment platform 2 and improve the installation stability of the adjustment platform 2. Figure 4 As shown, a reinforcing frame plate 14 is also fixedly installed on the base 1. The reinforcing frame plate 14 is inclined, and the side of the support plate 13 is fixedly connected to the base 1 through the reinforcing frame plate 14 to improve the structural strength of the support plate 13.

[0044] The specific working principle is as follows:

[0045] The aircraft engine is placed in the support space formed by the four positioning brackets 4, and the arc-shaped pads 42 on the top of each positioning bracket 4 are in contact with the surface of the aircraft engine, thereby providing sufficient support area and ensuring the stability of the aircraft engine placement.

[0046] Next, the four connecting ropes of the hoisting equipment are connected to the four lifting rings 8 in sequence, and then the hoisting equipment is used to hoist the adjustment platform 2, the support seat 3 on the top of the adjustment platform 2, and the aircraft engine in a unified manner through the four connecting ropes;

[0047] After the adjustment platform 2 is moved to be aligned with the top of the base 1, the hoisting equipment uses four connecting ropes to lower the adjustment platform 2, the support base 3 on the top of the adjustment platform 2, and the aircraft engine until the adjustment platform 2 is stably assembled on the top of the base 1, and then the four connecting ropes are released.

[0048] Before lowering the adjustment platform 2, the second lifting unit 121 is activated, causing the guide plate 122 to move vertically. After moving into place, the guide plate 122 is lowered so that it is inserted into the corresponding constraint groove 11, thereby improving the assembly accuracy of the base 1 and the adjustment platform 2.

[0049] After the base 1 and the adjustment platform 2 are assembled, the first magnetic unit 52 of the magnetic lifting assembly 5 and the second magnetic unit 72 of the magnetic support rod 7 are activated. First, the first magnetic unit 52 and the second magnetic unit 72 are magnetically attracted to the bottom surface of the adjustment platform 2. Then, the first lifting unit 51 is activated. The output end of the first lifting unit 51 is transmitted to the adjustment platform 2 through the first magnetic unit 52, so that the adjustment platform 2, the support seat 3 on the top of the adjustment platform 22, and the aircraft engine are moved upward to meet the maintenance requirements. During the maintenance process, the aircraft engine to be maintained is hoisted to other adjustment platforms 2 using hoisting equipment.

[0050] After an aircraft engine has been repaired, the first lifting unit 51 is reset, and the first magnetic suction unit 52 and the second magnetic suction unit 72 are stopped. The four connecting ropes of the hoisting equipment are reconnected to the four lifting rings 8. Then, the hoisting equipment lifts the adjustment platform 2 and the repaired aircraft engine together through the four connecting ropes. Then, the pre-installed aircraft engine to be repaired and the adjustment platform 2 below it are hoisted as a whole, and the above operation is repeated to achieve modular replacement and improve maintenance efficiency.

[0051] The above description of the disclosed embodiments enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A lifting device for aircraft engine maintenance, comprising: The base (1) and the adjustment platform (2) are characterized in that a magnetic lifting component (5) is fixedly provided at the middle position of the base (1), the top of the magnetic lifting component (5) is detachably connected to the adjustment platform (2), and a number of positioning brackets (4) are installed on the adjustment platform (2). The magnetic lifting assembly (5) includes a first lifting unit (51) fixedly mounted on the base (1), and a first magnetic unit (52) fixedly mounted on the top of the first lifting unit (51). The first magnetic unit (52) is used to magnetically fix to the bottom of the adjustment platform (2).

2. The lifting device for aircraft engine maintenance according to claim 1, characterized in that, Several lifting rings (8) are fixed on both sides of the upper surface of the adjustment platform (2).

3. The lifting device for aircraft engine maintenance according to claim 1, characterized in that, A constraint groove (11) is provided on both sides of the upper surface of the adjustment platform (2). The constraint groove (11) passes through the adjustment platform (2). Several positioning guide mechanisms (12) are fixed on the base (1). The top of the positioning guide mechanism (12) is inserted into the constraint groove (11).

4. The lifting device for aircraft engine maintenance according to claim 3, characterized in that, The positioning guide mechanism (12) includes a second lifting unit (121) fixedly mounted on the base (1). The telescopic end of the second lifting unit (121) is fixedly mounted with a guide plate (122), which is inserted into the constraint groove (11).

5. The lifting device for aircraft engine maintenance according to claim 4, characterized in that, The guide plate (122) is a long strip-shaped structure. The length of the guide plate (122) is greater than the thickness of the adjustment platform (2). The thickness of the guide plate (122) is not greater than the width of the constraint groove (11). The top of the guide plate (122) is a conical structure with two inclined surfaces.

6. The lifting device for aircraft engine maintenance according to claim 1, characterized in that, Two support seats (3) are installed on the adjustment platform (2). One support seat (3) is fixedly connected to the adjustment platform (2), and the other support seat (3) is slidably connected to the adjustment platform (2). The two support seats (3) are connected by a spacing adjustment component (9). The positioning bracket (4) is fixedly installed on the support seat (3).

7. The lifting device for aircraft engine maintenance according to claim 6, characterized in that, The spacing adjustment assembly (9) includes a first connecting rod (91) and a second connecting rod (92). The first connecting rod (91) is fixedly installed on the side wall of a support base (3), and the second connecting rod (92) is fixedly installed on the side wall of another support base (3). The first connecting rod (91) and the second connecting rod (92) are provided with several mounting holes (93). The first connecting rod (91) is a hollow structure, and the second connecting rod (92) is inserted into the first connecting rod (91). The first connecting rod (91) and the second connecting rod (92) are connected and limited by a positioning pin (94).

8. The lifting device for aircraft engine maintenance according to claim 1, characterized in that, A support plate (13) is fixed at each end of the base (1). The support plate (13) is set vertically, and the side of the support plate (13) is fixedly connected to the base (1) through a reinforcing frame plate (14).

9. The lifting device for aircraft engine maintenance according to claim 1, characterized in that, A guide cylinder (6) is fixedly provided on the base (1). A magnetic support rod (7) is slidably connected inside the guide cylinder (6). A second magnetic unit (72) is provided at the top of the magnetic support rod (7). A reset spring (73) is fixedly connected between the magnetic support rod (7) and the guide cylinder (6).

10. The lifting device for aircraft engine maintenance according to claim 1, characterized in that, The positioning bracket (4) includes a frame (41), and an arc-shaped pad (42) is fixedly provided on the top of the frame (41).

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