Clamping bracket for aircraft engine maintenance

Abstract

The clamping bracket for aircraft engine maintenance comprises a maintenance platform, a fixed seat and a movable seat are arranged on the outer wall of the top of the maintenance platform, a fixed ring is fixedly arranged on the outer wall of the top of the fixed seat and the outer wall of the top of the movable seat, and bearings are fixedly arranged on the inner walls of the two sides of the fixed ring. And movable rings are fixedly arranged on inner rings of the two bearings, two fixed supports are fixedly arranged on the inner walls of the two movable rings, and limiting clamping rings are fixedly arranged at the other ends of the two fixed supports. The output shafts of the two synchronous motors drive the gear discs to rotate, the two gear discs drive the movable rings to rotate through the teeth, the two movable rings drive the limiting clamping rings to rotate through the fixing support, the two limiting clamping rings drive the aircraft engine to rotate, and therefore the aircraft engine can be rotated conveniently; parts at different positions of the side face of the engine can be repaired and maintained conveniently, and the airplane does not need to be taken out of the clamping table through hoisting equipment for adjustment.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft maintenance auxiliary equipment, in particular to a clamping bracket for aircraft engine maintenance. Background Art

[0002] It is a highly complex and precise 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 aviation. Every important change in the history of human aviation is closely related to the technological progress of aircraft engines. After more than a hundred years of development, aircraft engines have developed into mature products with extremely high reliability. The aircraft engines in use include turbojet / turbofan engines, turboshaft / turboprop engines, ramjet engines, piston engines and other types.

[0003] There are many aircraft engine parts, and most of them are large in size and weight. Therefore, the engine needs to be lifted during the maintenance process. However, most aircraft engines are circular columnar structures, and their parts are distributed around the engine. During the maintenance of the aircraft engine, the parts need to be inspected. Therefore, the aircraft engine needs to be rotated frequently to adjust the aircraft engine parts to the appropriate angle to facilitate maintenance personnel to maintain the aircraft engine. However, the existing aircraft engine maintenance bracket requires the aircraft engine to be lowered and the rotation angle of the aircraft engine to be adjusted by lifting equipment and manpower, which is extremely inconvenient. Therefore, we propose a clamping bracket for aircraft engine maintenance. Utility Model Content

[0004] The utility model aims to provide a clamping bracket for aircraft engine maintenance to solve the above-mentioned technical deficiencies.

[0005] In order to achieve the above-mentioned purpose, the utility model provides the following technical solutions: a clamping bracket for aircraft engine maintenance, comprising a maintenance platform, a fixed seat and a movable seat are respectively provided on the top outer wall of the maintenance platform, a fixed ring is fixedly provided on the top outer wall of the fixed seat and the movable seat, bearings are fixedly provided on the inner walls on both sides of the fixed ring, movable rings are fixedly provided on the inner rings of the two bearings, two fixed brackets are fixedly provided on the inner walls of the two movable rings, and limiting clamping rings are fixedly provided on the other ends of the two fixed brackets, fixing openings are opened on the outer walls on both sides of the limiting clamping ring, and first hydraulic push rods are fixedly provided on the inner walls of the two fixing openings, the output shafts of the two first hydraulic push rods correspond to each other, the output shafts of the two first hydraulic push rods are fixedly provided with arc clamping blocks through couplings, the outer walls of the two movable rings are fixedly provided with teeth distributed at equal distances, a fixing plate is fixedly provided on one side of the top of the two fixed rings, a synchronous motor is fixedly provided on the top outer wall of the two fixed plates, and the output shafts of the two synchronous motors are fixedly connected with gear plates through couplings.

[0006] Preferably, the bottom outer wall of the fixed seat is fixedly connected to the top outer wall of the maintenance platform, the bottom outer wall of the movable seat is fixedly provided with a guide slider, a guide groove is opened on one side of the top of the maintenance platform, and the inner wall of the guide groove is slidably connected to the outer wall of the guide slider.

[0007] Preferably, a second hydraulic push rod is fixedly provided on the top outer wall of the maintenance platform, and a positioning block is fixedly provided on one side outer wall of the guide slider. The output shaft of the second hydraulic push rod is fixedly connected to the positioning block through a coupling, and the output shaft of the second hydraulic push rod can push the guide slider to slide on the inner wall of the guide groove, so as to adjust the position of the moving seat on the top of the maintenance platform.

[0008] Preferably, the top outer walls of the two fixing rings are provided with docking cuts, the outer wall of the gear plate is meshed with the teeth through the inner wall of the docking cuts, the gear plate is driven to rotate by the output shaft of the synchronous motor, and the gear plate drives the fixing ring to rotate through the teeth.

[0009] Preferably, rubber pads are fixedly provided on the inner walls of the two arc-shaped clamping blocks, which can avoid the outer wall of the aircraft engine from being clamped and can also increase the friction of the arc-shaped clamping blocks to clamp the aircraft engine more tightly.

[0010] In the above technical solution, the technical effects and advantages provided by the utility model are:

[0011] The output shafts of two synchronous motors drive the gear plates to rotate, the two gear plates drive the movable rings to rotate through the teeth, the two movable rings drive the limit clamp rings to rotate through the fixed brackets, and the two limit clamp rings drive the aircraft engine to rotate, so that the aircraft engine can be rotated easily, so as to facilitate the repair and maintenance of parts at different positions on the side of the engine. There is no need to take the aircraft out of the clamping table for adjustment through lifting equipment, which is easy to use and is conducive to shortening the maintenance cycle of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present utility model. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0013] Figure 1 This is a three-dimensional structural schematic diagram of a clamping bracket for aircraft engine maintenance according to the utility model;

[0014] Figure 2 This is a schematic diagram of the structure of a fixing ring of a clamping bracket for aircraft engine maintenance according to the utility model;

[0015] Figure 3The utility model is a schematic diagram of a limit clamp ring structure of a clamping bracket for aircraft engine maintenance.

[0016] Description of reference numerals:

[0017] 1 maintenance platform, 2 fixed seat, 3 moving seat, 4 fixed ring, 5 bearing, 6 movable ring, 7 teeth, 8 fixed bracket, 9 limit clamp ring, 10 fixed port, 11 first hydraulic push rod, 12 arc clamp block, 13 docking incision, 14 fixed plate, 15 synchronous motor, 16 gear plate, 17 guide groove, 18 guide slide block, 19 second hydraulic push rod, 20 positioning block. DETAILED DESCRIPTION

[0018] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0019] Embodiment 1

[0020] Refer to the instruction manual Figure 1-3 A clamping bracket for aircraft engine maintenance comprises a maintenance platform 1, a fixed seat 2 and a movable seat 3 are respectively provided on the top outer wall of the maintenance platform 1, a fixed ring 4 is fixedly provided on the top outer wall of the fixed seat 2 and the movable seat 3, bearings 5 ​​are fixedly provided on the inner walls of both sides of the fixed ring 4, movable rings 6 are fixedly provided on the inner rings of the two bearings 5, two fixed brackets 8 are fixedly provided on the inner walls of the two movable rings 6, and the other ends of the two fixed brackets 8 are fixedly provided with limit clamp rings 9, fixed openings 10 are opened on the outer walls of both sides of the limit clamp ring 9, first hydraulic push rods 11 are fixedly provided on the inner walls of the two fixed openings 10, the output shafts of the two first hydraulic push rods 11 correspond to each other, the output shafts of the two first hydraulic push rods 11 are fixedly provided with arc clamp blocks 12 through couplings, teeth 7 distributed at equal distances are fixedly provided on the outer walls of the two movable rings 6, a fixed plate 14 is fixedly provided on one side of the top of the two fixed rings 4, a synchronous motor 15 is fixedly provided on the top outer wall of the two fixed plates 14, and the output shafts of the two synchronous motors 15 are fixedly connected with gear plates 16 through couplings.

[0021] Embodiment 2

[0022] Based on the first embodiment, the bottom outer wall of the fixed seat 2 is fixedly connected to the top outer wall of the maintenance platform 1, the bottom outer wall of the movable seat 3 is fixedly provided with a guide slider 18, a guide groove 17 is opened on one side of the top of the maintenance platform 1, the inner wall of the guide groove 17 is slidably connected to the outer wall of the guide slider 18, and a second hydraulic push rod 19 is fixedly provided on the top outer wall of the maintenance platform 1, and a positioning block 20 is fixedly provided on the outer wall of one side of the guide slider 18. The output shaft of the second hydraulic push rod 19 is fixedly connected to the positioning block 20 through a coupling, and the output shaft of the second hydraulic push rod 19 can push the guide slider 18 to slide on the inner wall of the guide groove 17, so as to adjust the position of the movable seat 3 on the top of the maintenance platform 1.

[0023] Embodiment 3

[0024] Based on the first embodiment, the top outer walls of the two fixing rings 4 are provided with docking notches 13, the outer wall of the gear plate 16 is meshed with the teeth 7 through the inner wall of the docking notch 13, the gear plate 16 is driven to rotate by the output shaft of the synchronous motor 15, and the gear plate 16 drives the fixing ring 4 to rotate through the teeth 7, and the inner walls of the two arc-shaped clamping blocks 12 are fixed with rubber pads, which can avoid clamping the outer wall of the aircraft engine and at the same time increase the friction of the arc-shaped clamping blocks 12, so that the aircraft engine can be clamped more tightly.

[0025] Working principle of this utility model:

[0026] Refer to the instruction manual Figure 1-3 When in use, first move the aircraft engine to the top of the maintenance platform 1 through the lifting equipment, and position the two ends of the aircraft engine toward the inner wall of the two limit clamps 9, then move one end of the aircraft engine to one side of the fixed seat 2 through the lifting equipment, and then push the moving seat 3 through the output shaft of the second hydraulic push rod 19, and the moving seat 3 slides on the inner wall of the guide groove 17 through the guide slider 18, and the moving seat 3 moves to one side of the fixed seat 2. The two limit clamps 9 are respectively sleeved on the outer walls of the two ends of the aircraft engine. At this time, the output shaft of the first hydraulic push rod 11 is extended, and the output shaft of the first hydraulic push rod 11 clamps the two ends of the aircraft engine through the arc clamp block 12. When the maintenance personnel perform maintenance on the aircraft engine, when it is necessary to maintain the parts of the engine at different angles, the output shafts of the two synchronous motors 15 drive the gear plate 16 to rotate. The two gear plates 16 drive the movable ring 6 to rotate through the teeth 7, and the two movable rings 6 drive the limit clamp ring 9 to rotate through the fixed bracket 8. The two limit clamp rings 9 drive the aircraft engine to rotate, which is convenient for rotating the aircraft engine, so as to facilitate the repair and maintenance of parts at different positions on the side of the engine. There is no need to take the aircraft out of the clamping table for adjustment through the lifting equipment. It is easy to use and is conducive to shortening the maintenance cycle of the aircraft engine. After the aircraft engine is overhauled, the aircraft engine is fixed by the lifting equipment, and then the output shafts of the two first hydraulic push rods 11 are retracted to stop clamping the aircraft engine. At this time, the output shaft of the second hydraulic push rod 19 is retracted to move the movable seat 3 away from the fixed seat 2, and the aircraft engine is taken out from the inside of the two limit clamp rings 9 in cooperation with the lifting equipment, and the repaired aircraft engine is moved to the specified position through the lifting equipment.

[0027] The above only describes some exemplary embodiments of the present invention by way of illustration. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A clamping bracket for aircraft engine maintenance, comprising a maintenance platform (1), characterized in that: The top outer wall of the maintenance platform (1) is respectively provided with a fixed seat (2) and a movable seat (3), the top outer walls of the fixed seat (2) and the movable seat (3) are fixedly provided with a fixed ring (4), the inner walls on both sides of the fixed ring (4) are fixedly provided with bearings (5), the inner rings of the two bearings (5) are fixedly provided with movable rings (6), the inner walls of the two movable rings (6) are fixedly provided with two fixed brackets (8), the other ends of the two fixed brackets (8) are fixedly provided with a limit clamp ring (9), the outer walls on both sides of the limit clamp ring (9) are provided with fixed openings (10), and the two fixed openings (10) are provided with a plurality of fixed brackets (8). ) is fixedly provided with a first hydraulic push rod (11) on the inner wall thereof, the output shafts of the two first hydraulic push rods (11) correspond to each other, the output shafts of the two first hydraulic push rods (11) are fixedly provided with an arc clamping block (12) via a coupling, the outer walls of the two movable rings (6) are fixedly provided with teeth (7) distributed at equal distances, a fixing plate (14) is fixedly provided on one side of the top of the two fixing rings (4), a synchronous motor (15) is fixedly provided on the outer wall of the top of the two fixing plates (14), and the output shafts of the two synchronous motors (15) are fixedly connected with a gear plate (16) via a coupling.

2. The clamping bracket for aircraft engine maintenance according to claim 1, characterized in that: The bottom outer wall of the fixed seat (2) is fixedly connected to the top outer wall of the maintenance platform (1); the bottom outer wall of the movable seat (3) is fixedly provided with a guide slider (18); a guide groove (17) is provided on one side of the top of the maintenance platform (1); the inner wall of the guide groove (17) is slidably connected to the outer wall of the guide slider (18).

3. The clamping bracket for aircraft engine maintenance according to claim 2, characterized in that: A second hydraulic push rod (19) is fixedly provided on the top outer wall of the maintenance platform (1), a positioning block (20) is fixedly provided on one side outer wall of the guide slide block (18), and an output shaft of the second hydraulic push rod (19) is fixedly connected to the positioning block (20) via a coupling.

4. The clamping bracket for aircraft engine maintenance according to claim 1, characterized in that: The top outer walls of the two fixing rings (4) are provided with butt joint cutouts (13), and the outer wall of the gear plate (16) is meshed with the teeth (7) through the inner wall of the butt joint cutouts (13).

5. The clamping bracket for aircraft engine maintenance according to claim 1, characterized in that: Rubber pads are fixedly provided on the inner walls of the two arc-shaped clamping blocks (12).

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