Aircraft landing gear shock strut testing device

Abstract

The utility model relates to the field of aircraft landing gear shock struts, in particular to an aircraft landing gear shock strut testing device, which is characterized in that an insertion column is mounted on the upper end face of a bottom table, the insertion column is mounted at the bottom of a cylinder barrel in an insertion manner, a piston rod is mounted in the cylinder barrel in a sliding fit manner, and fixing grooves are symmetrically formed in the front and back of the upper end face of the bottom table; a first sliding block is installed in the fixing groove in a sliding fit mode, an L-shaped frame is installed on the upper end face of the first sliding block, a limiting ring is installed at the other end of the L-shaped frame, a containing groove is formed in the upper end face of the first sliding block, and a pressing plate is arranged in the containing groove. According to the utility model, the structure of the insertion column, the limiting ring and the limiting rod is adopted, so that the shock strut is limited and fixed, the shock strut is prevented from shaking in the testing process, and the stability of the device is further improved.

Description

Technical Field

[0001] The utility model relates to the field of aircraft landing gear shock struts, and particularly relates to a testing device for aircraft landing gear shock struts. Background Technique

[0002] When repairing an aircraft landing gear, if it involves the repair of the sealing components of the shock strut, it is necessary to conduct a seal ring positioning test on the shock strut to ensure the oil seal and airtightness of the installed sealing components.

[0003] Chinese Patent discloses a testing device for aircraft landing gear shock struts (authorization publication number CN 209542076U). This patented technology can solve the problems that the current construction methods in the industry need to rely on a relatively complex hydraulic control system, and the testing process requires multiple transfers and fixations, with huge operation time and labor consumption, which is not conducive to the development of standardized and process-based construction.

[0004] In the existing testing process, the bottom of the shock strut is mostly fixed, and the fixing effect is not ideal, resulting in a risk that the shock strut is prone to deviation and tipping, and the problem that it is inconvenient to disassemble after the test. Content of the Utility Model

[0005] To solve the above technical problems, the utility model provides a testing device for aircraft landing gear shock struts, which includes a bottom platform and a piston rod. A plug post is installed on the upper end surface of the bottom platform, and the plug post is installed at the bottom of the cylinder barrel by means of plugging. The piston rod is installed in the cylinder barrel by means of sliding fit. Fixed grooves are symmetrically arranged on the front and rear of the upper end surface of the bottom platform. A first slider is installed in the fixed groove by means of sliding fit. An L-shaped frame is installed on the upper end surface of the first slider. A limiting ring is installed at the other end of the L-shaped frame. A placement groove is arranged on the upper end surface of the first slider, and a pressing plate is arranged in the placement groove. First hydraulic cylinders are symmetrically installed on the left and right of the upper end surface of the bottom platform. A connecting plate is installed at the output end of the first hydraulic cylinder, and the piston rod is arranged at the bottom of the connecting plate.

[0006] Preferably: The pressing plate is screwed to the bottom platform through a limiting rod, and the limiting rods are symmetrically arranged about the front and rear of the bottom platform.

[0007] Preferably: A connecting column is installed in the middle of the upper end surface of the connecting plate. The connecting column is connected to the upper end surface of the piston rod through a limiting bolt. A top column is installed on the upper end surface of the limiting bolt. A slot is arranged on the outer side wall of the top column. A movable plate is installed on the upper end surface of the connecting plate by means of sliding fit. A plug rod is installed on the right end surface of the movable plate, and the plug rod is arranged in the slot by means of plugging. A top plate is installed on the upper end surface of the top column. A bottom groove is arranged at the bottom of the top plate. A spring rod is installed on the outer side wall of the plug rod, and the spring rod is installed in the bottom groove by means of plugging.

[0008] The technical effects and advantages of the utility model:

[0009] 1. In the present utility model, a structure of an insertion post, a limit ring and a limit rod is adopted to limit and fix the shock absorber strut, so as to prevent the shock absorber strut from shaking during the test, and thus from toppling over and causing injury to personnel, further improving the stability of the device.

[0010] 2. In the present utility model, a structure of a limit bolt and an insertion rod is adopted, which facilitates the removal of the shock absorber strut for replacement after the test is completed, and improves the stability of the installation of the limit bolt through the insertion rod structure. Description of the Drawings

[0011] Figure 1 is the front view of the structure of a shock absorber strut test device for an aircraft landing gear provided by an embodiment of the present application;

[0012] Figure 2 is the top view of the structure of a shock absorber strut test device for an aircraft landing gear provided by an embodiment of the present application;

[0013] Figure 3 is the front sectional view of a shock absorber strut test device for an aircraft landing gear provided by an embodiment of the present application;

[0014] Figure 4 is the left sectional view of a shock absorber strut test device for an aircraft landing gear provided by an embodiment of the present application;

[0015] Figure 5 is a partial enlarged view of area A in a shock absorber strut test device for an aircraft landing gear provided by an embodiment of the present application Figure 3 in;

[0016] In the figure: 1. Base table; 2. Piston rod; 11. Cylinder barrel; 12. First slider; 13. Limit ring; 14. Pressure plate; 15. First hydraulic cylinder; 16. Connecting plate; 17. Limit rod; 18. Insertion post; 19. Limit bolt; 21. Top post; 22. Insertion rod; 23. Top plate; 24. Spring rod. Detailed Description of the Preferred Embodiment

[0017] The present utility model will be further described in detail below in conjunction with the drawings and specific embodiments. The embodiments of the present utility model are given for purposes of illustration and description, and are not intended to be exhaustive or to limit the present utility model to the disclosed form. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments are chosen and described in order to best explain the principles of the present utility model and its practical application, and to enable those of ordinary skill in the art to understand the present utility model and design various embodiments with various modifications suitable for specific purposes.

[0018] Please refer to Figures 1 to 5, in this embodiment, a testing device for an aircraft landing gear shock strut is provided, which includes a base 1 and a piston rod 2. An insertion post 18 is installed on the upper end surface of the base 1, and the insertion post 18 is installed at the bottom of the cylinder barrel 11 in a plug-in manner. The piston rod 2 is installed in the cylinder barrel 11 by means of sliding fit. Fixing grooves are symmetrically arranged in the front and rear on the upper end surface of the base 1. First sliders 12 are installed in the fixing grooves by means of sliding fit. An L-shaped frame is installed on the upper end surface of the first slider 12, and a limiting ring 13 is installed at the other end of the L-shaped frame. A placement groove is formed on the upper end surface of the first slider 12, and a pressing plate 14 is arranged in the placement groove. First hydraulic cylinders 15 are symmetrically installed on the left and right of the upper end surface of the base 1. A connecting plate 16 is installed at the output end of the first hydraulic cylinder 15, and the piston rod 2 is arranged at the bottom of the connecting plate 16. During operation, the shock strut is composed of the cylinder barrel 11 and the piston rod 2. The shock strut is placed on the base 1, and the insertion post 18 performs positioning processing on it. The first hydraulic cylinder 15 is started to drive the piston rod 2 to move up and down, so as to perform testing processing on the shock strut. The limiting ring 13 is closely attached to the outer side wall of the cylinder barrel 11 to prevent the shock strut from shaking during the testing process, further improving the stability of the device and preventing it from tipping over and causing injury to personnel. The pressing plate 14 performs limiting and fixing processing on the first slider 12 to prevent it from sliding relatively.

[0019] The pressing plate 14 is screwed to the base 1 through a limiting rod 17, and the limiting rods 17 are symmetrically arranged in the front and rear of the base 1. During operation, the structure of the limiting rod 17 is adopted to further ensure the stability of the placement of the pressing plate 14 and prevent it from accidentally popping out due to vibration.

[0020] A connecting column is installed in the middle of the upper end surface of the connecting plate 16. The connecting column is connected to the upper end surface of the piston rod 2 through a limiting bolt 19. A top column 21 is installed on the upper end surface of the limiting bolt 19. Slots are formed on the outer side wall of the top column 21. A movable plate is installed on the upper end surface of the connecting plate 16 by means of sliding fit. A plug rod 22 is installed on the right end surface of the movable plate, and the plug rod 22 is arranged in the slot in a plug-in manner. A top plate 23 is installed on the upper end surface of the top column 21. A bottom groove is formed at the bottom of the top plate 23. A spring rod 24 is installed on the outer side wall of the plug rod 22, and the spring rod 24 is installed in the bottom groove in a plug-in manner. During operation, the structure of the limiting bolt 19 is adopted to facilitate the removal of the shock strut for replacement after the testing is completed. And through the structure of the plug rod 22, the limiting bolt 19 is prevented from rotating during the testing process, resulting in the separation of the connecting column and the piston rod 2. The spring rod 24 performs positioning processing on the plug rod 22.

[0021] During specific operation, the shock absorber strut consists of a cylinder barrel 11 and a piston rod 2. The shock absorber strut is placed on the base table 1, and the plug post 18 positions it. The first hydraulic cylinder 15 is activated to drive the piston rod 2 to move up and down, thereby testing the shock absorber strut. The limiting ring 13 closely adheres to the outer side wall of the cylinder barrel 11 to prevent the shock absorber strut from shaking during the test, further improving the stability of the device and avoiding tipping over and causing injury to personnel. The pressing plate 14 limits and fixes the first slider 12 to prevent relative sliding.

[0022] Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art and related fields without creative efforts shall fall within the scope of protection of the present invention. The structures, devices, and operation methods not specifically described and explained in the present invention, unless otherwise specified and limited, are implemented according to the conventional means in the art.

Claims

1. An aircraft landing gear shock absorber strut testing device, comprising a base (1) and a piston rod (2), characterized in that: The upper end surface of the base (1) is provided with a cylinder barrel (11), a piston rod (2) is installed in the cylinder barrel (11) by means of sliding fit, a fixing groove is symmetrically provided on the upper end surface of the base (1) in the front and rear directions, a first slider (12) is installed in the fixing groove by means of sliding fit, an L-shaped frame is installed on the upper end surface of the first slider (12), a limiting ring (13) is installed at the other end of the L-shaped frame, a placement groove is provided on the upper end surface of the first slider (12), a pressure plate (14) is arranged in the placement groove, a first hydraulic cylinder (15) is symmetrically installed on the upper end surface of the base (1), a connecting plate (16) is installed at the output end of the first hydraulic cylinder (15), and the piston rod (2) is arranged at the bottom of the connecting plate (16).

2. The aircraft landing gear shock strut testing device according to claim 1, characterized in that The pressure plate (14) and the base (1) are screwed together via a limiting rod (17), and the limiting rod (17) is symmetrically arranged front and back with respect to the base (1).

3. The aircraft landing gear shock strut testing device according to claim 1, characterized in that: The upper end surface of the base (1) is provided with an insertion column (18), and the insertion column (18) is installed at the bottom of the cylinder (11) by means of insertion.

4. The aircraft landing gear shock strut testing device according to claim 1, characterized in that: A connecting column is installed in the middle of the upper end surface of the connecting plate (16), and the connecting column is connected to the upper end surface of the piston rod (2) via a limiting bolt (19).

5. The aircraft landing gear shock strut testing device according to claim 4, characterized in that: A top column (21) is installed on the upper end surface of the limiting bolt (19), and a slot is provided on the outer wall of the top column (21). A movable plate is installed on the upper end surface of the connecting plate (16) by means of sliding fit, and an insertion rod (22) is installed on the right end surface of the movable plate. The insertion rod (22) is arranged in the slot by means of plugging.

6. The aircraft landing gear shock strut testing device according to claim 5, characterized in that: A top plate (23) is installed on the upper end surface of the top column (21), a bottom groove is opened at the bottom of the top plate (23), a spring rod (24) is installed on the outer side wall of the insertion rod (22), and the spring rod (24) is installed in the bottom groove by plugging.

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