Airplane axle jack detection tool

Abstract

A detection tool for an aircraft axle jack relates to the technical field of aircraft maintenance, a piston rod of the aircraft axle jack is driven to extend outwards until the head end of the piston rod of the aircraft axle jack is in contact with a top, an axial pressure value generated by the aircraft axle jack is acquired in real time through a force sensor I, and the aircraft axle jack is continuously loaded; and the test load is reached. A radial force is applied to the head end of the piston rod of the aircraft axle jack through the radial force application mechanism, and a radial pressure value generated by the radial force application mechanism to the head end of the piston rod of the aircraft axle jack is obtained in real time through the force sensor II until a radial test load is reached.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance technology, specifically to an aircraft wheel axle jack testing fixture. Background Technology

[0002] According to the national metrological verification procedure JJG621—2012 (hydraulic jacks), in addition to the initial inspection at the factory, jacks also need to undergo periodic inspections every 6 months during use.

[0003] In the field of aircraft maintenance, aircraft wheel and axle jacks are relatively large and heavy, making transportation inconvenient. Sending each jack to the laboratory for testing incurs high transportation costs and takes a long time. Based on actual needs and intense market competition, on-site testing of jacks is a developing trend. Summary of the Invention

[0004] In order to overcome the shortcomings of the above technologies, this utility model provides a tooling that is easy to use and enables on-site inspection of aircraft wheel axle jacks.

[0005] The technical solution adopted by this utility model to overcome its technical problem is:

[0006] A tooling for inspecting aircraft wheel axle jacks, comprising:

[0007] The base plate has lead screws installed vertically at its four corners at the top.

[0008] The top plate is connected to each lead screw via a height adjustment mechanism;

[0009] Force sensor I is mounted on the lower end of the top plate by screws, and the measuring end of force sensor I is connected to a downwardly protruding top head;

[0010] A connecting plate, vertically mounted on the side of the top plate, has a sensor mount on it, and force sensor II is mounted in the sensor mount; and

[0011] The radial force application mechanism is connected to the measuring end of the force sensor II. The radial force application mechanism applies radial force to the piston rod head of the aircraft wheel axle jack.

[0012] Furthermore, the aforementioned height adjustment mechanism includes through holes located at the four corners of the upper top plate, with lead screws inserted into the corresponding through holes. Nut I is screwed onto the lead screw located at the upper end of the upper top plate, and nut II is screwed onto the lead screw located at the lower end of the upper top plate. The lower end face of nut I contacts the upper end face of the upper top plate, and the upper end face of nut II contacts the lower end face of the upper top plate.

[0013] Preferably, the lower end of the aforementioned top head is provided with a ball head.

[0014] Preferably, the force sensor I is an LCSC2BH type spoke sensor.

[0015] Furthermore, the aforementioned radial force application mechanism is a hydraulic cylinder with its axis arranged horizontally. The tail end of the hydraulic cylinder is connected to the measuring end of the force sensor II, and its piston rod contacts the piston rod head of the aircraft wheel axle jack when it extends.

[0016] The beneficial effects of this invention are: it allows for simultaneous axial and radial load testing of aircraft wheel axle jacks, greatly improving the efficiency of aircraft wheel axle jack maintenance, shortening the testing cycle, and reducing testing costs. Since the lead screws are connected to the base plate via threaded connections, and the top plate is movably connected to each lead screw through a height adjustment mechanism, disassembly and assembly are convenient, improving portability and reducing manpower and material costs during transportation. Attached Figure Description

[0017] Figure 1 This is a diagram showing the usage state of this utility model;

[0018] Figure 2 This is a three-dimensional structural diagram of the present invention;

[0019] In the diagram, 1. Base plate 2. Lead screw 3. Top plate 4. Aircraft wheel axle jack 5. Nut I 6. Nut II 7. Force sensor I 8. Top head 9. Hydraulic cylinder 10. Force sensor II 11. Connecting plate 12. Screw 13. Ball head 14. Sensor seat. Detailed Implementation

[0020] The following is in conjunction with the appendix Figure 1 Appendix Figure 2 The present invention will be further described below.

[0021] A testing fixture for an aircraft wheel axle jack includes: a base plate 1 with lead screws 2 vertically arranged at its four upper corners; an upper top plate 3 connected to each lead screw 2 via a height adjustment mechanism; a force sensor I 7 mounted on the lower end of the upper top plate 3 via screws 12, the measuring end of the force sensor I 7 being connected to a downwardly protruding head 8; a connecting plate 11 mounted vertically on the side of the upper top plate 3, a sensor seat 14 mounted on the connecting plate 11, and a force sensor II 10 mounted in the sensor seat 14; and a radial force application mechanism connected to the measuring end of the force sensor II 10, the radial force application mechanism applying radial force to the piston rod head of the aircraft wheel axle jack 4. In use, the aircraft axle jack 4 is moved into the testing fixture, placing it on the base plate 1. The piston rod of the aircraft axle jack 4 is driven to extend outward until its head contacts the top head 8. The axial pressure value generated by the aircraft axle jack 4 is acquired in real time by force sensor I 7. Loading continues on the aircraft axle jack 4 until the test load is reached. A radial force is applied to the piston rod head of the aircraft axle jack 4 through a radial force application mechanism. The radial pressure value generated by the radial force application mechanism on the piston rod head of the aircraft axle jack 4 is acquired in real time by force sensor II 10 until the radial test load is reached. This allows the aircraft axle jack 4 to perform axial and radial load tests simultaneously, greatly improving its operational efficiency, shortening the testing cycle, and reducing testing costs. Since the lead screw 2 is connected to the base plate 1 by a threaded connection, and the top plate 3 is movably connected to each lead screw 2 through a height adjustment mechanism, it can be easily disassembled and assembled, improving portability and reducing manpower and material costs during transportation.

[0022] In one embodiment of this utility model, the height adjustment mechanism includes through holes at the four corners of the upper top plate 3. Lead screws 2 are inserted into the corresponding through holes. Nut I 5 is screwed onto the lead screw 2 located at the upper end of the upper top plate 3, and nut II 6 is screwed onto the lead screw 2 located at the lower end of the upper top plate 3. The lower end face of nut I 5 contacts the upper end face of the upper top plate 3, and the upper end face of nut II 6 contacts the lower end face of the upper top plate 3. Loosening nuts I 5 and II 6 allows the upper top plate 3 to slide up and down along the lead screws 2. After adjustment, tightening nuts I 5 and II 6 fixes the upper top plate 3 to each lead screw 2.

[0023] In one embodiment of this utility model, a ball head 13 is provided at the lower end of the top head 8. When the aircraft wheel axle jack 4 is being tested, the ball head 13 is embedded in the top socket of the piston rod of the aircraft wheel axle jack 4, so as to achieve the maximum contact area between the top head 8 and the top of the piston rod of the aircraft wheel axle jack 4, thereby improving the reliability of the test.

[0024] In one embodiment of this utility model, the force sensor I 7 is an LCSC2BH type spoke sensor.

[0025] In one embodiment of this utility model, the radial force application mechanism is a hydraulic cylinder 9. The axis of the hydraulic cylinder 9 is arranged in a horizontal direction. The tail end of the hydraulic cylinder 9 is connected to the measuring end of the force sensor II 10. When its piston rod extends, it contacts the piston rod head end of the aircraft wheel axle jack 4. When the piston rod of the hydraulic cylinder 9 extends outward, it applies a radial force to the piston rod head end of the aircraft wheel axle jack 4, and the test load is read by the sensor II 10.

[0026] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A tooling for inspecting aircraft wheel axle jacks, characterized in that, include: The base plate (1) has lead screws (2) installed at its four corners along the vertical direction. The top plate (3) is connected to each lead screw (2) through a height adjustment mechanism; Force sensor I (7) is installed at the lower end of the top plate (3) by screws (12). The measuring end of force sensor I (7) is connected to a downward protruding top head (8). A connecting plate (11) is vertically mounted on the side of the top plate (3). A sensor base (14) is mounted on the connecting plate (11), and a force sensor II (10) is mounted in the sensor base (14). The radial force application mechanism is connected to the measuring end of the force sensor II (10) and applies radial force to the piston rod head of the aircraft wheel axle jack (4).

2. The aircraft wheel axle jack inspection fixture according to claim 1, characterized in that: The height adjustment mechanism includes through holes at the four corners of the upper top plate (3), and screws (2) are inserted into the corresponding through holes. Nut I (5) is screwed onto the screw (2) at the upper end of the upper top plate (3), and nut II (6) is screwed onto the screw (2) at the lower end of the upper top plate (3). The lower end face of nut I (5) is in contact with the upper end face of the upper top plate (3), and the upper end face of nut II (6) is in contact with the lower end face of the upper top plate (3).

3. The aircraft wheel axle jack inspection fixture according to claim 1, characterized in that: The lower end of the top head (8) is provided with a ball head (13).

4. The aircraft wheel axle jack inspection fixture according to claim 1, characterized in that: The force sensor I (7) is an LCSC2BH type spoke sensor.

5. The aircraft wheel axle jack inspection fixture according to claim 1, characterized in that: The radial force application mechanism is a hydraulic cylinder (9). The axis of the hydraulic cylinder (9) is set in the horizontal direction. The tail end of the hydraulic cylinder (9) is connected to the measuring end of the force sensor II (10). When its piston rod extends, it contacts the piston rod head of the aircraft wheel axle jack (4).

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