Movable lifting appliance testing tool for aircraft maintenance

Abstract

A movable lifting appliance testing tool for aircraft maintenance relates to the technical field of aircraft maintenance, and is characterized in that a worm gear and worm transmission mechanism has a self-locking characteristic, and when a worm stops rotating, a lead screw stops rotating, so that the safety during lifting is ensured, and meanwhile, the transmission of the worm gear and the worm has a deceleration characteristic; therefore, compared with a crane for hoisting the airplane parts, the low-speed stable loading is realized, the detection efficiency and the detection precision are improved, the detection work of airplane maintenance hangers with different specifications and different shapes and sizes is met, the load test is closer to the actual use condition, and the safety of the test work is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft maintenance, and in particular to a movable aircraft maintenance hanger testing tool. Background Art

[0002] Aircraft maintenance slings (specialized equipment used to lift aircraft components during aircraft inspection and maintenance) require annual load testing of engine, fairing, and vertical tail slings, as required by relevant regulations and manufacturer documentation. These slings come in a variety of styles, carry large load capacities, and require high connection and installation precision. Conventional test equipment, with its limited loading capacity, single force application direction, and fixed installation requirements, cannot meet the testing requirements for large-scale lifting slings. Summary of the Invention

[0003] In order to overcome the deficiencies of the above technologies, the utility model provides a tool that can meet the testing requirements of slings of various forms and sizes and improve the detection accuracy.

[0004] The technical solution adopted by the utility model to overcome the technical problems is:

[0005] A movable aircraft maintenance sling testing tool, comprising:

[0006] The box body has an upper end connected to a lifting lug via a connecting rod mechanism;

[0007] The base is installed in the box body, and a worm wheel is rotatably installed in the base. The axis of the worm wheel is arranged in the vertical direction, and a screw hole is arranged in the worm wheel along its axial direction;

[0008] The worm is rotatably mounted in the box, the axis of the worm is arranged in the horizontal direction, and the worm is meshed with the worm wheel;

[0009] A power unit is provided on the box body and is used to drive the worm to rotate;

[0010] A lead screw, the axis of which is arranged in a vertical direction, and the lead screw is screwed into the screw hole of the worm wheel;

[0011] A guide sleeve is mounted on the base, the guide sleeve is coaxial with the lead screw, and the upper end of the lead screw is located in the hole of the guide sleeve; and

[0012] The sensor fixing device is located at the lower end of the box body, the sensor fixing device is installed at the bottom of the lead screw, the tension sensor is fixed in the sensor fixing device, and the tension sensor is connected to the aircraft maintenance sling.

[0013] Furthermore, the above-mentioned connecting rod mechanism includes ear seats and four connecting rods respectively installed at the four corners of the box body. The lower end of the connecting rod is hingedly connected to the ear seat through pin shaft II, and the upper end thereof is hingedly connected to the lifting ear through pin shaft I.

[0014] In order to improve reliability, the lower end of the connecting rod is rotatably connected to the pin shaft II through a universal bearing II.

[0015] In order to improve reliability, the upper end of the connecting rod is rotatably connected to the pin shaft I through a universal bearing I.

[0016] Preferably, the box body is a cube structure.

[0017] Furthermore, the power unit includes a reducer mounted on the housing and a servo motor connected to the input shaft of the reducer, and the output shaft of the reducer is coaxially connected to the worm through a coupling.

[0018] Furthermore, the above-mentioned sensor fixing device includes a sensor seat I installed at the lower end of the screw and a U-shaped sensor seat II. The sensor seat II is fixed to the sensor seat I by bolts, and the tension sensor is clamped between the sensor seat I and the sensor seat II.

[0019] In order to improve reliability, a protective sleeve is further included at the upper end of the guide sleeve. The protective sleeve is coaxially arranged with the guide sleeve. When the lead screw moves to the uppermost end, it is located in the protective sleeve.

[0020] The beneficial effects of the present invention are as follows: since the worm gear transmission mechanism has the self-locking characteristic, when the worm stops rotating, the lead screw also stops rotating, thereby ensuring safety during lifting; and at the same time, the worm gear transmission has the deceleration characteristic, thus achieving slow and stable loading of aircraft components compared to overhead cranes, improving the efficiency and accuracy of detection, meeting the detection work of aircraft maintenance slings of different specifications, shapes and sizes, making the load test closer to the actual use situation, and improving the safety of the test work. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a three-dimensional structural diagram of the present invention;

[0022] Figure 2 It is an exploded view of the three-dimensional structure of the present invention;

[0023] In the figure, 1. Housing 2. Reducer 3. Servo motor 4. Lifting ear 5. Connecting rod 6. Pin I 7. Ear seat 8. Pin II 9. Protective sleeve 10. Screw 11. Sensor seat I 12. Sensor seat II 13. Bolt 14. Universal bearing I 15. Universal bearing II 16. Coupling 17. Worm 18. Base 19. Guide sleeve 20. Worm gear. DETAILED DESCRIPTION

[0024] The following is combined with Figure 1 , Attachment Figure 2 The utility model is further described.

[0025] A movable aircraft maintenance sling test tool comprises: a box body 1, the upper end of which is connected to a lifting lug 4 through a connecting rod mechanism; a base 18, which is installed in the box body 1, and a worm gear 20 is rotatably installed in the base 18, the axis of the worm gear 20 is arranged in the vertical direction, and a screw hole is arranged in the worm gear 20 along its axial direction; a worm 17, which is rotatably installed in the box body 1, the axis of the worm gear 17 is arranged in the horizontal direction, and the worm 17 is meshed with the worm gear 20; a power unit, which is arranged on the box body 1, is used to drive The worm 17 rotates; the lead screw 10, whose axis is arranged in the vertical direction, is screwed into the threaded hole of the worm wheel 20; the guide sleeve 19 is mounted on the base 18 and is coaxial with the lead screw 10, with the upper end of the lead screw 10 located in the hole of the guide sleeve 19; and the sensor fixture is located at the lower end of the box 1 and is installed at the bottom of the lead screw 10. The tension sensor is fixed in the sensor fixture and connected to the aircraft maintenance lifting device. When in use, the lifting lug 4 is hung on the hook of the overhead crane, and the tension sensor is connected to the aircraft maintenance lifting device to be tested. The aircraft maintenance lifting device lifts the corresponding part of the aircraft. The overhead crane first performs a large stroke movement, generating an initial tension on the aircraft maintenance sling through the lifting lug 4, connecting rod mechanism, housing 1, screw 10, and sensor fixture. When the aircraft maintenance sling is about to receive a load, the overhead crane stops, and the power unit drives the worm 17 to rotate, which in turn drives the worm gear 20. Since the worm gear 20 is threadedly connected to the screw 10, the aircraft maintenance sling is driven upward to lift the aircraft component. At this time, the tension value is read by the tension sensor until the required load is reached. Due to the self-locking nature of the worm gear transmission mechanism, when the worm 17 stops rotating, the screw 10 also stops rotating, ensuring safety during lifting. At the same time, the worm gear transmission has a deceleration characteristic. Therefore, compared to the overhead crane, slow and smooth loading is achieved for lifting aircraft components, improving the efficiency and accuracy of testing. This meets the requirements for testing aircraft maintenance slings of different specifications, shapes, and sizes, making load testing more similar to actual use and improving testing safety.

[0026] In one embodiment of the present invention, the linkage mechanism includes lugs 7 mounted at the four corners of the housing 1 and four connecting rods 5. The lower ends of the connecting rods 5 are hingedly connected to the lugs 7 via pins II 8, and their upper ends are hingedly connected to the lifting lugs 4 via pins I 6. The four connecting rods 5 secure the lifting lugs 4 to the top of the housing 1. During lifting, the four connecting rods 5 are subjected to tension. Because the four connecting rods 5 are evenly arranged at the four corners of the housing 1, the tension is evenly distributed, the force is rationally applied, and the system is reliable. Preferably, in this embodiment, the lower ends of the connecting rods 5 are rotationally connected to the pins II 8 via universal bearings II 15. The upper ends of the connecting rods 5 are rotationally connected to the pins I 6 via universal bearings I 14. The provision of universal bearings II 15 and I 14 allows for the rotational coordination of universal bearings II 15 and I 14 when the connecting rod 5 is subjected to deflection forces, preventing damage to the connecting rod 5 and improving reliability.

[0027] In one embodiment of the present invention, preferably, the box body 1 is a cube structure.

[0028] In one embodiment of the present invention, the power unit includes a reducer 2 mounted on a housing 1 and a servo motor 3 drivingly connected to the input shaft of the reducer 2. The output shaft of the reducer 2 is coaxially connected to a worm 17 via a coupling 16. The servo motor 3 rotates, amplified by the torque of the reducer 2, and then drives the worm 17 via the coupling 16. The servo motor 3 can precisely control the rotation angle of the worm 17, thereby precisely controlling the axial movement distance of the lead screw 10.

[0029] In one embodiment of the present invention, the sensor fixing device includes a sensor holder I 11 mounted at the lower end of a lead screw 10 and a U-shaped sensor holder II 12. Sensor holder II 12 is secured to sensor holder I 11 via bolts 13, and a tension sensor is clamped between sensor holders I 11 and II 12. The tension sensor is clamped and secured by sensor holders I 11 and II 12, simplifying the connection and improving installation efficiency.

[0030] The guide sleeve 19 further includes a protective sleeve 9 disposed on the upper end thereof. The protective sleeve 9 is coaxially disposed with the guide sleeve 19. When the lead screw 10 moves to the uppermost end, the lead screw 10 is located in the protective sleeve 9. The provision of the protective sleeve 9 can effectively protect the lead screw 10, prevent the thread of the lead screw 10 from being damaged, and improve the reliability of use.

[0031] Finally, it should be noted that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art will be able to modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A movable aircraft maintenance sling test tool, characterized in that: include: A box body (1), the upper end of which is connected to a lifting lug (4) via a connecting rod mechanism; A base (18) is installed in the box (1), and a worm wheel (20) is rotatably installed in the base (18). The axis of the worm wheel (20) is arranged in a vertical direction, and a screw hole is arranged in the worm wheel (20) along its axial direction. A worm (17) is rotatably mounted in the housing (1), wherein the axis of the worm (17) is arranged in a horizontal direction, and the worm (17) is meshed with the worm wheel (20); A power unit, disposed on the housing (1), for driving the worm (17) to rotate; A lead screw (10) having an axis arranged in a vertical direction, the lead screw (10) being screwed into a screw hole of a worm wheel (20); A guide sleeve (19) is mounted on the base (18), the guide sleeve (19) is coaxial with the lead screw (10), and the upper end of the lead screw (10) is located in the hole of the guide sleeve (19); and The sensor fixing device is located at the lower end of the box body (1), the sensor fixing device is installed at the bottom of the lead screw (10), the tension sensor is fixed in the sensor fixing device, and the tension sensor is connected to the aircraft maintenance sling.

2. The movable aircraft maintenance sling testing tool according to claim 1, characterized in that: The connecting rod mechanism comprises ear seats (7) respectively installed at the four corners of the box body (1) and four connecting rods (5). The lower end of the connecting rod (5) is hingedly connected to the ear seat (7) through a pin shaft II (8), and the upper end of the connecting rod (5) is hingedly connected to the lifting ear (4) through a pin shaft I (6).

3. The movable aircraft maintenance sling testing tool according to claim 1, characterized in that: The lower end of the connecting rod (5) is rotatably connected to the pin shaft II (8) through a universal bearing II (15).

4. The movable aircraft maintenance sling testing tool according to claim 1, wherein: The upper end of the connecting rod (5) is rotatably connected to the pin shaft I (6) through a universal bearing I (14).

5. The movable aircraft maintenance sling testing tool according to claim 1, wherein: The box (1) is a cube structure.

6. The movable aircraft maintenance sling testing tool according to claim 1, characterized in that: The power unit comprises a reducer (2) mounted on a housing (1) and a servo motor (3) connected to the input shaft of the reducer (2); the output shaft of the reducer (2) is connected to the worm (17) via a coupling (16).

7. The movable aircraft maintenance sling testing tool according to claim 1, characterized in that: The sensor fixing device includes a sensor seat I (11) installed at the lower end of the screw (10) and a U-shaped sensor seat II (12). The sensor seat II (12) is fixed to the sensor seat I (11) by a bolt (13), and the tension sensor is clamped between the sensor seat I (11) and the sensor seat II (12).

8. The movable aircraft maintenance sling testing tool according to claim 1, wherein: It also includes a protective sleeve (9) arranged at the upper end of the guide sleeve (19), wherein the protective sleeve (9) and the guide sleeve (19) are coaxially arranged, and when the lead screw (10) moves to the uppermost end, it is located in the protective sleeve (9).

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