Aircraft fuselage middle section strength loading test tool

Abstract

The utility model relates to the technical field of testing tools, and discloses an airplane fuselage middle section strength loading testing tool which comprises a tool base, supporting legs and a fuselage shell, the left end of the top side of the tool base is fixedly connected with a fuselage tail supporting frame, and the front side and the rear side of the tool base are both fixedly connected with vertical rods. A pressure sensor is fixedly connected to the top side of the vertical rod, threaded jacks are fixedly connected to the top side of the pressure sensor, an I-shaped frame is fixedly connected to the top sides of the two threaded jacks, and a machine body front end fixing frame is fixedly connected to the right end of the top side of the tool base. The front side and the rear side of each supporting leg are in threaded connection with a lifting assembly for fixing. According to the utility model, the height of the threaded rod can be adjusted by rotating the handle through the lifting assembly on the supporting leg. The threaded rod drives the limiting sleeve, the U-shaped plate and the pressing pipe to move up and down, the pressing pipe presses the tail of the machine body, and the stabilizing effect on the machine body is further enhanced.

Description

Technical Field

[0001] The utility model relates to the technical field of testing tooling, in particular to a tooling for strength loading testing of a mid-section of an aircraft fuselage. Background Art

[0002] The aircraft midsection strength loading test fixture is a device specifically designed for testing the structural strength of an aircraft midsection. It is primarily used to verify the structural strength of the fuselage, determine the load-bearing capacity of the structure, and verify the manufacturing process. The aircraft midsection strength loading test fixture, also known as a strength test device or test fixture, is a specialized set of equipment designed for the aircraft midsection structure. The fixture typically consists of a loading frame, a force application device, and a measurement and control system. It is capable of simulating and applying various forces experienced by the fuselage during actual flight, such as bending, torsion, compression, and tension.

[0003] In existing technology, most aircraft mid-section strength loading test fixtures use clamps or straps for fixation. Due to their lack of adaptability, clamps are difficult to tightly fit the unique shapes of different aircraft fuselages. Furthermore, the clamping force is easily reduced by loose bolts or spring inelasticity. Furthermore, the limited contact area can easily lead to localized stress concentration, resulting in instability. Therefore, a mid-section aircraft fuselage strength loading test fixture was proposed to address these issues. Utility Model Content

[0004] In order to make up for the above deficiencies, the present invention provides an aircraft fuselage mid-section strength loading test fixture, which aims to improve the problem that some aircraft fuselage mid-section strength loading test fixtures in the prior art may be unstable during use.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0006] The cam is fixedly mounted on a support frame, and the cam is secured to the support frame with an angular channel formed between the end of the support leg and the support frame, and the cam is connected to the support frame by a threaded connection to the support leg.

[0007] As a further description of the above technical solution:

[0008] The inner wall of the limit block is slidably connected to a pressing assembly for pressing subsequent components, the bottom side of the pressing assembly is fixedly connected to a fixing rod, the bottom side of the fixing rod is fixedly connected to a disc, the bottom side of the disc is fixedly connected to a spring, the front and rear ends of the bottom side of the pressing assembly are fixedly connected to an opening plate, the inside of the opening plate is rotatably connected to a rotating plate, and the far ends of each two rotating plates are rotatably connected to a concave plate, and the bottom side of the concave plate is fixedly connected to the limiting rod;

[0009] As a further description of the above technical solution:

[0010] The lifting assembly includes a threaded rod, the outer portions of the two threaded rods are respectively threadedly connected to the front and rear ends of the top of the support leg, the top side of the threaded rod is fixedly connected to a handle, and the bottom side of the threaded rod is fixedly connected to a circular plate;

[0011] As a further description of the above technical solution:

[0012] The outer portion of the circular plate is rotatably connected to the inner wall of the limiting sleeve, and the bottom end of the threaded rod is rotatably connected to the interior of the limiting sleeve;

[0013] As a further description of the above technical solution:

[0014] The bottom side of the fuselage shell contacts the top side of the tooling base, the top side of the fuselage tail support frame contacts the left end of the bottom side of the fuselage shell, the interior of each two U-shaped plates contacts the front and rear ends of the pressure tube, and a weight block is slidably connected to the inside of the right end of the fuselage shell;

[0015] As a further description of the above technical solution:

[0016] The pressing assembly includes a sliding rod, the outer portion of the sliding rod is slidably connected to the inner portion of the sliding plate, the top side of the sliding rod is fixedly connected to a handle, and the bottom side of the sliding rod is fixedly connected to a strip plate;

[0017] As a further description of the above technical solution:

[0018] The outer portion of the strip plate is slidably connected to the inner wall of the sliding plate, and the bottom side of the strip plate is fixedly connected to the top side of the fixing rod;

[0019] As a further description of the above technical solution:

[0020] The top sides of each two opening plates are fixedly connected to the front and rear ends of the bottom side of one of the strip plates, and the outer portion of the limit rod is slidably connected to the inner wall of the limit block, and the outer portion of the limit rod is slidably connected to the inner wall of the storage box.

[0021] The utility model has the following beneficial effects:

[0022] In this utility model, the force generated by operating the threaded jack to rise is transmitted to the mid-section of the fuselage via the I-beam. A pressure sensor monitors the magnitude and changes of the force during the loading process in real time, allowing precise control of the magnitude and direction of the loading force to meet diverse testing requirements. The lifting assembly on the support leg adjusts the height of the threaded rod by turning a handle. The threaded rod drives the limit sleeve, U-shaped plate, and pressure tube up and down, pressing the pressure tube against the rear end of the fuselage, further stabilizing the fuselage.

[0023] 2. In the present invention, a handle is used to operate the sliding rod, which slides up and down. The sliding rod drives the strip plate to slide along the inner wall of the sliding plate. The strip plate transmits force to the disc and spring via the fixed rod. The spring is compressed, and the rotating connection structure of the opening plate, rotating plate, and concave plate causes the limit rod at the bottom of the concave plate to slide between the limit block and the inner wall of the storage box, thereby securing and sorting the components in the storage box, allowing users to quickly access the required tools and thereby improving work efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a three-dimensional schematic diagram of a mid-section strength loading test fixture for an aircraft fuselage proposed in the present invention;

[0025] Figure 2 This is a structural schematic diagram of an I-shaped frame of an aircraft fuselage midsection strength loading test fixture proposed by the present invention;

[0026] Figure 3 This is a schematic structural diagram of the support legs of a mid-section strength loading test fixture for an aircraft fuselage proposed in the present invention;

[0027] Figure 4 This is a schematic structural diagram of a threaded rod of a mid-section strength loading test fixture for an aircraft fuselage proposed in the present invention;

[0028] Figure 5 This is a schematic structural diagram of a sliding plate of a mid-section strength loading test fixture for an aircraft fuselage proposed in the present invention;

[0029] Figure 6 for Figure 5 Enlarged view of point A in the middle;

[0030] Figure 7The present invention is a schematic structural diagram of a limit sleeve of a tool for loading test of the mid-section strength of an aircraft fuselage.

[0031] Legend:

[0032] 1. Tooling base; 2. Fuselage tail support frame; 3. Vertical pole; 4. Pressure sensor; 5. Threaded jack; 6. I-beam; 7. Fuselage front end fixing frame; 8. Support leg; 9. Threaded rod; 10. Handle; 11. Limit sleeve; 12. U-shaped plate; 13. Pressure tube; 14. Fuselage shell; 15. Weight block; 16. Round plate; 17. Storage box; 18. Sliding plate; 19. Limit block; 20. Sliding rod; 21. Strip plate; 22. Fixed rod; 23. Disc; 24. Spring; 25. Opening plate; 26. Rotating plate; 27. Concave plate; 28. Limit rod. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0034] Reference Figures 1 to 3 The present invention provides an embodiment of a test fixture for the strength loading of the middle section of an aircraft fuselage, comprising a fixture base 1, support legs 8 and a fuselage shell 14. The fixture base 1 plays a fundamental role in the entire test fixture. The fixture base 1 is fixed to the ground by expansion screws. The left end of the top side of the fixture base 1 is fixedly connected to a fuselage tail support frame 2. This fuselage tail support frame 2 can perfectly fit the tail of the aircraft fuselage, providing important support for the tail of the aircraft fuselage. At the same time, vertical poles 3 are fixedly connected to the front and rear sides of the fixture base 1. These vertical poles 3 provide a stable installation position for the subsequent pressure sensor 4 and threaded jack 5. The concave surface of the fuselage tail support frame 2 fits the curved surface of the bottom of the fuselage, which can better adapt to the shape of the fuselage and provide stable support for the tail of the fuselage. The top side of the vertical pole 3 is fixedly connected to a pressure sensor 4. The pressure sensor 4 can accurately measure the magnitude and change of the force applied to the aircraft fuselage during the test. Threaded jacks 5 are fixedly attached to the top of pressure sensor 4. These two jacks 5 have a strong load-bearing capacity. An I-beam 6 is fixedly attached to the top of these two jacks. This sturdy structure evenly transmits the force generated by the jacks 5 to the midsection of the aircraft fuselage, ensuring the accuracy and reliability of the test.

[0035] Reference Figure 1 、 Figure 4 and Figure 7 , the right end of the top side of the tooling base 1 is fixedly connected to the front end fuselage fixing frame 7, and this front end fuselage fixing frame 7 is fixed to the front end rib of the aircraft fuselage by strong bolts, providing stable support for the front end of the aircraft fuselage. The design of the front end fuselage fixing frame 7 fully takes into account the structural characteristics of the aircraft fuselage, and can effectively disperse the force to ensure that the aircraft fuselage remains stable during the test. The support leg 8 plays an auxiliary support role in the tooling. The front and rear sides of the support leg 8 are threadedly connected to a lifting assembly for fixing. The lifting assembly includes a threaded rod 9, and the outer parts of the two threaded rods 9 are respectively threadedly connected to the front and rear ends of the top of the support leg 8. A handle 10 is fixedly connected to the top side of the threaded rod 9. The design of the handle 10 conforms to the principles of ergonomics. The operator can easily adjust the height of the threaded rod 9 by turning the handle 10;

[0036] The bottom of the lifting assembly is rotatably connected to a limiting sleeve 11, which can effectively limit the range of motion of the threaded rod 9, ensuring that the threaded rod 9 will not deviate during the adjustment process. The outer portion of the circular plate 16 is rotatably connected to the inner wall of the limiting sleeve 11. The bottom end of the threaded rod 9 is rotatably connected to the inside of the limiting sleeve 11, ensuring that the threaded rod 9 will not separate from the limiting sleeve 11 during the movement. The bottom side of the limiting sleeve 11 is fixedly connected to a U-shaped plate 12, which has good rigidity and stability. The two U-shaped plates 12 are internally movably connected to a pressure tube 13, which can fit tightly to the tail of the aircraft fuselage. By adjusting the height of the threaded rod 9, the pressure tube 13 can be pressed against the tail of the fuselage, further enhancing the fixing effect on the fuselage. The bottom side of the fuselage shell 14 is in contact with the top side of the tooling base 1. During the test, the fuselage shell 14 is subjected to forces from all directions. A weight block 15 is slidably connected to the right end of the fuselage shell 14. The weight block 15 can be adjusted according to test requirements to simulate the load conditions of the aircraft during actual flight. A circular plate 16 is fixedly connected to the bottom side of the threaded rod 9 to strengthen the connection.

[0037] Reference Figure 1 、 Figure 5 and Figure 6 , refer to Figures 1 to 3, the support leg 8 and the front side of one of the uprights 3 are fixedly connected with a storage box 17, and the storage box 17 can protect the tools and parts stored inside. The inner wall of the storage box 17 is slidably connected with a plurality of sliding plates 18, and the sliding plates 18 can be adjusted in position as needed to facilitate the storage and retrieval of tools and parts. The front and rear ends of the sliding plate 18 are fixedly connected with a limit block 19, and the limit block 19 can effectively limit the range of motion of the sliding plate 18, ensuring that the sliding plate 18 will not deviate during use. The inner wall of the limit block 19 is slidably connected with a pressing component for pressing subsequent components. The pressing component includes a sliding rod 20, and the outer portion of the sliding rod 20 is slidably connected to the inside of the sliding plate 18, and the sliding rod 20 can slide smoothly inside the sliding plate 18. The top side of the sliding rod 20 is fixedly connected with a handle, and the design of the handle is convenient for the operator to operate;

[0038] The bottom side of the sliding rod 20 is fixedly connected to a strip plate 21, which can transmit the movement of the sliding rod 20 to other components. The outer side of the strip plate 21 is slidably connected to the inner wall of the sliding plate 18 to ensure that the strip plate 21 does not deviate during movement. The bottom side of the pressing assembly is fixedly connected to a fixed rod 22, which can withstand greater pressure. The bottom side of the strip plate 21 is fixedly connected to the top side of the fixed rod 22 to ensure that the connection between the strip plate 21 and the fixed rod 22 is firm and reliable. The bottom side of the fixed rod 22 is fixedly connected to a disc 23, which can evenly transmit pressure to the spring 24. The bottom side of the disc 23 is fixedly connected to a spring 24, which has good elasticity and can act as a buffer when the pressing assembly is working;

[0039] The bottom and front ends of the pressing assembly are fixedly connected to an opening plate 25. The design of the opening plate 25 makes the pressing assembly structure more stable. The opening plate 25 is internally connected to a rotating plate 26, which can flexibly rotate within the opening plate 25. The opposite end of each rotating plate 26 is rotatably connected to a concave plate 27, which is designed to better cooperate with a stop rod 28. The bottom side of the concave plate 27 is fixedly connected to a stop rod 28, which effectively limits the movement of subsequent components. The top side of each opening plate 25 is fixedly connected to the front and back ends of the bottom side of one of the strip plates 21, respectively, to ensure a secure and reliable connection between the opening plate 25 and the strip plate 21. The outer portion of the stop rod 28 is slidably connected to the inner wall of the stop block 19, allowing the stop rod 28 to slide smoothly within the stop block 19. The outer portion of the stop rod 28 is also slidably connected to the inner wall of the storage box 17, ensuring that the stop rod 28 does not deviate during use. The pressing assembly can fix the components in the storage box 17 to prevent shaking during the test, thereby ensuring the accuracy and safety of the test.

[0040] Working Principle: First, the tooling base 1 is securely fixed to the ground with expansion screws to ensure the stability of the entire tooling during testing. The fuselage shell 14 is placed on the tooling base 1 so that its bottom side contacts the top side of the tooling base 1. The front end of the fuselage is bolted to the front end fixing bracket 7, providing a stable support point for the front end of the fuselage. The concave surface of the fuselage tail support bracket 2 conforms to the curved surface of the fuselage bottom, providing support for the tail of the fuselage and effectively distributing the weight and loading force of the fuselage. The vertical pole 3 is fixed to the ground with expansion screws, providing stable support for the pressure sensor 4 and threaded jack 5. When the mid-section of the fuselage needs to be loaded, the threaded jack 5 is operated to rise, and the generated force is transmitted to the mid-section of the fuselage through the I-beam 6. The pressure sensor 4 can monitor the magnitude and changes of the force during the loading process in real time, so as to accurately control the magnitude and direction of the loading force to meet different testing requirements. The lifting assembly on the support leg 8 can adjust the height of the threaded rod 9 by turning the handle 10. Threaded rod 9 drives the retaining sleeve 11, U-shaped plate 12, and pressure tube 13 to move up and down, pressing the pressure tube 13 against the tail of the fuselage, further strengthening the fuselage's fixation. The weight 15 inside the right end of the fuselage shell 14 can be slid and adjusted as needed to simulate the load conditions of the aircraft during actual flight, making the test more similar to actual operating conditions.

[0041] During the test process, if tools and parts are needed, they can be taken from the storage box 17 on the front side of the support leg 8 and the upright 3. The sliding plate 18 in the storage box 17 can be slid to adjust the position as needed. When it is necessary to fix the parts in the storage box 17, the sliding rod 20 is operated by the handle to slide up and down. The sliding rod 20 drives the strip plate 21 to slide on the inner wall of the sliding plate 18, and the strip plate 21 transmits the force to the disc 23 and the spring 24 through the fixing rod 22. The spring 24 is compressed by the force, and through the rotating connection structure of the opening plate 25, the rotating plate 26 and the concave plate 27, the limiting rod 28 at the bottom of the concave plate 27 slides on the limiting block 19 and the inner wall of the storage box 17, thereby fixing and sorting the parts in the storage box 17, so that the required tools can be quickly obtained, thereby improving work efficiency.

[0042] Finally, it should be noted that the above is only 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 can still modify the technical solutions described in the aforementioned embodiments or make equivalent replacements for some of the technical features therein. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A tool for testing the strength of a mid-section of an aircraft fuselage, comprising a tool base (1), support legs (8) and a fuselage shell (14), characterized in that: The left end of the top side of the tooling base (1) is fixedly connected to the fuselage tail support frame (2), the front and rear sides of the tooling base (1) are fixedly connected to the vertical pole (3), the top side of the vertical pole (3) is fixedly connected to the pressure sensor (4), the top side of the pressure sensor (4) is fixedly connected to the threaded jack (5), the top sides of the two threaded jacks (5) are fixedly connected to the I-beam (6), the right end of the top side of the tooling base (1) is fixedly connected to the fuselage front end fixing frame (7), the front and rear sides of the support legs (8) are fixedly connected to the vertical pole (3), the top side of the pressure sensor (4) is fixedly connected to the threaded jack (5), the top sides of the two threaded jacks (5) are fixedly connected to the I-beam (6), the right end of the top side of the tooling base (1) is fixedly connected to the fuselage front end fixing frame (7), the front and rear sides of the support legs (8) are fixedly connected to the vertical pole (3), the top side of the pressure sensor (4) is fixedly connected to the threaded jack (5), the top side ... top side of the A lifting component is connected with a groove for fixing, the bottom of the lifting component is rotatably connected to a limiting sleeve (11), the bottom side of the limiting sleeve (11) is fixedly connected to a U-shaped plate (12), the inside of the two U-shaped plates (12) are movably connected to a pressure tube (13), the support leg (8) and the front side of one of the vertical poles (3) are fixedly connected to a storage box (17), the inner wall of the storage box (17) is slidably connected to a plurality of sliding plates (18), and the front and rear ends of the sliding plates (18) are fixedly connected to a limiting block (19).

2. The aircraft fuselage midsection strength loading test fixture according to claim 1, characterized in that: The inner wall of the limit block (19) is slidably connected to a pressing assembly for pressing subsequent components, the bottom side of the pressing assembly is fixedly connected to a fixing rod (22), the bottom side of the fixing rod (22) is fixedly connected to a disc (23), the bottom side of the disc (23) is fixedly connected to a spring (24), the front and rear ends of the bottom side of the pressing assembly are fixedly connected to an opening plate (25), the inside of the opening plate (25) is rotatably connected to a rotating plate (26), the far ends of each two rotating plates (26) are rotatably connected to a concave plate (27), and the bottom side of the concave plate (27) is fixedly connected to a limit rod (28).

3. The aircraft fuselage midsection strength loading test fixture according to claim 1, characterized in that: The lifting assembly comprises a threaded rod (9), the outer portions of the two threaded rods (9) being threadedly connected to the front and rear ends of the top of the support leg (8), the top side of the threaded rod (9) being fixedly connected to a handle (10), and the bottom side of the threaded rod (9) being fixedly connected to a circular plate (16).

4. The aircraft fuselage midsection strength loading test fixture according to claim 3, characterized in that: The outside of the circular plate (16) is rotatably connected to the inner wall of the limiting sleeve (11), and the bottom end of the threaded rod (9) is rotatably connected to the inside of the limiting sleeve (11).

5. The aircraft fuselage midsection strength loading test fixture according to claim 3, characterized in that: The bottom side of the fuselage shell (14) contacts the top side of the tooling base (1), the top side of the fuselage tail support frame (2) contacts the left end of the bottom side of the fuselage shell (14), the interior of each two U-shaped plates (12) contacts the front and rear ends of the pressure tube (13), and the right end of the fuselage shell (14) is slidably connected to the inside with a weight block (15).

6. The aircraft fuselage midsection strength loading test fixture according to claim 2, characterized in that: The pressing assembly comprises a sliding rod (20), the outer portion of the sliding rod (20) is slidably connected to the inner portion of the sliding plate (18), the top side of the sliding rod (20) is fixedly connected to a handle, and the bottom side of the sliding rod (20) is fixedly connected to a strip plate (21).

7. The aircraft fuselage midsection strength loading test fixture according to claim 6, characterized in that: The outside of the strip plate (21) is slidably connected to the inner wall of the sliding plate (18), and the bottom side of the strip plate (21) is fixedly connected to the top side of the fixing rod (22).

8. The aircraft fuselage midsection strength loading test fixture according to claim 7, characterized in that: The top sides of each of the two opening plates (25) are fixedly connected to the front and rear ends of the bottom side of one of the strip plates (21), and the outer portion of the limiting rod (28) is slidably connected to the inner wall of the limiting block (19), and the outer portion of the limiting rod (28) is slidably connected to the inner wall of the storage box (17).

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