A tooling for measuring the riveting strength of aircraft damper skin

Abstract

This utility model provides a fixture for measuring the riveting strength of aircraft damper skin. A base positioning post is fixed to one side of the bottom of the base, and a top plate is fixed to one side of the top of the base via symmetrically arranged vertical plates. The damper assembly to be tested is fixed to the top of the top plate by multiple bolt assemblies. It also includes a pressure block assembly for applying pressure to the edge of the damper assembly's skin. The pressure block assembly includes two different types: a type I pressure block and a type II pressure block. A connecting plate is fixed to the top of each type I and type II pressure block, and a connecting post is fixed to the top of the connecting plate. The connecting post has a first locking pin hole machined on it for positioning and connecting with the lower pressure bushing of a tensile testing bench. This fixture, in conjunction with the tensile testing bench, can distribute the downward pressure force of the lower pressure bushing more evenly on the skin, thereby obtaining accurate measurement data and conveniently and accurately measuring the riveting strength of the aircraft damper skin.

Description

Technical Field

[0001] This utility model relates to the field of aviation equipment manufacturing, and in particular to a tooling for measuring the riveting strength of aircraft windshield skin. Background Technology

[0002] The riveting quality of aircraft damper skin directly affects the safety and performance of the aircraft. Insufficient riveting strength can lead to serious consequences such as skin loosening and detachment, threatening aircraft safety. Currently, there is a lack of convenient and accurate tooling for measuring the riveting strength of aircraft damper skin during aircraft manufacturing and maintenance. Existing inspection methods and tooling suffer from problems such as complex operation, inaccurate measurement results, and inability to truly and effectively reflect the stress at the riveting joints during actual use, failing to meet the requirements of high efficiency and precision in aircraft manufacturing and inspection. Utility Model Content

[0003] The purpose of this invention is to overcome the aforementioned shortcomings and provide a fixture for measuring the riveting strength of aircraft damper skin. This fixture effectively solves the problem that the complex curved surface of the skin makes it difficult to effectively fix and measure the riveting strength. This fixture, in conjunction with a tensile testing bench, can distribute the force applied by the downward pressure of the lower bushing more evenly across the skin. This results in accurate measurement data, addressing the deficiencies of existing measuring fixtures mentioned in the background section and enabling convenient and accurate measurement of the riveting strength of aircraft damper skin.

[0004] To achieve the above-mentioned technical features, the purpose of this utility model is as follows: a tooling for measuring the riveting strength of an aircraft damper skin, including a base, a base positioning column fixed on one side of the bottom of the base, a top plate fixed on one side of the top of the base by symmetrically arranged vertical plates, and a damper assembly to be tested fixedly installed on the top of the top plate by multiple bolt assemblies. It also includes a pressure block assembly for applying pressure to the skin at the edge of the wind turbine assembly; The pressing block assembly includes two different types of pressing blocks: Type I pressing blocks and Type II pressing blocks. Both the type I and type II pressure blocks have a connecting plate fixed to their tops. A connecting column is fixed to the top of the connecting plate, and a first locking pin hole is machined on the connecting column for positioning and connecting with the lower pressure bushing of the tensile testing table.

[0005] Preferably, a reinforcing plate is provided at the bottom of the base and in the area where the base positioning post is located.

[0006] Preferably, the base positioning post is provided with a second locking pin hole, which is used to fix the base of the tensile testing table after the locking pin passes through.

[0007] Preferably, the upper surface of the top plate has an arc-shaped top surface and is fitted to the outer surface of the damper assembly.

[0008] Preferably, the bolt assembly includes a long bolt that passes through bolt holes in the damper assembly and the top plate, and a nut is fixed to the other end of the long bolt.

[0009] Preferably, the bottom end of the connecting column is machined with a threaded post, and a locking nut is installed on the threaded post to be tightly connected to the lower pressure bushing of the tensile testing table.

[0010] Preferably, the bottom end face of the type I and type II pressing blocks adopts an arc-shaped structure and matches the surface of the skin.

[0011] Preferably, the size of the first-type pressing block is larger than the size of the second-type pressing block.

[0012] Preferably, the base, upright plate, top plate, and reinforcing plate are all assembled and welded from Q235 carbon structural steel.

[0013] Preferably, the type I pressure block, type II pressure block, connecting plate, and connecting column are all assembled and welded from Q235 carbon structural steel.

[0014] The present invention has the following beneficial effects: 1. This utility model tooling, when used in conjunction with a tensile testing bench, can distribute the pressure force of the lowering bushing more evenly on the skin. This results in accurate measurement data, addressing the shortcomings of existing measuring tooling mentioned in the background section, and enabling convenient and accurate measurement of the riveting strength of aircraft windshield skin.

[0015] 2. This fixture can be quickly installed on a tensile testing bench via a pin mechanism. It applies pressure to the skin riveting joint using pressure blocks, and measures the magnitude of the downward pressure using sensors on the tensile testing bench. This allows for accurate measurement of the riveting strength of the aircraft windshield skin, providing reliable data support for aircraft manufacturing and maintenance.

[0016] 3. The detachable design makes it easier to install the tooling onto the tensile testing table. The two pressure blocks of different sizes can more effectively simulate the actual working conditions to measure the riveting strength, making the measurement results more reflective of the actual situation.

[0017] 4. The damper skin riveting strength fixture uses Q235 carbon structural steel as the main material. This material has good strength, low cost and excellent welding performance, which can meet the test requirements. Attached Figure Description

[0018] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0019] Figure 1 This is a first-person three-dimensional view of the present invention when using a type of pressing block.

[0020] Figure 2This is a second-view three-dimensional image of the present invention when a type of pressing block is used.

[0021] Figure 3 This is a three-dimensional view from a third perspective when the present invention uses a type of pressing block.

[0022] Figure 4 This is a first-person 3D view of the present invention when the damper assembly is removed.

[0023] Figure 5 This is a second-view 3D diagram of the present invention with the damper assembly removed.

[0024] Figure 6 This is a third-person 3D view of the present invention when the damper assembly is removed.

[0025] Figure 7 This is a first-view three-dimensional view of the present invention when using a type II pressing block.

[0026] Figure 8 This is a second-view three-dimensional diagram of the present invention when using a type II pressing block.

[0027] Figure 9 This is a three-dimensional structural diagram of the compression block of this utility model.

[0028] Figure 10 This is a three-dimensional structural diagram of the type II pressure block of this utility model.

[0029] In the diagram: 1. Base plate; 2. Vertical plate; 3. Top plate; 4. Long bolt; 5. Damper assembly; 6. Reinforcing plate; 7. Second locking pin hole; 8. Base positioning post; 9. Skin; 10. Type I pressure block; 11. Connecting plate; 12. Threaded post; 13. Connecting post; 14. First locking pin hole; 15. Nut; 16. Arc-shaped top surface; 17. Type II pressure block. Detailed Implementation

[0030] The embodiments of this utility model will be further described below with reference to the accompanying drawings.

[0031] See Figure 1-10A fixture for measuring the riveting strength of aircraft damper skin includes a base 1, with a base positioning post 8 fixed to one side of the bottom of the base 1, and a top plate 3 fixed to one side of the top of the base 1 via symmetrically arranged vertical plates 2. The top of the top plate 3 is fixedly mounted with a damper assembly 5 to be tested via multiple bolt assemblies. The fixture also includes a pressure block assembly for applying pressure to the skin 9 at the edge of the damper assembly 5. The pressure block assembly includes two different types: a type 1 pressure block 10 and a type 2 pressure block 17. A connecting plate 11 is fixed to the top of each of the type 1 and type 2 pressure blocks 17. A connecting post 13 is fixed to the top of the connecting plate 11, and a first locking pin hole 14 is machined on the connecting post 13 for positioning and connecting with the lower pressure bushing of a tensile testing bench. This fixture, in conjunction with the tensile testing bench, can distribute the downward pressure of the lower pressure bushing more evenly on the skin, thereby obtaining accurate measurement data. This addresses the shortcomings of existing measuring fixtures mentioned in the background art, enabling convenient and accurate measurement of the riveting strength of aircraft damper skin. In practical use, the fan assembly 5 is fixed to the top of the top plate 3 by bolt assembly. Then, the type I pressure block 10 or type II pressure block 17 is selectively installed on the lower pressure bushing of the tensile test bench, and the tensile test bench is started. The type I pressure block 10 or type II pressure block 17 is pressed on the upper surface of the skin 9, thereby applying pressure to the skin 9 to achieve the purpose of rapid measurement of the riveting strength of the skin.

[0032] Furthermore, the bolt assembly ensures that the position of the skin 9 will not shift during the strength test, thus improving the accuracy of the test.

[0033] Furthermore, a reinforcing plate 6 is provided at the bottom of the base 1, in the area where the base positioning post 8 is located. The reinforcing plate 6 enhances the connection strength and reliability between the base plate 1 and the base positioning post 8.

[0034] Furthermore, the base positioning post 8 is machined with a second locking pin hole 7, which is used to position and fix the locking pin to the tensile testing table base after the locking pin passes through. The second locking pin hole 7 facilitates a reliable assembly connection between the locking pin and the tensile testing table base.

[0035] Furthermore, the upper surface of the top plate 3 adopts an arc-shaped top surface 16 and is attached to the outer surface of the damper assembly 5. The arc-shaped top surface 16 ensures a reliable fit and fixation between the damper assembly 5 and the top plate 3, thereby ensuring reliable fixation of the damper assembly 5 and ensuring stable support of the damper assembly 5.

[0036] Furthermore, the bolt assembly includes a long bolt 4, which passes through bolt holes on the damper assembly 5 and the top plate 3, and a nut 15 is fixed to the other end of the long bolt 4. This bolt assembly reliably fixes the damper assembly 5 to the top of the top plate 3, ensuring reliable fixation of the damper assembly 5 during subsequent pressure tests.

[0037] Furthermore, the bottom end of the connecting column 13 is machined with a threaded column 12, and a locking nut is fitted on the threaded column 12 to tightly connect with the lower pressure bushing of the tensile testing table. The threaded column 12 facilitates the subsequent installation of the locking nut, thereby reliably fixing the corresponding type I pressure block 10 or type II pressure block 17 to the lower pressure bushing of the tensile testing table.

[0038] Furthermore, the bottom surfaces of the type I pressure block 10 and type II pressure block 17 adopt an arc-shaped structure and mate with the surface of the skin 9. This arc-shaped structure ensures the uniformity of force on the skin 9 during subsequent tests, thereby guaranteeing the accuracy and reliability of the test data.

[0039] Furthermore, the size of the first-type pressure block 10 is larger than the size of the second-type pressure block 17. By using the two sets of first-type pressure blocks 10 and second-type pressure blocks 17 of different sizes, the actual working conditions can be simulated more effectively to measure the riveting strength.

[0040] Furthermore, the base 1, upright plate 2, top plate 3, and reinforcing plate 6 are all assembled and welded from Q235 carbon structural steel. The use of these materials ensures structural stability and reliability, effectively preventing deformation.

[0041] Furthermore, the type I pressure block 10, type II pressure block 17, connecting plate 11, and connecting column 13 are all assembled and welded from Q235 carbon structural steel. By using the aforementioned materials for assembly and welding, the structural stability and reliability are ensured, effectively preventing deformation.

[0042] The working process and principle of this utility model: The base 1 is connected to the tensile testing table via the base positioning column 8, providing stable support for the entire fixture; the long bolt 4 is used to fix the aircraft windshield assembly 5 to the top plate 3, ensuring the stability of the skin position during the measurement process; the type I pressure block 10 or type II pressure block 17 is mainly used to connect the lower pressure bushing of the tensile testing table, ensuring that the force can be more evenly distributed on the skin 9 when the lower pressure bushing of the tensile testing table is pressed down. The two pressure blocks of different sizes can more effectively simulate the actual working conditions to measure the riveting strength.

[0043] When using it, first install the measuring fixture into the corresponding position on the tensile testing table by locking it with the pin and M24 nut, such as... Figure 1As shown, the aircraft damper assembly is then fixed to the top plate 3. According to the testing requirements, downward pressure is applied to the skin 9 using a test bench. Operators can assess the riveting strength based on the measurement data. Compared with existing technologies, this fixture has significant advantages. It has low manufacturing costs, enables rapid and accurate measurement of the riveting strength of the aircraft damper skin, improves testing efficiency and accuracy, and can be quickly clamped onto a tensile testing bench, reducing human error. Its reasonable structural design and simple operation effectively reduce testing costs.

Claims

1. An aircraft wind door skin rivet strength measurement fixture, characterized by, Includes a base (1), a base positioning column (8) is fixed on one side of the bottom of the base (1), and a top plate (3) is fixed on one side of the top of the base (1) by symmetrically arranged vertical plates (2). The damper assembly (5) to be tested is fixedly installed on the top of the top plate (3) by multiple bolt assemblies. It also includes a pressure block assembly for applying pressure to the skin (9) at the edge of the damper assembly (5); The pressing assembly includes two different types of pressing blocks: Type I (10) and Type II (17). The top of the first type of pressure block (10) and the second type of pressure block (17) are respectively fixed with a connecting plate (11), and the top of the connecting plate (11) is fixed with a connecting column (13). The connecting column (13) is machined with a first locking pin hole (14) for positioning and connecting with the lower pressure bushing of the tensile test bench.

2. The rivet joint strength measuring tool for aircraft door skin according to claim 1, characterized in that: A reinforcing plate (6) is provided at the bottom of the base (1) and in the area where the base positioning post (8) is located.

3. The rivet joint strength measuring tool for aircraft door skin as defined in claim 1 wherein: The base positioning post (8) is machined with a second locking pin hole (7), which is used to fix the base of the tensile test bench after the locking pin passes through.

4. The rivet joint strength measuring tool for aircraft door skin as defined in claim 1 wherein: The upper surface of the top plate (3) adopts an arc-shaped top surface (16) and is attached to the outer surface of the damper assembly (5).

5. The rivet joint strength measuring tool for aircraft door skin as defined in claim 1 wherein: The bolt assembly includes a long bolt (4) that passes through bolt holes on the damper assembly (5) and the top plate (3), and a nut (15) is fixed to the other end of the long bolt (4).

6. The rivet joint strength measuring tool for aircraft door skin as defined in claim 1 wherein: The bottom end of the connecting column (13) is machined with a threaded column (12), and a locking nut is installed on the threaded column (12) to be tightly connected to the lower pressure bushing of the tensile test bench.

7. The aircraft windshield skin riveting strength measuring fixture according to claim 1, characterized in that: The bottom surfaces of the type I pressure block (10) and type II pressure block (17) adopt an arc-shaped structure and cooperate with the surface of the skin (9).

8. The rivet joint strength measuring tool for aircraft door skin as defined in claim 1 wherein: The size of the first type of pressure block (10) is larger than the size of the second type of pressure block (17).

9. The rivet joint strength measuring tool for aircraft door skin as defined in claim 2 wherein: The base (1), upright plate (2), top plate (3) and reinforcing plate (6) are all assembled and welded from Q235 carbon structural steel.

10. The rivet joint strength measuring tool for aircraft door skins of claim 1 wherein: The type I pressure block (10), type II pressure block (17), connecting plate (11) and connecting column (13) are all assembled and welded from Q235 carbon structural steel.

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