Clamp device for involution processing of intersection points of fuselage and wings of airplane

Abstract

The utility model relates to the technical field of aircraft manufacturing, and discloses an aircraft fuselage and wing intersection involution processing clamp device which comprises a wing lug and a fuselage lug, a first mounting shell and a second mounting shell are arranged on the left side and the right side of the wing lug and the left side and the right side of the fuselage lug respectively, and a clamping block is fixedly installed on the side face of the first mounting shell. A clamping groove is formed in the side face of the second installation shell. According to the device, the clamping blocks are clamped in the clamping grooves for first-time fixing, then second-time fixing is carried out through cooperation between the bolts and the nuts, and then third-time fixing is carried out by moving the second threaded rods into the circular grooves; through three times of fixation, it can be ensured that the fuselage and the wings are kept stable in the intersection involution machining process, displacement or deformation caused by vibration or external force is reduced, and therefore the precision and consistency of the machining process can be ensured, the positions and postures of the fuselage and the wings can be more accurately controlled, and the intersection involution precision is ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft manufacturing, and more specifically to a fixture device for processing the intersection of an aircraft fuselage and a wing. Background Art

[0002] The fuselage-wing joint process is a key step in the aircraft manufacturing process, involving the stability of the aircraft's overall structure and flight performance. This process mainly involves the precise docking and fixing of the fuselage and wings to ensure that the connection between them is firm and reliable.

[0003] At present, the common method used in the processing of fuselage and wing joint is manual jointing. Although this method is widely used in the aircraft manufacturing process, it also has some obvious disadvantages. In the manual jointing process, the fuselage and the wing first need to be accurately adjusted on a dedicated bracket to ensure that they can be accurately joined. Subsequently, the initial joint fixation is achieved by inserting the locating pins. However, once the locating pins are pulled out, the positioning between the fuselage and the wing can only be maintained by their own weight, which undoubtedly increases the uncertainty and risk in the processing process. The main problem of manual jointing is its sensitivity to cutting force. During the processing, if the cutting force is too large, it is easy to cause the fuselage and the wing to shift. The shifting will not only cause the final processed hole position to be unable to accurately match, but also have an adverse effect on the overall structural stability of the aircraft. This adverse effect may be reflected in the decline of the aircraft's flight performance and the weakening of the structural strength, thereby seriously affecting the quality and safety of the aircraft. In addition, the manual jointing method also has problems such as low operating efficiency and difficulty in ensuring processing accuracy. Since the operation process relies on manual experience and skill level, it is difficult to ensure the consistency and stability of each processing. This not only increases the uncertainty in the processing, but also increases the manufacturing cost and time cost. Utility Model Content

[0004] In order to overcome the shortcomings of the prior art, the utility model provides a fixture device for processing the intersection of an aircraft fuselage and a wing, which has the advantage of good aircraft manufacturing effect.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a fixture device for processing the intersection of an aircraft fuselage and a wing, comprising a wing ear and a fuselage ear, wherein a first mounting shell and a second mounting shell are respectively provided on the left and right sides of the wing ear and the fuselage ear, a clamping block is fixedly installed on the side of the first mounting shell, and a clamping slot is provided on the side of the second mounting shell;

[0006] A fixing plate, the fixing plate is fixedly mounted on the side of the mounting housing 2, a sleeve 1 is fixedly mounted inside the fixing plate and extends to both ends, a threaded rod 1 is movably mounted inside the sleeve 1, a handle 1 is fixedly mounted on one end of the threaded rod 1, and an L-shaped plate is movably mounted on the other end of the threaded rod 1;

[0007] Sleeve 2, the sleeve 2 is fixedly installed inside the L-shaped plate and extends to both ends, threaded rod 2 is movably installed inside the sleeve 2, and handle 2 is fixedly installed at one end of the threaded rod 2;

[0008] A circular groove is provided on the side of the first mounting shell, and a threaded rod 2 is movably installed inside the first mounting shell.

[0009] As a preferred technical solution of the utility model, a rectangular groove 1 is provided on the front of the fuselage ear piece, and a mortise and tenon block 1 is movably installed inside the rectangular groove 1, and a rectangular groove 3 is provided on the front of the wing ear piece, and a mortise and tenon block 3 is movably installed inside the rectangular groove 3;

[0010] Rectangular groove two, the rectangular groove two is respectively opened on the side of the mounting shell one and the mounting shell two, and the mortise and tenon block two and the mortise and tenon block four are movably installed inside the rectangular groove two, and the mortise and tenon block two is clamped inside the mortise and tenon block one, and the mortise and tenon block four is clamped inside the mortise and tenon block three.

[0011] As a preferred technical solution of the utility model, the distance between the two protrusions on the front side of the wing ear is equal to the size of the protrusion on the front side of the fuselage ear.

[0012] As a preferred technical solution of the utility model, the number of the mortise and tenon blocks one is four groups, and the number of the mortise and tenon blocks three is two groups.

[0013] As a preferred technical solution of the utility model, the inner diameter of the card slot is equal to the outer diameter of the card block, and there are two groups of card slots and card blocks.

[0014] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0015] 1. The utility model inserts a bolt into the inside of the circular hole and extends it to the rightmost end, and then limits it through a nut, and then turns the handle one to make the threaded rod one rotate and move to the left end so that the L-shaped plate also moves synchronously, and then turns the handle two to make the threaded rod two rotate and move forward into the inside of the circular groove, so as to fix the installation shell one and the installation shell two. Compared with the traditional device, this device first uses a clamping block to be clamped in the inside of the clamping groove for the first fixation, and then the second fixation is performed by the cooperation between the bolt and the nut, and then the threaded rod two is moved to the inside of the circular groove for the third fixation. The three fixations can ensure that the fuselage and the wing remain stable during the intersection matching processing, reduce the displacement or deformation caused by vibration or external force, thereby helping to ensure the accuracy and consistency of the processing process, and can more accurately control the position and posture of the fuselage and the wing, thereby ensuring the accuracy of the intersection matching, and can also keep the fuselage and the wing relatively fixed during the processing, reduce the time wasted due to adjusting the position, thereby helping to speed up the processing speed and improve production efficiency.

[0016] 2. The utility model fixes the fuselage ear piece to the mounting shell one and the mounting shell two by clamping the mortise and tenon block one into the inside of the rectangular groove one and clamping the mortise and tenon block two into the inside of the rectangular groove two, and similarly fixes the wing ear piece to the mounting shell one and the mounting shell two through the cooperation of the mortise and tenon block three and the mortise and tenon block four. Compared with the traditional device, this device fixes the wing ear piece and the fuselage ear piece to the mounting shell one and the mounting shell two respectively through the mortise and tenon structure. This connection method has good stability and can keep the relative positions between the components unchanged when subjected to external force or vibration to prevent loosening or sliding. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the structure of the utility model;

[0018] Figure 2 This is a schematic diagram of the front structure of the utility model;

[0019] Figure 3 This is a schematic diagram of the structure of the explosive arrow of the utility model;

[0020] Figure 4 This is a schematic diagram of the structure of the body ear piece of the utility model;

[0021] Figure 5 For this utility model Figure 1 Schematic diagram of the local magnifying glass structure at point A in the middle.

[0022] In the figure: 1. wing ear; 2. fuselage ear; 3. mounting shell one; 4. mounting shell two; 5. round hole; 6. bolt; 7. nut; 8. fixing plate; 9. sleeve one; 10. threaded rod one; 11. handle one; 12. L-shaped plate; 13. sleeve two; 14. threaded rod two; 15. round groove; 16. handle two; 17. rectangular groove one; 18. mortise and tenon block one; 19. rectangular groove two; 20. mortise and tenon block two; 21. rectangular groove three; 22. mortise and tenon block three; 23. clamping groove; 24. clamping block; 25. mortise and tenon block four. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0024] like Figures 1 to 5 As shown, the utility model provides a fixture device for processing the intersection of an aircraft fuselage and a wing, comprising a wing ear piece 1 and a fuselage ear piece 2, a mounting shell 1 3 and a mounting shell 2 4 are respectively arranged on the left and right sides of the wing ear piece 1 and the fuselage ear piece 2, a clamping block 24 is fixedly installed on the side of the mounting shell 1 3, and a clamping slot 23 is opened on the side of the mounting shell 2 4;

[0025] A fixing plate 8 is fixedly mounted on the side of the mounting housing 2 4, a sleeve 9 is fixedly mounted inside the fixing plate 8 and extends to both ends, a threaded rod 10 is movably mounted inside the sleeve 9, a handle 11 is fixedly mounted on one end of the threaded rod 10, and an L-shaped plate 12 is movably mounted on the other end of the threaded rod 10;

[0026] A second sleeve 13, which is fixedly installed inside the L-shaped plate 12 and extends to both ends. A second threaded rod 14 is movably installed inside the second sleeve 13, and a second handle 16 is fixedly installed at one end of the second threaded rod 14;

[0027] A circular groove 15 is provided on the side of the mounting housing 1 3, and a threaded rod 2 14 is movably mounted inside the mounting housing 1 3;

[0028] When in use, the wing ear piece 1 and the fuselage ear piece 2 are first clamped together, and then the mounting shell 1 3 and the mounting shell 2 4 are respectively arranged on the left and right sides thereof, and the clamping blocks 24 enter the inside of the clamping groove 23. Then the staff inserts the bolt 6 into the inside of the circular hole 5 and extends it to the rightmost end and limits it by the nut 7. Then, the handle 1 11 is turned, and the threaded rod 10 rotates and moves forward inside the sleeve 1 9, thereby driving the L-shaped plate 12 at its front end to move forward synchronously. At this time, the handle 2 16 is turned, and the threaded rod 2 14 rotates and moves forward inside the sleeve 2 13 and enters the inside of the circular groove 15, thereby fixing the mounting shell 1 3 and the mounting shell 2 4;

[0029] After the bolt 6 is inserted into the circular hole 5 and extends to the rightmost end, it is limited by the nut 7 and then the handle 11 is turned to make the threaded rod 10 rotate and move to the left end so that the L-shaped plate 12 also moves synchronously. Then the handle 2 16 is turned to make the threaded rod 2 14 rotate and move forward into the circular groove 15 to fix the mounting shell 1 3 and the mounting shell 2 4. Compared with the traditional device, this device first uses the clamping block 24 to clamp in the inside of the clamping groove 23 for the first fixation, and then the second fixation is performed by the cooperation between the bolt 6 and the nut 7, and then the threaded rod 2 14 is moved to the inside of the circular groove 15 for the third fixation. The three fixations can ensure that the fuselage and the wing remain stable during the intersection matching processing, reduce the displacement or deformation caused by vibration or external force, thereby helping to ensure the accuracy and consistency of the processing process, and can more accurately control the position and posture of the fuselage and the wing, thereby ensuring the accuracy of the intersection matching, and can also keep the fuselage and the wing relatively fixed during the processing, reduce the time wasted due to adjusting the position, thereby helping to speed up the processing speed and improve production efficiency.

[0030] The front of the fuselage ear piece 2 is provided with a rectangular groove 17, and a mortise and tenon block 18 is movably installed inside the rectangular groove 17; the front of the wing ear piece 1 is provided with a rectangular groove 3 21, and a mortise and tenon block 3 22 is movably installed inside the rectangular groove 3 21;

[0031] Rectangular groove 2 19, rectangular groove 2 19 is respectively opened on the side of mounting shell 1 3 and mounting shell 2 4, and mortise and tenon block 2 20 and mortise and tenon block 4 25 are movably installed inside rectangular groove 2 19, and mortise and tenon block 2 20 is clamped inside mortise and tenon block 1 18, and mortise and tenon block 4 25 is clamped inside mortise and tenon block 3 22;

[0032] When the installation shell 1 3 and the installation shell 2 4 are installed, the mortise and tenon block 1 18 is clamped into the inside of the rectangular groove 1 17, and the mortise and tenon block 2 20 is clamped into the inside of the mortise and tenon block 1 18 through the rectangular groove 2 19, so that the fuselage ear piece 2 is fixed to the installation shell 1 3 and the installation shell 2 4, and then the mortise and tenon block 3 22 is clamped into the inside of the rectangular groove 3 21 and the mortise and tenon block 4 25 is clamped into the inside of the mortise and tenon block 3 22 through the rectangular groove 2 19, so that the wing ear piece 1 is fixed to the installation shell 1 3 and the installation shell 2 4;

[0033] The fuselage ear 2 is fixed to the mounting shell 1 3 and the mounting shell 2 4 by clamping the mortise and tenon block 1 18 into the interior of the rectangular groove 17 and the mortise and tenon block 2 20 into the interior of the rectangular groove 2 19. Similarly, the wing ear 1 is fixed to the mounting shell 1 3 and the mounting shell 2 4 by the cooperation of the mortise and tenon block 3 22 and the mortise and tenon block 4 25. Compared with the traditional device, this device fixes the wing ear 1 and the fuselage ear 2 to the mounting shell 1 3 and the mounting shell 2 4 respectively through the mortise and tenon structure. This connection method has good stability and can keep the relative positions between the components unchanged when subjected to external force or vibration to prevent loosening or sliding.

[0034] The distance between the two protrusions on the front of the wing ear piece 1 is equal to the size of the protrusion on the front of the fuselage ear piece 2;

[0035] The distance between the two protrusions on the front of the wing ear 1 is equal to the size of the protrusion on the front of the fuselage ear 2. This design allows the protrusion on the front of the fuselage ear 2 to be better clamped between the two protrusions on the front of the wing ear 1, and the bolt 6 makes it more secure.

[0036] Among them, there are four groups of mortise and tenon blocks 18, and two groups of mortise and tenon blocks 3 22;

[0037] There are four groups of mortise and tenon blocks 18 and two groups of mortise and tenon blocks 3 22. The four groups of mortise and tenon blocks 18 make the fuselage ear piece 2 and the mounting shell 1 3 and the mounting shell 2 4 more firmly connected. The two groups of mortise and tenon blocks 3 22 make the wing ear piece 1 and the mounting shell 1 3 and the mounting shell 2 4 more firmly connected.

[0038] The inner diameter of the slot 23 is equal to the outer diameter of the block 24, and there are two groups of slots 23 and blocks 24.

[0039] The inner diameter value of the slot 23 and the outer diameter value of the block 24 are set to be equal in size, so that the friction force generated when the block 24 enters the slot 23 is larger, thereby ensuring the fixation of the mounting shell 1 3 and the mounting shell 2 4. There are two groups of slots 23 and blocks 24, so that the fixing effect is better.

[0040] The working principle and use process of this utility model:

[0041] When in use, the wing ear 1 and the fuselage ear 2 are first clamped together, and then the mounting shell 1 3 and the mounting shell 2 4 are respectively arranged on the left and right sides thereof, and the rear clamping block 24 enters the interior of the clamping groove 23. Then the staff inserts the bolt 6 into the interior of the circular hole 5 and extends it to the rightmost end and limits it by the nut 7. Then, the handle 11 is turned, and the threaded rod 10 rotates and moves forward inside the sleeve 9, thereby driving the L-shaped plate 12 at its front end to move forward synchronously. At this time, the handle 2 16 is turned, and the threaded rod 2 14 rotates and moves forward inside the sleeve 2 13 and enters the interior of the circular groove 15 to fix the mounting shell 1 3 and the mounting shell 2 4.

[0042] When the installation shell 1 3 and the installation shell 2 4 are installed, the mortise and tenon block 18 is clamped into the inside of the rectangular groove 17, and the mortise and tenon block 20 is clamped into the inside of the mortise and tenon block 18 through the rectangular groove 2 19, so that the fuselage ear piece 2 is fixed to the installation shell 1 3 and the installation shell 2 4, and then the mortise and tenon block 3 22 is clamped into the inside of the rectangular groove 3 21 and the mortise and tenon block 4 25 is clamped into the inside of the mortise and tenon block 3 22 through the rectangular groove 2 19, so that the wing ear piece 1 is fixed to the installation shell 1 3 and the installation shell 2 4.

[0043] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0044] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A fixture device for processing the intersection of an aircraft fuselage and a wing, comprising a wing ear piece (1) and a fuselage ear piece (2), characterized in that: The left and right sides of the wing ear piece (1) and the fuselage ear piece (2) are respectively provided with a mounting shell 1 (3) and a mounting shell 2 (4); a clamping block (24) is fixedly mounted on the side of the mounting shell 1 (3), and a clamping slot (23) is provided on the side of the mounting shell 2 (4); A fixing plate (8), the fixing plate (8) being fixedly mounted on the side of the second mounting shell (4), a sleeve (9) being fixedly mounted inside the fixing plate (8) and extending to both ends, a threaded rod (10) being movably mounted inside the sleeve (9), a handle (11) being fixedly mounted on one end of the threaded rod (10), and an L-shaped plate (12) being movably mounted on the other end of the threaded rod (10); A second sleeve (13), the second sleeve (13) is fixedly installed inside the L-shaped plate (12) and extends to both ends, a second threaded rod (14) is movably installed inside the second sleeve (13), and a second handle (16) is fixedly installed at one end of the second threaded rod (14); A circular groove (15) is provided on the side of the first mounting shell (3), and a second threaded rod (14) is movably installed inside the first mounting shell (3).

2. The fixture device for processing the intersection of an aircraft fuselage and a wing according to claim 1, characterized in that: The front face of the fuselage ear piece (2) is provided with a rectangular groove one (17), and a mortise and tenon block one (18) is movably installed inside the rectangular groove one (17); the front face of the wing ear piece (1) is provided with a rectangular groove three (21), and a mortise and tenon block three (22) is movably installed inside the rectangular groove three (21); A rectangular groove 2 (19), wherein the rectangular groove 2 (19) is respectively provided on the side of the mounting shell 1 (3) and the mounting shell 2 (4), wherein the interior of the rectangular groove 2 (19) is movably provided with a mortise and tenon block 2 (20) and a mortise and tenon block 4 (25), and the mortise and tenon block 2 (20) is clamped in the interior of the mortise and tenon block 1 (18), and the mortise and tenon block 4 (25) is clamped in the interior of the mortise and tenon block 3 (22).

3. The fixture device for processing the intersection of an aircraft fuselage and a wing according to claim 1, characterized in that: The distance between the two protrusions on the front side of the wing ear piece (1) is equal to the size of the protrusion on the front side of the fuselage ear piece (2).

4. The fixture device for processing the intersection of an aircraft fuselage and a wing according to claim 2, characterized in that: The number of the mortise and tenon blocks one (18) is four groups, and the number of the mortise and tenon blocks three (22) is two groups.

5. The fixture device for processing the intersection of an aircraft fuselage and a wing according to claim 1, characterized in that: The inner diameter of the clamping slot (23) is equal to the outer diameter of the clamping block (24), and there are two groups of the clamping slot (23) and the clamping block (24).

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