A riveting head mechanism and riveting method for complex cavity structures of aircraft

Abstract

The present invention discloses a riveting head mechanism and a riveting method for complex cavity structures of aircraft, including a fixing plate, a rotating plate, a rotating shaft, a compactor, a riveting head, a base, and a spring. The fixing plate is sleeved and fixed on a riveting machine through a hydraulic transmission rod. A station locking hole is provided on the fixing plate. The rotating plate is detachably connected to the fixing plate. A plurality of station switching holes are provided on the rotating plate. The base is fixed on the rotating plate, and the riveting head is fixed at the end of the base. The compactor is a thin-walled rotary body structure and is sleeved on the riveting head together with the spring. One end of the spring abuts against the boss of the riveting head, and the other end abuts against the compactor. The present invention uses the riveting head to avoid the interference of the flanging of complex cavity structure parts, and the rotating mechanism enables the riveting head mechanism to quickly switch stations; a pressure foot is added to apply a pre-compression force to the workpiece to eliminate the influence of non-uniform normal directions; the split structure can be popularized and applied to products with other similar structures.

Description

Technical Field

[0001] The present invention relates to a riveting technology in the field of aircraft manufacturing, specifically a riveting head mechanism and a riveting method for complex cavity structures of aircraft. Background Art

[0002] The riveting technology is a commonly used riveting technology in the field of aircraft assembly. At present, it is mainly applied to products with open spaces such as beams and ribs and flat outer shapes. For products such as aircraft cabin doors with complex cavities and large-curvature skin structures, using traditional riveting technology has two disadvantages: one is that the parts of such products often have flanges, and during riveting, the riveting head interferes with the flange and cannot be riveted; the second is that the space is relatively narrow, and it is inconvenient to switch the working position of the riveting head; the third is that due to the curvature of the skin, it is difficult to ensure the normal alignment of the rivets during riveting, and the upset head is easily deformed. Summary of the Invention

[0003] The purpose of the present invention is to provide a riveting head mechanism suitable for products with complex cavity and hyperbolic skin structures in view of the deficiencies of the existing riveting technology, which can not only ensure the riveting quality but also expand the application range of the riveting technology.

[0004] A riveting head mechanism for complex cavity structures of aircraft includes a fixing plate, a rotating plate, a rotating shaft, a compressor, a riveting head, a base, and a spring. The two sides of the fixing plate are provided with positioning holes consistent with the hydraulic transmission rods on the riveting machine, and a rotating shaft through-hole is provided in the center. The fixing plate is sleeved and fixed on the riveting machine through the hydraulic transmission rods. On the center line connecting the two hydraulic transmission rod positioning holes on the fixing plate, a working position locking hole is provided near the side edge of the fixing plate. The rotating plate is a circular plate structure, and a rotating shaft through-hole is provided in the center. The rotating shaft passes through the through-holes in the centers of the fixing plate and the rotating plate, and the rotating plate and the fixing plate are fixed by a detachable screw connection. A plurality of working position switching holes are evenly distributed on the rotating plate. The base is an "L" - shaped structure and is fixed on the rotating plate. The riveting head is fixed at the end of the base. The compressor is a thin - walled rotating body structure and is sleeved on the riveting head together with the spring. One end of the spring abuts against the boss of the riveting head, and the other end abuts against the compressor.

[0005] Further, a long circular hole is opened on the side surface of the compressor, and a circular hole is opened on the side surface of the riveting head. A pin passes through the long circular hole of the compressor and is fixed in the circular hole of the riveting head to limit the compressor, and the compressor can slide relative to the riveting head.

[0006] Further, the protruding amount δ of the lower end of the compressor from the end surface of the riveting head has the following relationship with the length h of the rivet and the sandwich thickness σ: δ=(h - σ)×0.8.

[0007] Further, the rotating plate is provided with 4 station switching holes, including a 0° station switching hole, a 90° station switching hole, a 180° station switching hole, and a 270° station switching hole. After the rotating plate rotates around the rotating shaft until any station switching hole coincides with the station locking hole, the locking pin is inserted into the hole to lock the orientation of the riveting head.

[0008] A method of riveting using the above-mentioned riveting head mechanism for complex cavity structures of aircraft includes the following steps:

[0009] 1. The product to be riveted enters the station between the riveting head mechanism and the lower riveting head, so that the riveting head mechanism is located above the product to be riveted with a complex cavity structure;

[0010] 2. Lower the height of the riveting head mechanism so that the end of the base is lower than the upper edge of the cavity of the product and bypass the cavity flanging;

[0011] 3. Adjust the posture of the product so that the riveting head is aligned with the rivet head;

[0012] 4. Start the riveting machine, the riveting head mechanism descends, enters the cavity, the compactor contacts the skin surface to be riveted on the bottom surface of the cavity, and applies a pre-compression force to flatten the local skin around the rivet to be riveted;

[0013] 5. When the spring compression reaches the limit, the riveting head mechanism and the lower riveting head jointly apply pressure to the rivet to complete the riveting work;

[0014] 6. Move the product to the next riveting position to continue riveting until all the single-row rivets are riveted;

[0015] 7. Pull out the locking pin, loosen the rotating shaft, rotate the rotating plate to adjust the riveting head mechanism to other stations in turn, then insert the locking pin to fix it, and repeat steps 1 to 5 until all the rivets at all stations are riveted.

[0016] The advantages of the present invention are as follows: 1) The "L"-shaped outer shape of the base allows the riveting head to bypass the interference of the part flange during the descending process, and the addition of a rotating mechanism enables the riveting head mechanism to quickly switch stations; 2) A pre-compression force can be applied to the workpiece during riveting to flatten the local skin before the rivet is fully deformed, eliminating the influence of non-uniform normal direction; 3) Adopting a split structure, splitting the stress part and the connecting part into the riveting head and the base, and by designing bases with different outer shapes, it can be widely applied to other products with similar structures.

[0017] The following further describes the present invention in detail with reference to the accompanying drawings and examples. Description of the Drawings

[0018] Figure 1 It is a three-dimensional schematic diagram of the riveting head mechanism

[0019] Figure 2Schematic diagram of the connection structure of the compactor, riveting head and spring and the working principle of the riveting head mechanism

[0020] Figure 3 Exploded view of the rotating mechanism of the riveting head

[0021] Figure 4 Schematic diagram of the working state of the rotating mechanism of the riveting head

[0022] Figure 5 Schematic diagram of the working state of the riveting head mechanism

[0023] Explanation of the numbers in the figure: 1. Fixed plate; 2. Rotating plate; 3. Rotating shaft; 4. Locking pin; 5. Compactor; 6. Riveting head; 7. Base; 8. Spring; 9. Pin; 10. Hatch door; 11. Skin; 12. Flanged doorframe; 13. Riveting head mechanism; 14. Lower riveting head; 15. Hydraulic drive rod positioning hole; 16. Station locking hole; 17. Rotating shaft through hole; 18. 0° station switching hole; 19. 90° station switching hole; 20. 180° station switching hole; 21. 270° station switching hole Detailed implementation method

[0024] In this embodiment, as Figure 1 shown, a riveting head mechanism for the complex cavity structure of an aircraft includes a fixed plate 1, a rotating plate 2, a rotating shaft 3, a locking pin 4, a compactor 5, a riveting head 6, a base 7, a spring 8, and a pin 9. Hydraulic drive rod positioning holes 15 consistent with the hydraulic drive rods on the riveting machine are provided on both sides of the fixed plate 1, and a rotating shaft through hole 17 is provided in the center. The fixed plate 1 is sleeved and fixed on the riveting machine through the hydraulic drive rods. On the center line connecting the two hydraulic drive rod positioning holes on the fixed plate 1, 1 station locking hole 16 is provided near the side edge of the fixed plate 1. The rotating plate 2 is a circular plate-like structure, and a rotating shaft 3 through hole is provided in the center. The rotating shaft 3 passes through the through holes in the centers of the fixed plate 1 and the rotating plate 2, and the rotating plate 2 and the fixed plate 1 are fixed by a detachable screw connection method. In this example, 4 station switching holes are evenly distributed on the rotating plate 2, namely the 0° station switching hole 18, the 90° station switching hole 19, the 180° station switching hole 20, and the 270° station switching hole 21. The base 7 is an "L"-shaped structure and is fixed on the rotating plate 2. The riveting head 6 is fixed at the end of the base 7. The compactor 5 is a thin-walled rotating body structure and is sleeved on the riveting head 6 together with the spring 8. One end of the spring 8 abuts against the boss of the riveting head 6, and the other end abuts against the compactor 5.

[0025] As Figure 1 shown, a long circular hole is opened on the side of the compactor 5, a circular hole is opened on the side of the riveting head 6, and the pin 9 passes through the long circular hole of the compactor 5 and is fixed in the circular hole of the riveting head 6 to limit the compactor 5, and the compactor 5 can slide relative to the riveting head 6.

[0026] As Figure 2As shown, the lower end of the presser 5 needs to protrude from the end face of the riveting head 6. The relationship between the protrusion amount δ, the rivet length h, and the sandwich thickness σ is: δ = (h - σ) × 0.8.

[0027] The pressers with different protrusion amounts manufactured according to the above relationship are verified in practice as follows:

[0028] 1 When the rivet length h is 14 mm and the sandwich thickness σ is 9 mm, the protrusion amount δ = (h - σ) × 0.8 = 4 mm. After riveting, the height of the rivet upset head can reach 1.5 mm, meeting the quality requirements.

[0029] 2 When the rivet length h is 16 mm and the sandwich thickness σ is 12 mm, the protrusion amount δ = (h - σ) × 0.8 = 3.2 mm. After riveting, the height of the rivet upset head can reach 1.5 mm, meeting the quality requirements.

[0030] As Figure 3 and Figure 4 shown, the fixed plate 1 is provided with 1 station locking hole 16, and the rotating plate 2 is provided with 4 station switching holes. The rotating plate 2 rotates around the rotating shaft 3 until the station switching hole coincides with the station locking hole, and the locking pin 4 is inserted into the hole to lock the orientation of the riveting head.

[0031] As Figure 2 , Figure 3 , Figure 4 and Figure 5 shown, a method for riveting using the above-mentioned riveting head mechanism includes the following steps:

[0032] 1 The product to be riveted enters the station between the riveting head mechanism and the lower riveting head 14, and the riveting head mechanism is located above the product to be riveted with a complex cavity structure;

[0033] 2 Lower the height of the riveting head mechanism so that the end of the base 7 is lower than the upper edge of the cavity of the product and bypass the cavity flange;

[0034] 3 Adjust the posture of the product so that the riveting head 6 is aligned with the rivet head;

[0035] 4 Start the riveting machine, the riveting head mechanism descends, enters into the cavity, the presser 5 contacts the surface of the skin to be riveted on the bottom surface of the cavity, and applies a pre-pressing force to flatten the local skin around the rivet to be riveted;

[0036] 5 When the compression amount of the spring 8 reaches the limit, the riveting head mechanism and the lower riveting head 14 jointly apply pressure to the rivet to complete the riveting work;

[0037] 6 Move the product to the next riveting position to continue riveting until all the single-row rivets are riveted;

[0038] 7 Pull out the locking pin 4, loosen the rotating shaft 3, rotate the rotating plate 2 to adjust the riveting head mechanism to other workstations in sequence, then insert the locking pin 4 to fix it, and repeat steps 1 to 5 until the riveting of all workstations is completed.

Claims

1. A riveting method for complex cavity structures of aircraft, characterized in that A riveting head mechanism for a complex cavity structure of an aircraft is used for riveting. The riveting head mechanism includes a fixing plate, a rotating plate, a rotating shaft, a compressor, a riveting head, a base, and a spring. Positioning holes consistent with the hydraulic transmission rods on the riveting machine are provided on both sides of the fixing plate, and a rotating shaft through hole is provided in the center. The fixing plate is sleeved and fixed on the riveting machine through the hydraulic transmission rods. On the center line connecting the two hydraulic transmission rod positioning holes on the fixing plate, a station locking hole is provided near the side edge of the fixing plate. The rotating plate is a circular plate-like structure, and a rotating shaft through hole is provided in the center. The rotating shaft passes through the through holes in the centers of the fixing plate and the rotating plate, and the rotating plate and the fixing plate are fixed by a detachable screwing method. A plurality of station switching holes are evenly distributed on the rotating plate. The base is an "L" - shaped structure and is fixed on the rotating plate. The riveting head is fixed at the end of the base. The compressor is a thin - walled rotating body structure and is sleeved on the riveting head together with the spring. One end of the spring abuts against the boss of the riveting head, and the other end abuts against the compressor. A long round hole is opened on the side surface of the compressor, and a round hole is opened on the side surface of the riveting head. A pin passes through the long round hole of the compressor and is fixed in the round hole of the riveting head to limit the compressor. The compressor can slide relative to the riveting head. The specific riveting method includes the following steps: 1 - 1 The product to be riveted enters the station between the riveting head mechanism and the lower riveting head, so that the riveting head mechanism is located above the product to be riveted with a complex cavity structure; 1 - 2 Lower the height of the riveting head mechanism so that the end of the base is lower than the upper edge of the cavity of the product and bypasses the cavity flange; 1 - 3 Adjust the posture of the product so that the riveting head is aligned with the rivet head; 1 - 4 Start the riveting machine, the riveting head mechanism descends and enters the cavity. The compressor contacts the skin surface to be riveted on the bottom surface of the cavity and applies a pre - pressing force to flatten the local skin around the rivet to be riveted; 1 - 5 When the compression amount of the spring reaches the limit, the riveting head mechanism and the lower riveting head jointly apply pressure to the rivet to complete the riveting work; 1 - 6 Move the product to the next riveting position to continue riveting until all the single - row rivets are riveted; 1 - 7 Pull out the locking pin, loosen the rotating shaft, rotate the rotating plate to adjust the riveting head mechanism to other stations in turn, then insert the locking pin to fix, and repeat steps 1 - 1 to 1 - 5 until all the rivets at all stations are riveted.

2. The riveting method for complex cavity structures of an aircraft according to claim 1, characterized in that The relationship between the protruding amount δ of the lower end of the compressor of the riveting head mechanism from the end face of the riveting head, the length h of the rivet, and the sandwich thickness σ is: δ=(h - σ)×0.

8.

3. A riveting method for complex cavity structures of aircraft according to claim 1, characterized in that The rotating plate of the riveting head mechanism is provided with 4 station switching holes, including a 0° station switching hole, a 90° station switching hole, a 180° station switching hole, and a 270° station switching hole. After the rotating plate rotates around the rotating shaft until any station switching hole coincides with the station locking hole, insert the locking pin into the hole to lock the orientation of the riveting head.

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