An automatic interference bolt installation device for aircraft assembly

Abstract

The present invention relates to an automatic installation device for interference bolts used in aircraft assembly, which includes a clamping and pressing component, a riveting gun component, and a feeding component. The clamping and pressing component is arranged on the riveting gun component, and the riveting gun component is arranged on the feeding component. The clamping and pressing component includes clamping jaws, an elastic member, a push rod, and a linear module. The two clamping jaws are symmetrically arranged. One end of the tails of the two clamping jaws is connected by the elastic member, and the other ends of the tails are respectively rotatably connected to the linear module. The push rod is arranged on the riveting gun component and is located between the tails of the two clamping jaws. The interference bolt is clamped by the clamping and pressing component, and then the feeding component makes the interference bolt reach the pre-installation hole position. The linear module retracts, and the tails of the two clamping jaws contact the push rod, so as to deflect to both sides, causing the clamping jaws to open to both sides against the binding force of the elastic member. Then, the riveting gun component applies a squeezing force to the interference bolt to make the interference bolt and the hole perform interference connection.

Description

Technical Field

[0001] The present invention relates to the technical field of interference connection, and particularly to an automatic installation device for interference bolts used in aircraft assembly. Background Art

[0002] Interference connection technology is an assembly technology that realizes interference fit by making the connecting piece and the fastening hole generate a certain amount of interference through interference fit. Interference connection can not only ensure the sealing between the connecting piece and the hole wall, but also improve the sealing performance of parts such as the fuel tank area, reduce the usage amount of sealant, and at the same time improve the fatigue life of the structure. The main parts applied on aircraft include main load-bearing components such as fuselage girders, joints, and wing panel butt girders. When assembling the aircraft body structure, interference connection technology is increasingly used.

[0003] According to different interference amounts, it is divided into interference connection with low interference amount and interference connection with high interference amount. Interference connection with low interference amount refers to the interference amount that does not cause the yield of the structural material of the hole wall, and the deformation around the structural hole is within the elastic range. Interference connection with high interference amount refers to that in aviation structures, the interference amount of interference fit mostly exceeds 1%. In this case, the stress in the structure exceeds the elastic limit of the material, causing plastic deformation within a certain range near the hole wall. Due to the swelling of the plastic zone where plastic deformation occurs and being hindered by the adjacent elastic zone, residual compressive stress will be generated at the hole edge, thereby improving the fatigue resistance of the structure and achieving the effect of improving the fatigue life. Interference fit connection is divided into interference riveting and interference bolt connection. The rivet in interference fit riveting has a clearance fit with the rivet hole before installation, and the interference amount between the rivet and the rivet hole is formed during the riveting process. The shank of the interference bolt is larger than the hole diameter before installation and is installed by mechanical or freezing methods. Therefore, the installation of interference bolts is more difficult.

[0004] Currently, the manual assembly method is adopted. After drilling the hole, the interference bolt is inserted into the hole, and the bolt is made to reach the predetermined position by knocking. On the other side of the working object, the nut is installed and tightened to complete the installation of the interference bolt. The manual assembly method has problems such as high labor intensity, difficult control of installation quality, and unsatisfactory connection effect. Summary of the Invention

[0005] (1) Technical Problems to be Solved

[0006] The technical problem to be solved by the present invention is to provide an automatic installation device for interference bolts used in aircraft assembly, so as to solve the technical problems such as high labor intensity, difficult control of installation quality, and unsatisfactory connection effect existing in the manual assembly method.

[0007] (2) Technical Solutions

[0008] An embodiment of the present invention provides an automatic installation device for interference bolts in aircraft assembly, which includes a clamping and tightening assembly, a riveting gun assembly, and a feeding assembly; the clamping and tightening assembly is arranged on the riveting gun assembly, and the clamping and tightening assembly is used for clamping interference bolts; the riveting gun assembly is used to apply an extrusion force to the interference bolts to perform interference connection between the interference bolts and the holes; the riveting gun assembly is arranged on the feeding assembly, and the feeding assembly is used for the position movement of the riveting gun assembly; the clamping and tightening assembly includes clamping jaws, elastic members, ejector rods, and a linear module. The two clamping jaws are symmetrically arranged. Each clamping jaw includes a head and a tail. The two tails are rotatably connected to the linear module at one end away from the head, and the other ends of the two tails are connected by the elastic members to keep the two clamping jaws clamped. The ejector rod is arranged on the riveting gun assembly and is located between the tails of the two clamping jaws. When the linear module retracts, the tails of the two clamping jaws contact the ejector rod, so as to deflect to both sides, causing the clamping jaws to overcome the binding force of the elastic members and open to both sides.

[0009] Further, the elastic member adopts an O-shaped spring. Grooves for accommodating the O-shaped spring are correspondingly arranged on the tails of the two clamping jaws. The O-shaped spring is sleeved on the grooves to tightly hoop the two clamping jaws.

[0010] Further, an opening is arranged in the radial direction between the heads of the two clamping jaws, and the interference bolt is squeezed into the space between the heads of the two clamping jaws through the opening.

[0011] Further, it further includes an L-shaped top block. The L-shaped top blocks are respectively arranged on the tails of the two clamping jaws. A chamfer is arranged on the surface of the L-shaped top block corresponding to the ejector rod. When the L-shaped top block contacts the ejector rod, under the guiding action of the ejector rod, the chamfer of the L-shaped top block makes the chamfered surface parallel to the side surface of the ejector rod, so as to guide the L-shaped top block to deflect and open the head of the clamping jaw.

[0012] Further, the linear module includes a pull rod, a U-shaped claw, a slide rail, a slider, and a cylinder. The cylinder block and the slide rail of the cylinder are both arranged on the riveting gun assembly. The slider is movably arranged on the slide rail, and one end of the slider is connected to the rod body of the cylinder. The other end of the slider is connected to the U-shaped claw. The two ends of the U-shaped claw are arranged downward and are respectively connected to the two pull rods. One ends of the two pull rods are respectively connected to the tails of the two clamping jaws through pins.

[0013] Furthermore, the riveting gun assembly includes a riveting gun base, a transmission rod, a riveting rod, a sleeve, a gland, and a return spring. The riveting rod is arranged between the two jaws. A rod cap is provided at one end of the riveting rod, and the rod cap abuts against one end of the transmission rod. The other end of the transmission rod is arranged in the riveting gun base and is driven by the riveting gun base to extend or retract. The sleeve is sleeved on the riveting rod, with one end connected to the riveting gun base and the other end sealed by the gland. The return spring is arranged between the gland and the rod cap for resetting the riveting rod.

[0014] Furthermore, it further includes an opposed switch which is respectively arranged on both sides of the sleeve and close to one end of the initial position of the rod cap for detecting the reset situation of the riveting rod.

[0015] Furthermore, a sliding ring is arranged between the U-shaped claw and the sleeve.

[0016] Furthermore, the feeding assembly includes a fixed seat, a sliding table, and a sliding table driving member. The sliding table is used to connect the riveting gun assembly. The sliding table is movably arranged on the fixed table through a track and is driven by the sliding table driving member arranged on the fixed seat.

[0017] Furthermore, it further includes a baffle, a laser distance sensor, and a magnetic switch. The baffle is arranged on one side of the sliding table. The laser distance sensor is arranged at one end of the fixed seat and is on the same straight line parallel to the moving direction of the sliding table as the baffle. The magnetic switch is arranged on the fixed seat at the initial position of the sliding table and corresponds to the position of the baffle.

[0018] (3) Beneficial effects

[0019] In summary, in the present invention, the interference bolt is clamped by the clamping and pressing assembly, and then the feeding assembly makes the interference bolt reach the pre-installation hole position. The linear module retracts, and the tails of the two jaws contact the ejector rod, so as to deflect to both sides, causing the jaws to open to both sides against the binding force of the elastic member. Then, the riveting gun assembly applies an extrusion force to the interference bolt to perform interference connection between the interference bolt and the hole. The device has a high degree of integration, realizes functions such as adaptive clamping, uniform pushing, and position detection during the installation process of the interference bolt, and has a high degree of automation. Description of the drawings

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments of the present invention will be briefly introduced below. Obviously, the following described drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0021] Figure 1 It is a three-dimensional structural schematic diagram of an automatic interference bolt installation device for aircraft assembly;

[0022] Figure 2 It is a front view structural schematic diagram of an automatic interference bolt installation device for aircraft assembly (the feeding component is omitted);

[0023] Figure 3 It is a top view structural schematic diagram of an automatic interference bolt installation device for aircraft assembly;

[0024] Figure 4 It is a structural schematic diagram of another state (when the jaws are open) of an automatic interference bolt installation device for aircraft assembly (the elastic part is omitted for easy observation of the L-shaped top block);

[0025] Figure 5 It is a schematic diagram of the A-A cross-section of an automatic interference bolt installation device for aircraft assembly;

[0026] Figure 6 It is a schematic diagram of the B-B cross-section of an automatic interference bolt installation device for aircraft assembly;

[0027] In the figure: 1. Clamping and pressing component; 2. Riveting gun component; 3. Feeding component; 10. Jaws; 11. Elastic part; 12. Thumb rod; 13. Linear module; 100. Opening; 14. L-shaped top block; 15. Pull rod; 16. U-shaped claw; 17. Slide rail; 18. Slide block; 19. Cylinder; 20. Riveting gun seat; 21. Transmission rod; 22. Riveting rod; 23. Sleeve; 24. Pressing cover; 25. Return spring; 26. Through-beam sensor; 27. Sliding ring; 30. Fixed seat; 31. Slide table; 33. Baffle; 34. Laser distance sensor; 35. Magnetic switch. Specific embodiments

[0028] The following further describes the embodiments of the present invention in detail with reference to the drawings and examples. The detailed description and drawings of the following examples are used to exemplarily illustrate the principle of the present invention, but cannot be used to limit the scope of the present invention, that is, the present invention is not limited to the described embodiments, and covers any modifications, replacements, and improvements of parts, components, and connection methods without departing from the spirit of the present invention.

[0029] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The following will describe this application in detail with reference to the drawings and embodiments.

[0030] Please refer to Figures 1 to 6, an embodiment of the present invention provides an automatic installation device for interference bolts in aircraft assembly, which includes a clamping and tightening assembly 1, a riveting gun assembly 2, and a feeding assembly 3. The clamping and tightening assembly 1 is arranged on the riveting gun assembly 2, and the clamping and tightening assembly 1 is used for clamping interference bolts; the riveting gun assembly 2 is used to apply an extrusion force to the interference bolts to make the interference bolts and holes perform interference connection; the riveting gun assembly 2 is arranged on the feeding assembly 3, and the feeding assembly 3 is used for the position movement of the riveting gun assembly 2.

[0031] Among them, the clamping and tightening assembly 1 includes clamping jaws 10, elastic members 11, ejector rods 12, and linear modules 13. The two clamping jaws 10 are symmetrically arranged. The clamping jaws 10 include a head and a tail. The two tails are respectively rotatably connected to the linear module 13 at one end away from the head, and the other ends of the two tails are connected by the elastic member 11, so that the clamping jaws 10 form a lever structure with a long rod at the head and a short rod at the tail with the rotation connection as the rotation axis, and the two clamping jaws 10 are kept clamped by the elastic member 11.

[0032] The ejector rod 12 is arranged on the riveting gun assembly 2 and is located between the tails of the two clamping jaws 10. One end of the ejector rod 12 is round-headed for smooth transition. When the linear module 13 retracts, it pulls the tails of the two clamping jaws 10 into contact with the ejector rod 12. The tails of the clamping jaws 10 will deflect and avoid in order to adapt to the ejector rod 12. According to the principle of the lever, the clamping jaws 10 overcome the binding force of the elastic member 11 and open to both sides.

[0033] In the actual operation process, the clamping and tightening assembly 1 clamps the interference bolts, that is, under the restraint of the elastic member 11, the two clamping jaws 10 clamp the interference bolts. Due to the use of the lever principle, when the linear module 13 is stationary, this clamping state has a certain self-locking ability. The interference bolts are brought to the pre-installation hole position through the feeding assembly 3. The linear module 13 retracts, and the tails of the two clamping jaws 10 come into contact with the ejector rod 12, so as to deflect to both sides, making the clamping jaws 10 overcome the binding force of the elastic member 11 and open to both sides. Then, the riveting gun assembly 2 applies an extrusion force to the interference bolts to make the interference bolts and holes perform interference connection. After the installation is completed, the linear module 13 resets, and the tails of the two clamping jaws 10 are separated from the contact with the ejector rod 12. Under the action of the elastic member 11, the clamping jaws 10 are closed again to restore the initial state, which is convenient for the next interference connection. The device has a high degree of integration, realizing functions such as adaptive clamping, uniform pushing, and position detection during the installation process of interference bolts, and has a high degree of automation.

[0034] In some embodiments, the elastic member 11 is an O-shaped spring. Grooves for accommodating the O-shaped spring are correspondingly provided on the tails of the two jaws 10. The O-shaped spring is sleeved on the grooves. The O-shaped spring is made by connecting the head and tail of a long strip spring and can expand outwards. By binding one end of the tail of the jaw 10 with the O-shaped spring, the two jaws 10 are tightened, so that the jaws 10 are closed.

[0035] In some embodiments, an opening 100 is provided in the radial direction between the heads of the two jaws 10. The interference bolt is squeezed into the space between the heads of the two jaws 10 through the opening 100. Specifically, the nut of the interference bolt is squeezed from one side of the opening 100 to the other side. Since the nut is approximately circular, the opening 100 will expand along with the outer shape of the nut, causing the jaws 10 to slightly open to both sides against the binding force of the elastic member 11 until the interference bolt is completely clamped by the jaws 10.

[0036] In some embodiments, an L-shaped top block 14 is further included. The L-shaped top blocks 14 are respectively arranged at the tails of the two jaws 10. A chamfer is provided on the surface of the L-shaped top block 14 corresponding to the ejector rod 12. When the L-shaped top block 14 contacts the ejector rod 12, under the guiding action of the ejector rod 12, the chamfer of the L-shaped top block 14 makes the chamfered surface parallel to the side surface of the ejector rod 12, thereby guiding the L-shaped top block 14 to deflect and opening the heads of the jaws 10. There are four groups of the L-shaped top blocks 14, two of which are corresponding to each other and are arranged up and down respectively. Correspondingly, there are also two groups of ejector rods 12, so that when the jaws 10 are opened, the upper and lower forces are more uniform.

[0037] In some embodiments, the linear module 13 includes a pull rod 15, a U-shaped claw 16, a slide rail 17, a slider 18 and a cylinder 19. The cylinder block of the cylinder 19 and the slide rail 17 are both arranged on the riveting gun assembly 2. The slider 18 is movably arranged on the slide rail 17, and one end of the slider 18 is connected to the rod body of the cylinder 19. The other end of the slider 18 is connected to the U-shaped claw 16. The two ends of the U-shaped claw 16 are arranged downward and are respectively connected to the two pull rods 15. One ends of the two pull rods 15 are respectively connected to the tails of the two jaws 10 through pins. When the cylinder 19 retracts, it drives the slide rail 17, the U-shaped claw 16 and the pull rod 15 to move to the right together, and the tails of the jaws 10 also follow and move to the right to abut against the ejector rod 12. The cylinder 19 can be replaced by other linear actuators, such as an oil cylinder, an electric telescopic rod, etc.

[0038] In some embodiments, the riveting gun assembly 2 includes a riveting gun base 20, a transmission rod 21, a riveting rod 22, a sleeve 23, a gland 24, and a return spring 25. The riveting rod 22 is disposed between the two jaws 10. One end of the riveting rod 22 is provided with a rod cap, which abuts against one end of the transmission rod. The other end of the transmission rod is disposed within the riveting gun base 20 and is driven by the riveting gun base 20 to extend or retract. The transmission rod 21 and the riveting gun base 20 are common devices in the prior art and will not be described in detail again. A linear actuator such as a hydraulic cylinder or a pneumatic cylinder can also be used as a substitute. The sleeve 23 is sleeved on the riveting rod 22, and one end is connected to the riveting gun base 20, and the other end is sealed by the gland 24. The return spring 25 is disposed between the gland 24 and the rod cap for resetting the riveting rod 22. During use, the rod cap of the riveting rod 22 is abutted by one end of the transmission rod 21 to feed together, thereby providing an extrusion force to the interference bolt, pressing the interference bolt into the hole to complete the interference connection. The force is evenly distributed during the extrusion process, and the stroke is fixed, so the connection quality is good. After the interference connection is completed, the transmission rod 21 retracts, and the riveting rod 22 is reset under the action of the return spring 25. The advantage of the above setting of the riveting gun assembly 2 is that it can adapt to interference bolts of different specifications, and the corresponding riveting rod 22 and the corresponding connection components can be replaced, greatly improving the applicability.

[0039] In some embodiments, it further includes an opposed photoelectric switch 26. The opposed photoelectric switches 26 are respectively disposed on both sides of the sleeve 23 and close to one end of the initial position of the rod cap. It is specifically stated that there are holes on the sleeve 23 for the opposed light to pass through. When the signals of the two opposed photoelectric switches 26 are blocked, it indicates that the riveting rod 22 or the transmission rod 21 blocks the light. When the signals of the opposed photoelectric switches 26 are conducted, it indicates that the riveting rod 22 has not returned to its position, so as to detect the reset situation of the riveting rod 22 and prevent the riveting rod 22 from being deformed and unable to reset after multiple rivetings as a fault detection.

[0040] In some embodiments, a sliding ring 27 is disposed between the U-shaped claw 16 and the sleeve 23. The sliding ring 27 can be connected to the U-shaped claw 16 to reduce the friction between the U-shaped claw 16 and the sleeve 23 and play a certain guiding role.

[0041] In some embodiments, the feeding assembly 3 includes a fixed seat 30, a sliding table 31, and a sliding table driving member. The sliding table 31 is used to connect the riveting gun assembly 2. The sliding table 31 is movably disposed on the fixed table through a track. The sliding table 31 is driven by a sliding table driving member disposed on the fixed seat 30. Through the expansion and contraction of the sliding table driving member, a feeding action is realized so that the jaws 10 clamping the interference bolt reach the specified hole position. The sliding table driving member includes but is not limited to a pneumatic cylinder, an oil cylinder, an electric telescopic rod, etc.

[0042] In some embodiments, it further includes a baffle 33, a laser distance sensor 34, and a magnetic switch 35. The baffle 33 is disposed on one side of the sliding table 31. The laser distance sensor 34 is disposed at one end of the fixed seat 30 and is on the same straight line parallel to the moving direction of the sliding table 31 as the baffle 33. The position of the sliding table 31 can be detected in real time by the laser distance sensor 34, so as to determine the feed amount by controlling the insertion depth of the interference bolt and judge whether the interference bolt is inserted in place. The magnetic switch 35 is disposed on the fixed seat 30 at the initial position of the sliding table 31 and corresponds to the position of the baffle 33. The magnetic switch 35 can detect whether the sliding table 31 is in the initial state.

[0043] It should be clear that each embodiment in this specification is described in a progressive manner. For the same or similar parts among the embodiments, reference can be made to each other. The key point of each embodiment is to illustrate the differences from other embodiments. For the method embodiments, reference can be made to the relevant parts of the device embodiments. The present invention is not limited to the specific steps and structures described above and shown in the figures. And, for the sake of brevity, the detailed description of known method technologies is omitted here.

[0044] The above are only the embodiments of the present application and do not limit the present application. For those skilled in the art, various changes and modifications can be made to the present application without departing from the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included within the scope of the claims of the present application.

Claims

1. An automatic installation device for interference bolts used in aircraft assembly, characterized in that: It includes a clamping and pressing component, a riveting gun component, and a feeding component; The clamping and pressing component is arranged on the riveting gun component, and the clamping and pressing component is used for clamping the interference bolt; The riveting gun component is used to apply a squeezing force to the interference bolt to make an interference connection between the interference bolt and the hole; The riveting gun component is arranged on the feeding component, and the feeding component is used for the position movement of the riveting gun component; The clamping and pressing component includes clamping jaws, an elastic member, a ejector rod, and a linear module. The two clamping jaws are symmetrically arranged. Each clamping jaw includes a head and a tail. The two tails are respectively rotatably connected to the linear module at one end away from the head. The other ends of the two tails are connected by the elastic member to keep the two clamping jaws clamped. The ejector rod is arranged on the riveting gun component and is located between the tails of the two clamping jaws. When the linear module retracts, the tails of the two clamping jaws contact the ejector rod, so as to deflect to both sides, making the clamping jaws overcome the binding force of the elastic member and open to both sides; It also includes an L-shaped top block. The L-shaped top blocks are respectively arranged on the tails of the two clamping jaws. The surface of the L-shaped top block corresponding to the ejector rod is provided with a chamfer. When the L-shaped top block contacts the ejector rod, under the guiding action of the ejector rod, the chamfer surface of the L-shaped top block is parallel to the side surface of the ejector rod, so as to guide the L-shaped top block to deflect and open the head of the clamping jaw.

2. The automatic interference bolt installation device for aircraft assembly according to claim 1, characterized in that: The elastic member adopts an O-shaped spring. Grooves for accommodating the O-shaped spring are correspondingly arranged on the tails of the two clamping jaws. The O-shaped spring is sleeved on the groove to tightly hoop the two clamping jaws.

3. An automatic interference bolt installation device for aircraft assembly according to claim 1, characterized in that: An opening is arranged in the radial direction between the heads of the two clamping jaws. The interference bolt is squeezed into the space between the heads of the two clamping jaws through the opening.

4. The automatic interference bolt installation device for aircraft assembly according to claim 1, characterized in that: The linear module includes a pull rod, a U-shaped pull claw, a slide rail, a slider, and a cylinder. The cylinder block and the slide rail of the cylinder are both arranged on the riveting gun component. The slider is movably arranged on the slide rail, and one end of the slider is connected to the rod body of the cylinder. The other end of the slider is connected to the U-shaped pull claw. The two ends of the U-shaped pull claw are arranged downward and are respectively connected to the two pull rods. One ends of the two pull rods are respectively connected to the tails of the two clamping jaws through pins.

5. The automatic interference bolt installation device for aircraft assembly according to claim 4, characterized in that: The riveting gun component includes a riveting gun seat, a transmission rod, a riveting rod, a sleeve, a gland, and a return spring. The riveting rod is arranged between the two clamping jaws. A rod cap is arranged at one end of the riveting rod. The rod cap abuts against one end of the transmission rod. The other end of the transmission rod is arranged in the riveting gun seat and is driven by the riveting gun seat to extend or retract. The sleeve is sleeved on the riveting rod, and one end is connected to the riveting gun seat, and the other end is sealed by the gland. The return spring is arranged between the gland and the rod cap for resetting the riveting rod.

6. The automatic interference bolt installation device for aircraft assembly according to claim 5, wherein: It also includes an opposed switch. The opposed switches are respectively arranged on both sides of the sleeve and close to one end of the initial position of the rod cap for detecting the reset situation of the riveting rod.

7. An automatic interference bolt installation device for aircraft assembly according to claim 5, characterized in that: A sliding ring is arranged between the U-shaped pull claw and the sleeve.

8. An automatic interference bolt installation device for aircraft assembly according to claim 1, characterized in that: The feeding assembly includes a fixed base, a sliding table, and a sliding table driving member. The sliding table is used to connect the riveting gun assembly. The sliding table is movably arranged on the fixed table through a track, and the sliding table is driven by a sliding table driving member arranged on the fixed base.

9. The automatic interference bolt installation device for aircraft assembly according to claim 8, characterized in that: It further includes a baffle, a laser distance sensor, and a magnetic switch. The baffle is arranged on one side of the sliding table. The laser distance sensor is arranged at one end of the fixed base and is on the same straight line parallel to the movement direction of the sliding table as the baffle. The magnetic switch is arranged on the fixed base at the initial position of the sliding table and corresponds to the position of the baffle.

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