Automatic high-precision positioning device and method for large-size aircraft stringer

Abstract

The invention discloses an automatic high-precision positioning device and method for a large-size aircraft stringer. The device comprises a base and a plurality of positioning assemblies, and the positioning assemblies are movably arranged on the upper end face of the base; the positioning assembly comprises a movable seat, a driving mechanism, a mounting rod, a distance adjusting mechanism and a plurality of positioning rods; a mounting cavity is formed in the movable seat, the driving mechanism is mounted in the mounting cavity, the positioning rod is arranged at the lower end of the driving mechanism, a through groove allowing the positioning rod to penetrate through is formed in the lower end of the mounting cavity, and the driving mechanism is used for driving the mounting rod to move up and down in the mounting cavity; the positioning rods are movably mounted on the mounting rod at intervals, and the interval adjusting mechanism is used for adjusting the interval between every two adjacent positioning rods. According to the device, the distance adjusting mechanism is arranged, so that the distance between every two adjacent positioning rods can be automatically adjusted, then the distance between stringers is automatically adjusted, and automation is greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft manufacturing devices, and in particular to an automatic high-precision positioning device and method for a long stringer of a large-size aircraft. Background Art

[0002] The largest structural unit in the aircraft fuselage structure is the wall panel (skin and long stringer), which is also the most severely stressed structural member. Most of the fuselage load is transmitted through the wall panel. The long stringer is the longitudinal member of the fuselage structure. In the truss fuselage, it is mainly used to withstand the axial force caused by the bending of the fuselage. In addition, the long stringer supports the skin, which increases the critical stress of the skin under compression and shear instability. The accuracy of the relative position of the long stringer greatly affects the overall structural performance of the fuselage wall panel.

[0003] The existing wall panels need to be positioned during the forming process. When positioning the long stringers, due to the differences in the shapes of different parts of the body, the spacing between the front and rear ends of multiple stringers will be different when positioning the long stringers. Therefore, when positioning, staff are often required to assist in operating the positioning equipment between the multiple stringers to adjust and determine the spacing between the stringers. The operation is inconvenient, the automation effect is poor, and manual operation is likely to cause a certain impact on the spacing accuracy. Summary of the invention

[0004] The problem to be solved by the present invention is to provide an automatic high-precision positioning device and method for a long stringer of a large-sized aircraft. By setting a spacing adjustment mechanism, the spacing between two adjacent positioning rods can be automatically adjusted, and then the spacing between the stringers can be automatically adjusted, thereby greatly improving automation.

[0005] The technical solution provided by the present invention to solve the above problems is: an automatic high-precision positioning device for a long stringer of a large-sized aircraft, comprising a base and a plurality of positioning components, wherein the plurality of positioning components are movably arranged on the upper end surface of the base; the positioning components comprise a movable seat, a driving mechanism, a mounting rod, a spacing adjustment mechanism and a plurality of positioning rods;

[0006] The movable seat is provided with an installation cavity, the driving mechanism is installed in the installation cavity, the positioning rod is arranged at the lower end of the driving mechanism, the lower end of the installation cavity is provided with a through slot for the positioning rod to pass through, and the driving mechanism is used to drive the installation rod to move up and down in the installation cavity;

[0007] The positioning rods are movably installed on the mounting rods at intervals, and the spacing adjustment mechanism is used to adjust the spacing between two adjacent positioning rods.

[0008] Preferably, a slide rail is disposed on the upper end surface of the base, and a slide platform cooperating with the slide rail is disposed on the lower end surface of the movable seat.

[0009] Preferably, the driving mechanism comprises an electric telescopic rod and a connecting block, wherein the connecting blocks are arranged at both ends of the mounting rod, one end of the electric telescopic rod is connected to the cavity top of the mounting cavity, and the other end is connected to the connecting block.

[0010] Preferably, a guide block is provided on a side of the connecting block away from the mounting rod, and a guide rail cooperating with the guide block is provided on a side wall of the mounting cavity.

[0011] Preferably, the positioning rod includes a movable block, a connecting rod, a movable rod, a spring 1 and a positioning head, the movable block is movably mounted on the mounting rod, one end of the connecting rod is connected to the movable block, an end of the connecting rod away from the movable block is provided with an axial movable groove, one end of the movable rod is movably connected to the movable groove, a limiting ring is provided on the movable rod, the spring 1 is mounted on the movable rod, one end of the spring 1 abuts against the limiting ring, and the other end abuts against the lower end of the connecting rod, and the positioning head is provided at an end of the movable rod away from the connecting rod.

[0012] Preferably, the connection angles between the connecting rods and the movable blocks in the plurality of positioning rods are different so that the positioning heads at the lower ends of the plurality of positioning rods are arranged in an arc shape.

[0013] Preferably, the spacing adjustment mechanism includes a second spring, a temperature field and a plurality of thermo-elastic rings. The second spring is sleeved on both sides of the mounting rod and one end thereof abuts against the connecting block and the other end thereof abuts against the movable block. The plurality of thermo-elastic rings are sleeved on the mounting rod and are spaced apart between two adjacent movable blocks. The temperature field is used to apply temperature to the thermo-elastic rings so as to cause axial deformation of the thermo-elastic rings.

[0014] Preferably, the thermostrictive ring is made of titanium alloy memory material.

[0015] Preferably, an axial electromagnet bar is provided on the mounting rod, and a magnetic block which can be attracted to the electromagnet bar is provided in the movable block; a receiving groove is provided on the movable block, and the magnetic block can be movably installed in the receiving groove, and a spring three is also provided in the receiving groove, one end of the spring three is fixedly connected to the groove top of the receiving groove, and the other end is fixedly connected to the upper end surface of the magnetic block, clamping blocks are provided on both sides of the magnetic block, and a plurality of limiting teeth one are provided on the lower end surface of the clamping block, and a limiting tooth two which can cooperate with the limiting tooth one is provided on the upper end surface of the mounting rod.

[0016] The present invention also discloses a positioning method using the automatic high-precision positioning device for a large-size aircraft long stringer as described above, the method comprising the following steps:

[0017] S1. Place the aircraft skin on the base and fix it;

[0018] S2, installing the long stringer on the aircraft skin at an approximate position according to the long stringer installation setting position of the aircraft skin, starting the temperature field, and adjusting the temperature of the temperature field so that the thermostrictive ring is adjusted to a required length to adjust the spacing of the positioning rods;

[0019] S3. After the adjustment is completed, the electromagnet bar is energized to generate suction force, and the magnetic block is attracted toward the electromagnet bar until the limiting tooth 1 on the lower end surface of the clamping block is engaged with the limiting tooth 2 on the mounting rod, and then the temperature field is closed;

[0020] S4. After the adjustment is completed, the electric telescopic rod is turned on to drive the positioning rod to move downward until the positioning head on the positioning rod positions and fixes the long stringer;

[0021] S5. After the long stringer and the skin are bonded, keep the positioning rod fixed to the long stringer until the long stringer and the skin are initially cured and bonded.

[0022] Compared with the prior art, the advantages of the present invention are: by providing a spacing adjustment mechanism, the present invention can automatically adjust the spacing between two adjacent positioning rods, and then automatically adjust the spacing between the beams, thereby greatly improving automation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings described herein are used to provide further understanding of the present invention and constitute a part of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0024] Figure 1 It is a three-dimensional structural schematic diagram of the present invention;

[0025] Figure 2 is a cross-sectional view of a positioning assembly of the present invention;

[0026] Figure 3 yes Figure 2 The enlarged schematic diagram of point A in the middle;

[0027] Figure 4 yes Figure 2 The enlarged schematic diagram of point B in the middle;

[0028] Figure 5 is a cross-sectional view of the mounting rod and the movable block of the present invention;

[0029] Figure 6 It is a three-dimensional structural schematic diagram of the mounting rod of the present invention.

[0030] The accompanying drawings are marked with: 1. movable seat, 2. slide table, 3. slide rail, 4. base, 5. electric telescopic rod, 6. guide rail, 7. guide block, 8. connecting block, 9. spring two, 10. installation cavity, 11. movable block, 12. thermosensitive elastic ring, 13. installation rod, 14. connecting rod, 15. spring three, 16. receiving groove, 17. magnetic block, 18. movable groove, 19. movable rod, 20. spring one, 21. limiting ring, 22. positioning head, 23. clamping block, 24. limiting tooth one, 25. limiting tooth two, 26. electromagnet bar. DETAILED DESCRIPTION

[0031] The following will describe the implementation methods of the present invention in detail with reference to the accompanying drawings and embodiments, so that the implementation process of how the present invention applies technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0032] In the description of the present invention, it should be noted that directional words, such as the terms "center", "lateral", "longitudinal", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating directions and positional relationships are based on the directions or positional relationships shown in the accompanying drawings, which are only for the convenience of narrating the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and cannot be understood as limiting the specific scope of protection of the present invention.

[0033] In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features. Therefore, the definition of "first" and "second" features can explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "several" is two or more, unless otherwise clearly and specifically defined.

[0034] In the present invention, unless otherwise specified and limited, the terms "assemble", "connect", and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can also be a mechanical connection; it can be directly connected, or it can be connected through an intermediate medium, or the two elements can be internally connected. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] It should be understood that when used in this specification and the appended claims, the terms "include" and "comprises" indicate the presence of described features, integers, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or combinations thereof.

[0036] It should also be understood that the terms used in this description of the embodiments of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the embodiments of the present invention. As used in the description of the embodiments of the present invention and the appended claims, unless the context clearly indicates otherwise, the singular forms of "a", "an" and "the" are intended to include plural forms. Example 1

[0037] like Figure 1-Figure 6 As shown, this embodiment discloses an automatic high-precision positioning device for a long stringer of a large-sized aircraft, comprising a base 4 and a plurality of positioning components, wherein the plurality of positioning components are movably arranged on the upper end surface of the base 4; the characteristic is that the positioning component comprises a movable seat 1, a driving mechanism, a mounting rod 13, a spacing adjustment mechanism and a plurality of positioning rods;

[0038] The movable seat 1 is provided with a mounting cavity 10, the driving mechanism is installed in the mounting cavity 10, the positioning rod is arranged at the lower end of the driving mechanism, the lower end of the mounting cavity 10 is provided with a through slot for the positioning rod to pass through, and the driving mechanism is used to drive the mounting rod 13 to move up and down in the mounting cavity 10;

[0039] The positioning rods are movably installed on the mounting rod 13 at intervals, and the spacing adjustment mechanism is used to adjust the spacing between two adjacent positioning rods.

[0040] Specifically, the connection method between the base and the movable seat is: a slide rail 3 is arranged on the upper end surface of the base 4, and a slide table 2 cooperating with the slide rail 3 is arranged on the lower end surface of the movable seat 1. The movement of the movable seat can be realized through the cooperation of the slide rail and the slide table. A locking mechanism is also arranged on the base, and the movable seat is locked by the locking mechanism after the movable seat moves to a specified position. The specific structure of the locking mechanism belongs to the prior art, and technical personnel in this field can design and select it according to the prior art, so it will not be repeated here.

[0041] In this embodiment, the driving mechanism includes an electric telescopic rod 5 and a connecting block 8, wherein the connecting block 8 is arranged at both ends of the mounting rod 13, one end of the electric telescopic rod 5 is connected to the cavity top of the mounting cavity 10, and the other end is connected to the connecting block 8, and the electric telescopic rod is controlled by a controller to drive the mounting rod to move up and down. In order to improve the stability of the mounting rod during movement, a guide block 7 is arranged on the side of the connecting block 8 away from the mounting rod 13, and a guide rail 6 cooperating with the guide block 7 is arranged on the side wall of the mounting cavity 10.

[0042] The positioning rod comprises a movable block 11, a connecting rod 14, a movable rod 19, a spring 20 and a positioning head 22. The movable block 11 is movably mounted on the mounting rod 13. One end of the connecting rod 14 is connected to the movable block 11. An axial movable groove 18 is provided at one end of the connecting rod 14 away from the movable block 11. One end of the movable rod 19 is movably connected to the movable groove 18. A limiting ring 21 is provided on the movable rod 19. The spring 20 is mounted on the movable rod 19. One end of the spring 20 abuts against the limiting ring 21, and the other end abuts against the lower end of the connecting rod 14. The positioning head 22 is provided at one end of the movable rod 19 away from the connecting rod 14. Furthermore, the connection angles of the connecting rods 14 and the movable blocks 11 in the multiple positioning rods are different, so that the positioning heads 22 at the lower ends of the multiple positioning rods are arranged in an arc shape.

[0043] In the above scheme, after the long beam is placed, the electric telescopic rod 5 is started to drive the installation rod 13 and the positioning rod to move downward. After the positioning head 22 at the lower end of the positioning rod contacts the long beam, the positioning rod continues to move downward, and the movable rod 19 compresses the spring 20 under the reaction of the long beam; this scheme provides a spring 20, so that multiple positioning rods arranged in an arc shape can fix the long beam after moving downward the same distance.

[0044] In this embodiment, specifically, the spacing adjustment mechanism includes a spring 9, a temperature field and a plurality of thermo-elastic rings 12. The spring 9 is mounted on both sides of the mounting rod 13 and one end is in contact with the connecting block 8 and the other end is in contact with the movable block 11. The plurality of thermo-elastic rings 12 are mounted on the mounting rod 13 and are spaced between two adjacent movable blocks 11. The temperature field is used to apply temperature to the thermo-elastic ring 12 so that the thermo-elastic ring 12 undergoes axial deformation. Further, the thermo-elastic ring 12 is made of titanium alloy memory material. Assuming that the longitudinal length of the thermo-elastic ring 12 before deformation is A1, the temperature field condition to be applied is determined according to the required spacing of the movable blocks 11, and the longitudinal linear deformation coefficient B of the thermo-elastic ring 12 is obtained. Then, the longitudinal length of the thermo-elastic ring 12 after deformation is A2, wherein A2=A1×B.

[0045] In the above scheme, after the spacing between the movable blocks 11 is adjusted, in order to prevent the movable block 11 from being displaced again on the mounting rod 13 to affect the positioning, the temperature field needs to be maintained all the time. It is known to those skilled in the art that continuously maintaining the temperature field requires more energy. Therefore, in the present scheme, an axial electromagnet bar 26 is provided on the mounting rod 13, and a magnetic block 17 that can be attracted to the electromagnet bar 26 is provided in the movable block 11; a receiving groove 16 is provided on the movable block 11, and the magnetic block 17 can be movably installed in the receiving groove 16, and a spring three 15 is also provided in the receiving groove 16, one end of the spring three 15 is fixedly connected to the groove top of the receiving groove 16, and the other end is fixedly connected to the upper end face of the magnetic block 17, and clamping blocks 23 are provided on both sides of the magnetic block 17, and the lower end face of the clamping block 23 is provided with a plurality of limiting teeth one 24, and the upper end face of the mounting rod 13 is provided with limiting teeth two 25 that can cooperate with limiting teeth one 24.

[0046] In the above scheme, after the spacing adjustment of the movable block 11 is completed, the electromagnet bar 26 is controlled to be energized. After being energized, the electromagnet bar 26 generates a magnetic force to attract the magnetic block 17. At the same time, the magnetic block 17 stretches the spring three 15 under the action of the suction force of the electromagnet bar 26, and the limiting tooth one 24 on the clamping block 23 on both sides of the magnetic block 17 is engaged with the limiting tooth two 25. On the one hand, this scheme uses the suction force of the electromagnet bar 26 to pre-magnetize the magnetic block 17 to complete the movement limit of the movable block 11. On the other hand, the invention uses the engagement of the limiting tooth one 24 with the limiting tooth two 25 to enhance the limiting effect of the movable block 11. Example 2

[0047] This embodiment discloses a positioning method using an automatic high-precision positioning device for a large-size aircraft stringer as described in Embodiment 1. Specifically, the method comprises the following steps:

[0048] S1, placing the aircraft skin on the base 4 for fixing;

[0049] S2, installing the long stringer on the aircraft skin according to the approximate position according to the long stringer installation setting position, starting the temperature field, adjusting the temperature of the temperature field so that the thermostrictive ring 12 is adjusted to the required length, thereby adjusting the spacing of the positioning rods;

[0050] S3. After the adjustment is completed, the electromagnet bar 26 is energized to generate suction force, and the magnetic block 17 is attracted toward the electromagnet bar 26 until the limiting tooth 1 24 on the lower end surface of the clamping block 23 is engaged with the limiting tooth 2 25 on the mounting rod 13, and then the temperature field is closed;

[0051] S4, after the adjustment is completed, the electric telescopic rod 5 is turned on to drive the positioning rod to move downward until the positioning head 22 on the positioning rod positions and fixes the long stringer;

[0052] S5. After the long stringer and the skin are bonded, keep the positioning rod fixed to the long stringer until the long stringer and the skin are initially cured and bonded.

[0053] The above description is only for the best embodiment of the present invention, but it should not be understood as limiting the claims. The present invention is not limited to the above embodiments, and its specific structure is allowed to be changed. All changes made within the scope of protection of the independent claims of the present invention are within the scope of protection of the present invention.

Claims

1. An automatic high-precision positioning device for a long stringer of a large-sized aircraft, comprising a base (4) and a plurality of positioning components, wherein the plurality of positioning components are movably arranged on an upper end surface of the base (4); characterized in that: The positioning assembly comprises a movable seat (1), a driving mechanism, a mounting rod (13), a spacing adjustment mechanism and a plurality of positioning rods; The movable seat (1) is provided with a mounting cavity (10), the driving mechanism is installed in the mounting cavity (10), the positioning rod is provided at the lower end of the driving mechanism, the lower end of the mounting cavity (10) is provided with a through slot for the positioning rod to pass through, and the driving mechanism is used to drive the mounting rod (13) to move up and down in the mounting cavity (10); The positioning rods are movably installed on the mounting rod (13) at intervals, and the spacing adjustment mechanism is used to adjust the spacing between two adjacent positioning rods.

2. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 1, characterized in that: The upper end surface of the base (4) is provided with a slide rail (3), and the lower end surface of the movable seat (1) is provided with a slide platform (2) that cooperates with the slide rail (3).

3. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 1, characterized in that: The driving mechanism comprises an electric telescopic rod (5) and a connecting block (8), wherein the connecting blocks (8) are arranged at both ends of the mounting rod (13), one end of the electric telescopic rod (5) is connected to the cavity top of the mounting cavity (10), and the other end is connected to the connecting block (8).

4. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 3, characterized in that: A guide block (7) is provided on a side of the connection block (8) away from the mounting rod (13), and a guide rail (6) cooperating with the guide block (7) is provided on a side wall of the mounting cavity (10).

5. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 4, characterized in that: The positioning rod comprises a movable block (11), a connecting rod (14), a movable rod (19), a spring (20) and a positioning head (22); the movable block (11) is movably mounted on the mounting rod (13); one end of the connecting rod (14) is connected to the movable block (11); an end of the connecting rod (14) away from the movable block (11) is provided with an axial movable groove (18); one end of the movable rod (19) is movably connected to the movable groove (18); a limiting ring (21) is provided on the movable rod (19); the spring (20) is mounted on the movable rod (19); one end of the spring (20) abuts against the limiting ring (21) and the other end abuts against the lower end of the connecting rod (14); and the positioning head (22) is provided at an end of the movable rod (19) away from the connecting rod (14).

6. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 5, characterized in that: The connection angles between the connecting rods (14) in the plurality of positioning rods and the movable block (11) are different, so that the positioning heads (22) at the lower ends of the plurality of positioning rods are arranged in an arc shape.

7. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 5 or 6, characterized in that: The spacing adjustment mechanism comprises a second spring (9), a temperature field and a plurality of thermo-elastic rings (12); the second spring (9) is sleeved on both sides of a mounting rod (13) and has one end abutting against a connecting block (8) and the other end abutting against a movable block (11); a plurality of thermo-elastic rings (12) are sleeved on the mounting rod (13) and are spaced apart and distributed between two adjacent movable blocks (11); the temperature field is used to apply temperature to the thermo-elastic rings (12) so as to cause the thermo-elastic rings (12) to undergo axial deformation.

8. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 7, characterized in that: The thermostrictive ring (12) is made of a titanium alloy memory material.

9. The automatic high-precision positioning device for a large-size aircraft stringer according to claim 8, characterized in that: The mounting rod (13) is provided with an axial electromagnet bar (26), and the movable block (11) is provided with a magnetic block (17) that can be attracted to the electromagnet bar (26); the movable block (11) is provided with a receiving groove (16), and the magnetic block (17) can be movably installed in the receiving groove (16), and a spring three (15) is also provided in the receiving groove (16), one end of the spring three (15) is fixedly connected to the groove top of the receiving groove (16), and the other end is fixedly connected to the upper end surface of the magnetic block (17), and the magnetic block (17) is provided with a clamping block (23) on both sides, and the lower end surface of the clamping block (23) is provided with a plurality of limiting teeth one (24), and the upper end surface of the mounting rod (13) is provided with a limiting tooth two (25) that can cooperate with the limiting tooth one (24).

10. A positioning method using the automatic high-precision positioning device for a large-size aircraft stringer as claimed in claim 9, characterized in that: The method comprises the following steps, S1, placing the aircraft skin on the base (4) for fixing; S2, installing the long stringer on the aircraft skin at an approximate position according to the long stringer installation setting position of the aircraft skin, starting the temperature field, and adjusting the temperature of the temperature field so that the thermostrictive ring (12) is adjusted to a required length, thereby adjusting the spacing of the positioning rods; S3. After the adjustment is completed, the electromagnet bar (26) is energized to generate suction force, and the magnetic attraction block (17) is attracted toward the electromagnet bar (26) until the limiting tooth 1 (24) on the lower end surface of the clamping block (23) is engaged with the limiting tooth 2 (25) on the mounting rod (13), and then the temperature field is closed; S4, after the adjustment is completed, the electric telescopic rod (5) is turned on to drive the positioning rod to move downward until the positioning head (22) on the positioning rod positions and fixes the long stringer; S5. After the long stringer and the skin are bonded, keep the positioning rod fixed to the long stringer until the long stringer and the skin are initially cured and bonded.

Images