Positioning tool and aircraft nose landing gear girder replacement method

Abstract

The invention discloses a positioning tool and an aircraft nose landing gear girder replacement method, the positioning tool is used for connecting an aircraft, the aircraft is provided with a first girder and a second girder, the first girder and the second girder are arranged at intervals, the positioning tool comprises a supporting body and two connecting assemblies, and the supporting body is arranged between the first girder and the second girder; the connecting assembly comprises first connecting pieces and second connecting pieces, the two first connecting pieces are detachably connected with the first girder or the second girder respectively, and the second connecting pieces are connected to the supporting body and can be detachably connected with the first connecting pieces. The method can effectively solve the problem that the in-situ reloading of the nose landing gear girder is easy to deviate when an airplane is repaired due to the fact that the process of repairing and reloading the nose landing gear girder is opposite to the process of manufacturing the nose landing gear girder.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft maintenance, and particularly relates to a positioning tooling and a method for replacing the front landing gear beam of an aircraft. Background Art

[0002] The front landing gear bay of an aircraft is a structure for installing and storing the front landing gear, responsible for bearing and transmitting the landing gear load, and at the same time providing support for the landing gear installation and retraction mechanism. The retraction mechanism of the front landing gear door is also installed in the front landing gear bay.

[0003] Generally, the front landing gear is rotatably connected to the beam. For example, in the Chinese invention patent with the publication number: CN117429600A, titled: A Locking Mechanism and an Aircraft Landing Gear of an Aircraft, the locking mechanism of the aircraft landing gear includes a push-pull link, a locking device, a driving component, an upper strut, and a lower strut. The aircraft landing gear includes the locking mechanism, a wheel, a main body structure, and an actuator. The upper strut is movably connected to the lower strut, and the actuator drives the push-pull link and the driving component to enable the upper strut and the lower strut to be folded and unfolded, thereby completing the retraction and extension of the aircraft landing gear. In this structure, through the linkage locking of the push-pull link, the locking device, the driving component, the upper strut, the lower strut, and the actuator, the retraction and extension of the aircraft landing gear can be completed, without the need for a separate hydraulic device, reducing the weight of the aircraft system and the use and maintenance costs of the entire system, and having low manufacturing costs.

[0004] During the repair of aircraft damage, the replacement of the main load-bearing structural members can effectively ensure the safety of the aircraft during flight. Since the aircraft is manufactured by first positioning and installing the beam and then installing the surrounding profiles, while during damage repair and replacement, the relative positions of all profiles and frames are first determined, and then the position of the front landing gear beam is positioned, resulting in a deviation in the in-situ replacement of the front landing gear beam during aircraft damage repair. Summary of the Invention

[0005] The purpose of the present invention is to overcome the above technical deficiencies, and propose a positioning tooling and a method for replacing the front landing gear beam of an aircraft, so as to solve the technical problem that in the prior art, due to the reverse process of the landing gear beam during damage repair and replacement compared to the manufacturing process, it is easy to cause a deviation in the in-situ replacement of the front landing gear beam during aircraft damage repair.

[0006] To achieve the above technical purpose, the present invention adopts the following technical solutions: In the first aspect, the present invention provides a positioning tooling for connecting an aircraft, the aircraft having a first beam and a second beam, the first beam and the second beam being spaced apart from each other, including: A support body disposed between the first beam and the second beam; and Two connecting components, the connecting components include a first connecting member and a second connecting member, the two first connecting members are respectively detachably connected to the first girder or the second girder, and the second connecting body is connected to the support body and can be detachably connected to the first connecting body.

[0007] In some embodiments, rotating shaft holes are respectively formed on opposite sides of the first girder and the second girder. The first connecting member includes a first connecting body, and one end of the first connecting body is slidably inserted into the rotating shaft hole and is clamped with the first girder or the second girder.

[0008] In some embodiments, the first connecting body is cylindrical, an external thread is formed at one end of the first connecting body, the first connecting member further includes a threaded connecting sleeve, one end of the first connecting body passes through the rotating shaft hole, and the threaded connecting sleeve is threadedly connected to one end of the first connecting body and abuts against the first girder or the second girder.

[0009] In some embodiments, the first connecting body has a small-diameter section and a large-diameter section. The small-diameter section is arranged farther from the support body than the large-diameter section. An external thread is formed on the circumferential outer wall of the small-diameter section. The threaded connecting sleeve is threadedly connected to the small-diameter section of the first connecting body, and the end of the large-diameter section abuts against the first girder or the second girder.

[0010] In some embodiments, the first connecting member further includes a retaining ring. The retaining ring is sleeved on the small-diameter section of the first connecting body and is tightly abutted against the threaded connecting sleeve and the first girder or the second girder.

[0011] In some embodiments, a first through hole is axially formed in the first connecting body. The support body is rod-shaped, and both ends of the support body are respectively slidably inserted into the first through hole. The second connecting member is connected to the support body and can be clamped with the first connecting body.

[0012] In some embodiments, a second through hole is further radially formed in the first connecting body. The second through hole is communicated with the first through hole. A locking hole is formed in the support body opposite to the second through hole. The second connecting member includes a second connecting body. One end of the second connecting body is sequentially inserted into the second through hole and the locking hole to limit the relative sliding of the support body with respect to the first connecting body.

[0013] In some embodiments, a tip is formed at one end of the second connecting body, and the cross-sectional area of the tip gradually increases in a direction away from the first connecting body.

[0014] In some embodiments, the second connecting member further includes a limiting block, which is connected to the other end of the second connecting body and abuts against the first connecting body.

[0015] In a second aspect, the present invention also provides a method for replacing the front landing gear beam of an aircraft. Using the positioning tooling as described above, the specific steps are as follows: Decompose the parts inside the cabin Decompose the cross-frame inside the front landing gear cabin, disconnect the connection between the second beam and the surrounding structure, and cut and remove the first rib and the second rib; Positioning of the first beam tooling Taking the second beam as the first reference, install the positioning tooling by borrowing the rotating shaft holes on the first beam and the second beam, and record the distance between the first beam and the first reference; Decomposition of the first beam Decompose the bulkhead inside the front landing gear cabin, decompose all the connecting members between the first beam and the surrounding frames, beams, skins and other structures, and disconnect the connection between the first beam and the surrounding structure; Positioning of the first beam Referring to the positions of the first rib and the second rib, reinstall the first beam, and ensure proper installation with reference to the distance between the first beam and the first reference; Installation of the first beam After completing the positioning of the first beam, add a first angle box at the connection between the first beam and the first rib, and add a second angle box at the connection between the first beam and the second rib; Working positioning of the second beam Taking the first beam as the second reference, install the positioning tooling by borrowing the positions of the rotating shaft holes on the first beam and the second beam, and record the distance between the second beam and the second reference; Decomposition of the second beam Decompose the bulkhead inside the front landing gear cabin, decompose all the connecting members between the second beam and the surrounding frames, beams, skins and other structures, and disconnect the connection between the second beam and the surrounding structure; Positioning of the second beam Referring to the positions of the first rib and the second rib, reinstall the second beam, and ensure proper installation with reference to the distance between the second beam and the second reference; Installation of the second beam After completing the positioning of the second beam, add a first angle box at the connection between the second beam and the first rib, and add a second angle box at the connection between the second beam and the second rib; Installation of the parts inside the cabin Reinstall the cross-frame inside the front landing gear cabin according to the drawing requirements.

[0016] Compared with the prior art, the beneficial effects of the positioning tooling and the method for replacing the front landing gear beam of the aircraft provided by the present invention include: a support body is arranged between the first beam and the second beam of the landing gear, and two first connecting pieces are respectively arranged at both ends of the support body, and the two first connecting pieces are respectively detachably connected to the first beam and the second beam, and the second connecting piece is configured to detachably connect the first connecting piece and the support body. Compared with the prior art, by arranging the support body between the first beam and the second beam of the landing gear to position and support the first beam and the second beam, it can effectively ensure the in-situ replacement of the first beam and the second beam of the landing gear, reduce the installation error of the replacement, and at the same time, through the first connecting piece and the second connecting piece, the detachable connection between the support body and the first beam and the second beam of the landing gear can be realized, with simple operation and convenient construction, and it can solve the technical problem in the prior art that because the process of repairing and replacing the damaged landing gear beam is opposite to that of manufacturing, it is easy to cause deviation in the in-situ replacement of the front landing gear beam during the repair of the aircraft damage. Description of the Drawings

[0017] Figure 1 FIG. 6 is a three-dimensional view of a positioning tooling provided by an embodiment of the present invention connected to a first beam and a second beam; Figure 2 FIG. 9 is a three-dimensional view of a positioning tooling provided by an embodiment of the present invention connected to a first beam and a second beam from another perspective; Figure 3 FIG. 12 is a three-dimensional view of a first beam provided by an embodiment of the present invention; Figure 4 FIG. 15 is a three-dimensional view of a second beam provided by an embodiment of the present invention; Figure 5 FIG. 18 is a three-dimensional view of a support body provided by an embodiment of the present invention; Figure 6 FIG. 21 is a three-dimensional view of a first connecting body provided by an embodiment of the present invention; Figure 7 FIG. 24 is a three-dimensional view of a threaded connection sleeve provided by an embodiment of the present invention; Figure 8 FIG. 27 is a three-dimensional view of a second connecting piece provided by an embodiment of the present invention.

[0018] Description of the Reference Numerals: First beam 100; second beam 200; support body 300; connection assembly 400; first connecting piece 410; first connecting body 411; threaded connection sleeve 412; retaining ring 413; second connecting piece 420; second connecting body 421; limiting block 422; frame 500; first rib 600; second rib 700; first angle box 800; second angle box 900. Detailed Embodiments

[0019] In order to make the objectives, technical solutions, and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0020] To solve the technical problem that the procedures for repairing and replacing the damaged landing gear beam are opposite to those during manufacturing, which easily leads to deviations in the in-situ replacement of the front landing gear beam during aircraft damage repair, the present invention provides a positioning tooling and a method for replacing the front landing gear beam of an aircraft. By arranging the support body 300 between the first beam 100 and the second beam 200 of the landing gear, positioning and supporting the first beam 100 and the second beam 200, it can effectively ensure the in-situ replacement of the first beam 100 and the second beam 200 of the landing gear, reduce the installation error during replacement. At the same time, through the first connecting member 410 and the second connecting member 420, a detachable connection can be achieved between the support body 300 and the first beam 100 and the second beam 200 of the landing gear, with simple operation and convenient construction.

[0021] Please refer to Figures 1 to 8 , Figure 1 , Figure 2 FIG. is a schematic structural diagram of the positioning tooling and the method for replacing the front landing gear beam of an aircraft according to an embodiment of the present invention. The positioning tooling is used to connect the aircraft, and the aircraft has a first beam 100 and a second beam 200, which are arranged at intervals from each other. It includes: a support body 300 and two connecting assemblies 400. The support body 300 is arranged between the first beam 100 and the second beam 200. The connecting assembly 400 includes a first connecting member 410 and a second connecting member 420. The two first connecting members 410 are respectively detachably connected to the first beam 100 or the second beam 200, and the second connecting body 421 is connected to the support body 300 and can be detachably connected to the first connecting body 411.

[0022] In this device, a support body 300 is arranged between the first beam 100 and the second beam 200 of the landing gear. Two first connecting members 410 are respectively arranged at both ends of the support body 300. The two first connecting members 410 can be respectively detachably connected to the first beam 100 and the second beam 200. The second connecting member 420 is configured to detachably connect the first connecting member 410 and the support body 300.

[0023] Furthermore, by disposing the support body 300 between the first girder 100 and the second girder 200 of the landing gear to position and support the first girder 100 and the second girder 200, it can effectively ensure the in-situ replacement of the first girder 100 and the second girder 200 of the landing gear, reduce the installation error during replacement. At the same time, through the first connecting member 410 and the second connecting member 420, a detachable connection between the support body 300 and the first girder 100 and the second girder 200 of the landing gear can be realized. The operation is simple and convenient for construction, and it can solve the technical problem in the prior art that because the procedures for repairing and replacing damaged landing gear girders are opposite to those during manufacturing, it is easy to cause deviations in the in-situ replacement of the front landing gear girder during aircraft damage repair.

[0024] In this embodiment, as Figures 1 to 4 shown, rotating shaft holes are respectively formed on the opposite sides of the first girder 100 and the second girder 200. The first connecting member 410 includes a first connecting body 411. One end of the first connecting body 411 can be slidably inserted into the rotating shaft hole and is clamped with the first girder 100 or the second girder 200.

[0025] The first connecting body 411 respectively realizes the detachable connection between the first connecting body 411 and the first girder 100 and the second girder 200 by being inserted into the rotating shaft holes of the first girder 100 and the second girder 200 and being clamped with the rotating shaft holes.

[0026] Furthermore, rotating shaft holes are respectively formed on the opposite sides of the first girder 100 and the second girder 200 here, which are respectively used to realize the rotational connection between the landing gear and the first girder 100 and the second girder 200. This is a conventional setting well-known to those skilled in the art and will not be elaborated here too much.

[0027] As one implementation manner, the first connecting body 411 is cylindrical. An external thread is formed at one end of the first connecting body 411. The first connecting member 410 further includes a threaded connection sleeve 412. One end of the first connecting body 411 passes through the rotating shaft hole, and the threaded connection sleeve 412 is threadedly connected to one end of the first connecting body 411 and abuts against the first girder 100 or the second girder 200.

[0028] The threaded connection sleeve 412 is threadedly connected to the first connecting body 411 and forms an integral body with the first connecting body 411. By abutting the threaded connection sleeve 412 against the first girder 100 or the second girder 200, the sliding of the support body 300 relative to the first girder 100 or the second girder 200 can be restricted.

[0029] Furthermore, by providing a threaded connection sleeve 412 at one end of the support body 300, the relative sliding of the support body 300 along a single direction with respect to the first main beam 100 or the second main beam 200 can be restricted respectively. If two threaded connection sleeves 412 are provided at both ends of the support body 300 respectively, the support body 300 can be positioned between the first main beam 100 and the second main beam 200. This is a conventional setting well-known to those skilled in the art and will not be elaborated further here.

[0030] As an implementation manner, for example Figure 6 shown, the first connection body 411 has a small-diameter section and a large-diameter section. The small-diameter section is arranged farther from the support body 300 relative to the large-diameter section. An external thread is provided on the outer circumferential wall of the small-diameter section. The threaded connection sleeve 412 is threadedly connected to the small-diameter section of the first connection body 411, and the end of the large-diameter section abuts against the first main beam 100 or the second main beam 200.

[0031] The first connection body 411 has a small-diameter section and a large-diameter section. The threaded connection sleeve 412 and the large-diameter section of the first connection body 411 are respectively arranged on both sides of the first main beam 100 or the second main beam 200, and can respectively abut against the first main beam 100 or the second main beam 200, so that the support body 300 can be connected to the first main beam 100 or the second main beam 200 and form a fixation.

[0032] As an implementation manner, for example Figure 2 shown, the first connector 410 further includes a retaining ring 413. The retaining ring 413 is sleeved on the small-diameter section of the first connection body 411 and is tightly abutted against the threaded connection sleeve 412 and the first main beam 100 or the second main beam 200.

[0033] By providing a retaining ring 413 between the threaded connection sleeve 412 and the first main beam 100 or the second main beam 200, the connection stability can be increased and the support stability of the positioning tooling can be improved.

[0034] Furthermore, here the retaining ring 413 is a common and easily purchasable washer or gasket in the market, which is a conventional setting well-known to those skilled in the art and will not be elaborated further here.

[0035] In this embodiment, for example Figure 6 shown, the first connection body 411 is axially provided with a first through hole. The support body 300 is rod-shaped, and both ends of the support body 300 are respectively slidably inserted into the first through hole. The second connector 420 is connected to the support body 300 and can be clamped with the first connection body 411.

[0036] The support body 300 can slide relative to the first connection body 411, and by using the clamping between the first connection body 411 and the second connector 420, a fixed connection between the support body 300 and the first connection body 411 can be achieved.

[0037] As an implementation manner, for example, Figure 6 , Figure 7 As shown, the first connecting body 411 is further provided with a second through hole along its radial direction, and the second through hole communicates with the first through hole. The support body 300 is provided with a locking hole opposite to the second through hole. The second connecting member 420 includes a second connecting body 421. One end of the second connecting body 421 is sequentially inserted into the second through hole and the locking hole to limit the relative sliding of the support body 300 with respect to the first connecting body 411.

[0038] By using the second connecting body 421 arranged along the radial direction of the first through hole, the detachable connection between the support body 300 and the first connecting body 411 is realized.

[0039] Furthermore, the support body 300 and the first connecting body 411 are respectively provided with a locking hole and a second through hole along the radial direction of the first through hole. By using the cooperation between the second connecting body 421 and the locking hole and the second through hole, the support body 300 and the first connecting body 411 cannot slide relative to each other along the axial direction of the first through hole.

[0040] As an implementation manner, for example, Figure 8 As shown, one end of the second connecting body 421 is formed with a tip, and the cross-sectional area of the tip gradually increases in the direction away from the first connecting body 411.

[0041] The second connecting body 421 is formed with a tip, which can facilitate the user to insert the second connecting body 421 into the locking hole and the second through hole in sequence, facilitating construction and operation.

[0042] As an implementation manner, for example, Figure 8 As shown, the second connecting member 420 further includes a limiting block 422. The limiting block 422 is connected to the other end of the second connecting body 421 and abuts against the first connecting body 411.

[0043] The limiting block 422 can abut against the outer wall of the first connecting body 411, which is used to facilitate the user to judge whether the second connecting body 421 is accurately inserted into the locking hole and the second through hole, thereby improving the connection stability of the device.

[0044] The present invention also provides a method for replacing the front landing gear beam of an aircraft. By using the positioning tooling as above, as Figure 1 , Figure 2 shown, the specific steps are as follows: Decompose the parts in the cabin, Decompose the transverse frame 500 in the front landing gear cabin. The transverse frame in the front landing gear cabin includes five pieces of No. 1 transverse frame, No. 2 transverse frame, No. 3 transverse frame, No. 4 transverse frame, and No. 5 transverse frame which are arranged at intervals from top to bottom. Decompose the connection between the second beam 200 and the surrounding structure, and cut off and remove the first rib 600 and the second rib 700; Tooling positioning for the first main beam 100 Taking the second main beam 200 as the first reference, install the positioning tooling by borrowing the rotating shaft holes on the first main beam 100 and the second main beam 200, and record the distance between the first main beam 100 and the first reference. Among them, use a laser distance measuring device to record the distance between the first main beam 100 and the positioning reference Disassembly of the first main beam 100 Disassemble the inner frame 500 of the front landing gear compartment, disassemble all the connecting parts between the first main beam 100 and the surrounding frames, beams, skins and other structures, and disconnect the connection between the first main beam 100 and the surrounding structures Positioning of the first main beam 100 Refer to the positions of the first rib 600 and the second rib 700, reinstall the first main beam 100, and ensure the correct installation with reference to the distance between the first main beam 100 and the first reference. Among them, use the positioning tooling and the laser distance measuring device to ensure the correct installation of the first main beam 100 Installation of the first main beam 100 After completing the positioning of the first main beam 100, add the first angle box 800 at the connection between the first main beam 100 and the first rib 600, and add the second angle box 900 at the connection between the first main beam 100 and the second rib 700. The structures of the first angle box 800 and the second angle box 900 are customized on site. Here, the angle box belongs to the conventional settings well-known to those skilled in the art and will not be elaborated further Working positioning for the second main beam 200 Taking the first main beam 100 as the second reference, install the positioning tooling by borrowing the positions of the rotating shaft hole installation holes on the first main beam 100 and the second main beam 200, and record the distance between the second main beam 200 and the second reference. Among them, use a laser distance measuring device to record the distance between the second main beam 200 and the positioning reference Disassembly of the second main beam 200 Disassemble the inner frame 500 of the front landing gear compartment, disassemble all the connecting parts between the second main beam 200 and the surrounding frames, beams, skins and other structures, and disconnect the connection between the second main beam 200 and the surrounding structures Positioning of the second main beam 200 Refer to the positions of the first rib 600 and the second rib 700, reinstall the second main beam 200, and ensure the correct installation with reference to the distance between the second main beam 200 and the second reference. Among them, use the positioning tooling and the laser distance measuring device to ensure the correct installation of the second main beam 200 Installation of the second main beam 200 After completing the positioning of the second girder 200, a first angle box 800 is added at the connection between the second girder 200 and the first rib 600, and a second angle box 900 is added at the connection between the second girder 200 and the second rib 700. The structures of the first angle box 800 and the second angle box 900 are customized according to the site. The angle box here is a conventional setting well-known to those skilled in the art and will not be elaborated further; Installation of in-cabin parts, Restore the installation of the in-cabin cross frame of the nose landing gear according to the drawing requirements. The in-cabin cross frame of the nose landing gear includes five cross frames, namely, No. 1 cross frame, No. 2 cross frame, No. 3 cross frame, No. 4 cross frame, and No. 5 cross frame, which are arranged at intervals from top to bottom.

[0045] For a better understanding of the present invention, the following combines Figures 1 to 8 to elaborate in detail on the technical solution of the present invention: A support 300 is arranged between the first girder 100 and the second girder 200 of the landing gear. Two first connectors 410 are respectively arranged at both ends of the support 300. The two first connectors 410 can be detachably connected to the first girder 100 and the second girder 200 respectively. The second connector 420 is configured to detachably connect the first connector 410 and the support 300. Compared with the prior art, by arranging the support 300 between the first girder 100 and the second girder 200 of the landing gear, positioning and supporting the first girder 100 and the second girder 200 can effectively ensure the in-situ replacement of the first girder 100 and the second girder 200 of the landing gear, reduce the installation error of the replacement, and at the same time, the support 300 can be detachably connected to the first girder 100 and the second girder 200 of the landing gear through the first connector 410 and the second connector 420, with simple operation and convenient construction.

[0046] The specific working process of the present invention, decomposition of in-cabin parts, decomposition of the in-cabin cross frame of the nose landing gear, where the in-cabin cross frame of the nose landing gear includes five cross frames, namely, No. 1 cross frame, No. 2 cross frame, No. 3 cross frame, No. 4 cross frame, and No. 5 cross frame, which are arranged at intervals from top to bottom. Decompose the connection between the second girder 200 and the surrounding structure, and cut off and remove the first rib 600 and the second rib 700; Tooling positioning of the first girder 100, taking the second girder 200 as the first reference, installing the positioning tooling by borrowing the rotating shaft holes on the first girder 100 and the second girder 200, and recording the distance between the first girder 100 and the first reference. Among them, a laser ranging device is used to record the distance between the first girder 100 and the positioning reference; Decomposition of the first girder 100, decompose the in-cabin bulkhead 500 of the nose landing gear, decompose all the connectors between the first girder 100 and the surrounding frames, beams, skins and other structures, and disconnect the connection between the first girder 100 and the surrounding structure; Positioning of the first main beam 100. Refer to the positions of the first rib 600 and the second rib 700, reinstall the first main beam 100, and ensure proper installation with reference to the distance between the first main beam 100 and the first reference. Among them, use the positioning tooling and laser distance measuring equipment to ensure the proper installation of the first main beam 100; Installation of the first main beam 100. After completing the positioning of the first main beam 100, add the first angle box 800 at the connection between the first main beam 100 and the first rib 600, and add the second angle box 900 at the connection between the first main beam 100 and the second rib 700. Among them, the structures of the first angle box 800 and the second angle box 900 are customized according to the site. Here, the angle box is a conventional setting well-known to those skilled in the art and will not be elaborated further; Working positioning of the second main beam 200. Take the first main beam 100 as the second reference, borrow the positions of the rotating shaft hole installation holes on the first main beam 100 and the second main beam 200, and record the distance between the second main beam 200 and the second reference. Among them, use the laser distance measuring equipment to record the distance between the second main beam 200 and the positioning reference; Disassembly of the second main beam 200. Disassemble the inner frame 500 of the nose landing gear compartment, disassemble all the connecting parts between the second main beam 200 and the surrounding frames, beams, skins and other structures, and disconnect the connection between the second main beam 200 and the surrounding structures; Positioning of the second main beam 200. Refer to the positions of the first rib 600 and the second rib 700, reinstall the second main beam 200, and ensure proper installation with reference to the distance between the second main beam 200 and the second reference. Among them, use the positioning tooling and laser distance measuring equipment to ensure the proper installation of the second main beam 200; Installation of the second main beam 200. After completing the positioning of the second main beam 200, add the first angle box 800 at the connection between the second main beam 200 and the first rib 600, and add the second angle box 900 at the connection between the second main beam 200 and the second rib 700. Among them, the structures of the first angle box 800 and the second angle box 900 are customized according to the site. Here, the angle box is a conventional setting well-known to those skilled in the art and will not be elaborated further; Installation of the in-cabin parts. Reinstall the horizontal frames in the nose landing gear compartment according to the drawing requirements. Among them, the horizontal frames in the nose landing gear compartment include 1st horizontal frame, 2nd horizontal frame, 3rd horizontal frame, 4th horizontal frame, and 5th horizontal frame, which are arranged at intervals from top to bottom, a total of 5 pieces.

[0047] Through the above structure and method, the present invention can solve the technical problem in the prior art that because the procedures for repairing and replacing the damaged landing gear main beam are opposite to those during manufacturing, it is easy to cause deviations in the in-situ replacement of the nose landing gear main beam during aircraft damage repair. The specific embodiments of the present invention described above do not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and deformations made according to the technical concept of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A positioning tooling for connecting an aircraft, the aircraft having a first girder and a second girder, the first girder and the second girder being spaced apart from each other, characterized in that, Including: A support body, arranged between the first girder and the second girder; And Two connecting components, the connecting component includes a first connecting piece and a second connecting piece, the two first connecting pieces are respectively detachably connected to the first girder or the second girder, and the second connecting body is connected to the support body and can be detachably connected to the first connecting body.

2. The positioning tooling according to claim 1, characterized in that, Rotating shaft holes are respectively formed on the opposite sides of the first girder and the second girder. The first connecting piece includes a first connecting body, and one end of the first connecting body is slidably inserted into the rotating shaft hole and is clamped with the first girder or the second girder.

3. The positioning tooling according to claim 2, wherein, The first connecting body is cylindrical, an external thread is formed at one end of the first connecting body. The first connecting piece further includes a threaded connecting sleeve. One end of the first connecting body passes through the rotating shaft hole, and the threaded connecting sleeve is threadedly connected to one end of the first connecting body and abuts against the first girder or the second girder.

4. The positioning tooling according to claim 3, wherein, The first connecting body has a small-diameter section and a large-diameter section. The small-diameter section is arranged farther away from the support body relative to the large-diameter section. An external thread is formed on the circumferential outer wall of the small-diameter section. The threaded connecting sleeve is threadedly connected to the small-diameter section of the first connecting body, and the end of the large-diameter section abuts against the first girder or the second girder.

5. The positioning tooling according to claim 4, wherein, The first connecting piece further includes a retaining ring, the retaining ring is sleeved on the small-diameter section of the first connecting body and is tightly abutted against the threaded connecting sleeve and the first girder or the second girder.

6. The positioning tooling according to claim 3, wherein A first through hole is axially formed in the first connecting body. The support body is rod-shaped, and both ends of the support body are slidably inserted into the first through hole. The second connecting piece is connected to the support body and can be clamped with the first connecting body.

7. The positioning tooling according to claim 6, characterized in that, A second through hole is further formed in the first connecting body in the radial direction. The second through hole is communicated with the first through hole. A locking hole is formed in the support body relative to the second through hole. The second connecting piece includes a second connecting body. One end of the second connecting body is sequentially inserted into the second through hole and the locking hole to limit the relative sliding of the support body with respect to the first connecting body.

8. The positioning tooling according to claim 7, wherein One end of the second connecting body forms a tip, and the cross-sectional area of the tip gradually increases in the direction away from the first connecting body.

9. The positioning tooling according to claim 7, characterized in that, The second connecting piece further includes a limiting block, the limiting block is connected to the other end of the second connecting body and abuts against the first connecting body.

10. A method for replacing the main beam of an aircraft nose landing gear, characterized in that, Using the positioning tooling according to any one of claims 1-9, the specific steps are as follows: Decompose the parts in the cabin, Decompose the transverse frame in the nose landing gear cabin, decompose the connection between the second girder and the surrounding structure, and cut and remove the first rib and the second rib; Positioning the first girder tooling, Taking the second girder as the first reference, install the positioning tooling by borrowing the rotating shaft holes on the first girder and the second girder, and record the distance between the first girder and the first reference; Decomposition of the first girder, Decompose the bulkhead in the nose landing gear cabin, decompose all the connecting pieces between the first girder and the surrounding frames, beams, skins and other structures, and disconnect the connection between the first girder and the surrounding structure; Positioning of the first girder, Refer to the positions of the first rib and the second rib, reinstall the first main beam, and ensure proper installation by referring to the distance between the first main beam and the first reference; Installation of the first main beam, After completing the positioning of the first main beam, add a first angle box at the connection between the first main beam and the first rib, and add a second angle box at the connection between the first main beam and the second rib; Working positioning of the second main beam, Using the first main beam as the second reference, borrow the positions of the rotating shaft hole mounting holes on the first main beam and the second main beam, and record the distance between the second main beam and the second reference; Disassembly of the second main beam, Disassemble the bulkhead inside the nose landing gear bay, disassemble all the connecting parts between the second main beam and the surrounding frames, beams, skins and other structures, and disconnect the connection between the second main beam and the surrounding structures; Positioning of the second main beam, Refer to the positions of the first rib and the second rib, reinstall the second main beam, and ensure proper installation by referring to the distance between the second main beam and the second reference; Installation of the second main beam, After completing the positioning of the second main beam, add a first angle box at the connection between the second main beam and the first rib, and add a second angle box at the connection between the second main beam and the second rib; Installation of in-cabin parts, Reinstall the transverse frame inside the nose landing gear bay according to the drawing requirements.

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