Auxiliary tool for assembling aircraft wings

Abstract

The auxiliary tool comprises a support body, a support base is arranged in the middle of the rear end face of the support body, an adjusting assembly is arranged at the tail end of the support base, a second supporting leg is arranged at the bottom adjusting end of the adjusting assembly, and adjustable supporting legs are symmetrically distributed at the two ends of the support body. A plurality of holes A for mounting a fuselage center block symmetrically penetrate through the two sides of the bracket main body, and a plurality of holes B for mounting a wing front beam symmetrically penetrate through the two sides of the bracket main body. By means of the tool, the fuselage connecting center block and the wing front beam can be drilled on the same tool, it is ensured that hole positions are consistent, the hidden danger of hole position deviation is eliminated, the working efficiency and the mounting quality are improved, and aircraft safety is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft wing assembly, and particularly to an auxiliary tooling for aircraft wing assembly. Background Art

[0002] The wing is one of the important components of an aircraft and is installed on the fuselage. Its most important function is to generate lift, and together with the tail wing, it forms good stability and maneuverability. In addition, ammunition, equipment, and fuel tanks can be loaded inside the wing, and landing gears, engines, suspended missiles, auxiliary fuel tanks, and other external equipment can be installed on the wing.

[0003] The connection center blocks between the left and right wings and the fuselage of existing aircraft are bolt-connected. Before docking, holes need to be drilled at the end of the connection center block on the fuselage and the front beam of the wing, and the hole positions of the two need to be kept consistent. Before using the tooling, the holes on the connection center block of the fuselage are obtained on machining equipment, and the installation holes at the end of the front beam of the wing are drilled on the fuselage during docking with the connection center block of the fuselage. The working area inside the fuselage is narrow, and there is no good operating space during drilling, resulting in poor drilling quality, affecting the wing docking installation and even the flight safety of the aircraft. Moreover, the installation work efficiency is low, and when there is a deviation during docking, it is easy to cause damage to the installation bolts. Therefore, an auxiliary tooling for aircraft wing assembly is proposed to solve the above problems. Summary of the Invention

[0004] (I) Object of the Invention To solve the technical problems existing in the background art, the present invention proposes an auxiliary tooling for aircraft wing assembly. Through this tooling, the connection center block of the fuselage and the front beam of the wing can be drilled on the same tooling, ensuring consistent hole positions, eliminating potential hazards of hole position deviation, improving work efficiency and installation quality, and ensuring the safety of the aircraft.

[0005] (II) Technical Solution An auxiliary tooling for aircraft wing assembly includes a bracket main body. A bracket base is provided in the middle of the rear end face of the bracket main body. An adjusting assembly is provided at the end of the bracket base. A second support foot is provided on the bottom adjusting end of the adjusting assembly. Adjustable legs are symmetrically distributed at both ends of the bracket main body; A plurality of A holes for installing the fuselage center block are symmetrically penetrated through both sides of the bracket main body, and a plurality of B holes for installing the front beam of the wing are also symmetrically penetrated through both sides of the bracket main body.

[0006] Preferably, the adjusting assembly includes a second rotation knob, a second transmission rod, and a second transmission hole. The second transmission hole vertically penetrates through the end of the bracket base. The second transmission rod penetrates through the bracket base through the second transmission hole. The second rotation knob is provided at the top of the second transmission rod, and the second support foot is provided at the bottom of the second transmission rod.

[0007] Preferably, both ends of the second transmission rod are coaxially connected between the second rotation knob and the second support leg.

[0008] Preferably, the adjustable support leg includes a support mounting block, a first support leg, a first rotation knob, a first transmission hole, and a first transmission rod. The support mounting block is detachably connected to the side of the bracket body. The first transmission hole vertically penetrates the support mounting block. The first transmission rod penetrates the support mounting block through the first transmission hole. The top of the first transmission rod is coaxially connected to the first rotation knob, and the bottom of the first transmission rod is coaxially connected to the first support leg.

[0009] Preferably, both the first transmission rod and the second transmission rod are threaded rods, both the second transmission hole and the first transmission hole are threaded holes, the first transmission rod is threadedly connected to the first transmission hole, and the second transmission rod is threadedly connected to the second transmission hole.

[0010] Preferably, it further includes a first screw. A plurality of the first screws penetrate the support mounting block and extend into the interior of the bracket body, and the bracket body is threadedly connected to the first screw.

[0011] Preferably, reinforcing plates are further provided at both ends of the bracket base and on the side of the bracket body. A plurality of second screws in one group penetrate one side of the reinforcing plate and are threadedly connected to the bracket body, and a plurality of second screws in another group penetrate the other side of the reinforcing plate and are threadedly connected to the bracket base.

[0012] Preferably, the sizes and shapes of the A hole and the B hole match the positioning holes of the fuselage center block and the front wing beam.

[0013] Preferably, the bracket body, the bracket base, and the adjustable support leg are made of high-strength and corrosion-resistant metal materials.

[0014] Compared with the prior art, the above technical solutions of the present invention have the following beneficial technical effects: 1. The auxiliary tooling for assembling the aircraft wing can accurately obtain the installation hole positions of the fuselage connection center block and the end of the front wing beam before docking, avoid operations in the narrow space inside the fuselage, ensure the docking and installation quality, drill holes for the fuselage connection center block and the front wing beam on the same tooling, ensure the consistency of the hole positions, avoid potential hole position deviation hazards in the subsequent installation process, improve work efficiency, and at the same time obtain good installation quality to ensure the safety of the aircraft.

[0015] 2. The auxiliary tooling for assembling the aircraft wing has a simple structure, is easy to use, has a low cost, is easy to maintain, and can improve the wing installation efficiency. Brief Description of the Drawings

[0016] Figure 1 FIG. 1 is a schematic structural view of an auxiliary tooling for aircraft wing assembly proposed by the present invention.

[0017] Figure 2 FIG. 2 is a schematic structural view of the main body of an auxiliary tooling for aircraft wing assembly proposed by the present invention.

[0018] Figure 3 FIG. 3 is a rear view of an auxiliary tooling for aircraft wing assembly proposed by the present invention.

[0019] Figure 4 FIG. 4 is a cross-sectional view of an adjustment assembly in an auxiliary tooling for aircraft wing assembly proposed by the present invention.

[0020] Figure 5 FIG. 5 is a cross-sectional view of an adjustable leg in an auxiliary tooling for aircraft wing assembly proposed by the present invention.

[0021] Reference Numerals: 1, reinforcement plate; 2, adjustable leg; 201, support mounting block; 202, first support foot; 203, first rotation knob; 204, first transmission hole; 205, first screw; 206, first transmission rod; 3, bracket main body; 4, bracket base; 5, adjustment assembly; 501, second rotation knob; 502, second transmission rod; 503, second support foot; 504, second transmission hole; 6, hole A; 7, hole B; 8, second screw. Detailed Description of the Invention

[0022] 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 in conjunction with the specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present invention. In addition, in the following description, the descriptions of well-known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0023] In the description of the invention, it should be noted that the orientation or positional relationships indicated by the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", etc. are based on the orientation or positional relationships shown in the drawings. These are only for the convenience of describing 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 therefore should not be construed as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0024] In the description of the invention, it should be noted that unless otherwise clearly specified and defined, terms such as "installed", "equipped with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, such as welding, riveting, bonding, etc., or a detachable connection, such as threaded connection, key connection, pin connection, etc., or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. 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.

[0025] As Figures 1-5 As shown, an auxiliary tooling for aircraft wing assembly proposed by the present invention includes a support main body 3. A support base 4 is provided in the middle of the rear end face of the support main body 3. An adjusting component 5 is provided at the end of the support base 4. Among them, the support base 4 and the support main body 3 are vertically arranged. A second support foot 503 is provided on the bottom adjusting end of the adjusting component 5. Adjustable legs 2 are symmetrically distributed at both ends of the support main body 3; a plurality of A holes 6 for installing the fuselage center block are symmetrically penetrated through both sides of the support main body 3, and a plurality of B holes 7 for installing the wing front beam are symmetrically penetrated through both sides of the support main body 3.

[0026] In the present invention, the pitch of the A holes 6 is designed according to the aviation standard part interface, and the pitch tolerance is controlled within 0.05 mm. With the alloy positioning pin shaft treated by liquid nitrogen cooling, the thermal expansion coefficient compensation is realized. Through the laser tracker calibration system, the coplanarity of the fuselage center block and the wing front beam is ensured.

[0027] ‌The diameter of the B holes 7 matches the wing front beam bolts (not shown), and the edges of the hole positions are chamfered to avoid scratches during assembly; Each group of B holes 7 contains 4 - 6 hole positions, which are distributed in a linear array, and the pitch tolerance is controlled within ±0.1 mm to ensure uniform distribution of the front beam load.

[0028] The first rotation knob 203 is integrated with a scale (minimum scale 0.5 mm), supports visual fine adjustment, and the adjustment range is 0 - 200 mm; The bottom of the leg is provided with a first support foot 202, and the foot pad is made of nitrile rubber with a friction coefficient ≥0.6, which effectively prevents the tooling from sliding due to external forces, vibrations or tilting during operation, provides a stable and reliable support foundation for the tooling, and ensures the safety and stability during the use of the tooling.

[0029] The adjusting component 5 realizes vertical adjustment through a second transmission rod 502. The second transmission rod 502 is made of stainless steel (nickel-plated on the surface for rust prevention); the nickel coating can effectively prevent the direct contact between the second transmission rod 502 and moist air / aviation hydraulic oil, form a dense passivation film, and block the path of electrochemical corrosion.

[0030] The adjustment stroke of the adjustment component 5 is 50 mm, and the adjustment accuracy is ±0.05 mm. During the wing installation operation, due to the complexity of the wing's own structure, the slight differences in the material density of each part, and many factors such as the position of the lifting point, the occurrence of the center-of-gravity offset phenomenon is extremely likely. Through the adjustment component 5, the center-of-gravity offset can be compensated in real time, and fine adjustment can be carried out within the range of 50 mm. Through the fine adjustment of 0.05 mm, when the center of gravity shows an offset trend, the safety and accuracy of the wing hoisting operation are guaranteed, potential risks caused by the center-of-gravity offset are avoided, and a solid and reliable technical support is provided for the entire wing installation process.

[0031] Moreover, for the three-point support system (two adjustable legs 2 + adjustment component 5), the tooling can automatically adapt to the working condition with a ground inclination angle ≤ 5°.

[0032] In an optional embodiment, the adjustment component 5 includes a second rotation knob 501, a second transmission rod 502, and a second transmission hole 504. The second transmission hole 504 vertically penetrates the end of the bracket base 4. The second transmission rod 502 penetrates the bracket base 4 through the second transmission hole 504. The second rotation knob 501 is provided at the top of the second transmission rod 502, and the second support foot 503 is provided at the bottom of the second transmission rod 502.

[0033] It should be noted that by rotating the second rotation knob 501, the second rotation knob 501 can drive the second transmission rod 502 to rotate, so that the second transmission rod 502 can be lifted and lowered inside the second transmission hole 504, enabling it to drive the second support foot 503 to achieve fine adjustment in the vertical direction and compensate for the center-of-gravity offset during the assembly process.

[0034] In an optional embodiment, both ends of the second transmission rod 502 are coaxially connected between the second rotation knob 501 and the second support foot 503.

[0035] It should be noted that precision center holes are machined at both ends of the second transmission rod 502, and they are respectively connected to the second rotation knob 501 and the second support foot 503 through elastic couplings (not shown); In an alternative embodiment, the adjustable support leg 2 includes a support mounting block 201, a first support foot 202, a first rotation knob 203, a first transmission hole 204, and a first transmission rod 206. The support mounting block 201 is detachably connected to the side of the bracket main body 3. The first transmission hole 204 vertically penetrates the support mounting block 201. The first transmission rod 206 passes through the support mounting block 201 through the first transmission hole 204. The top of the first transmission rod 206 is coaxially connected to the first rotation knob 203, and the bottom of the first transmission rod 206 is coaxially connected to the first support foot 202. Both the first transmission rod 206 and the second transmission rod 502 are threaded rods, and both the second transmission hole 504 and the first transmission hole 204 are threaded holes. There is a threaded connection between the first transmission rod 206 and the first transmission hole 204, and there is a threaded connection between the second transmission rod 502 and the second transmission hole 504.

[0036] It should be noted that by rotating the first rotation knob 203, the first rotation knob 203 can vertically lift and lower inside the first transmission hole 204 through the first transmission rod 206, thereby driving the first support foot 202 to also lift and lower, so that the leveling of the tooling can be completed according to actual usage requirements.

[0037] Among them, each rotation of the first rotation knob 203 drives the first support foot 202 to lift and lower by 3 mm, and the adjustment range is 0 - 250 mm.

[0038] Moreover, the adjustable support leg 2 and the bracket main body 3 are detachably connected, so that it is convenient to detach the adjustable support leg 2 from the bracket main body 3 for maintenance.

[0039] In an alternative embodiment, it further includes a first screw 205. A plurality of first screws 205 penetrate through the support mounting block 201 and extend into the interior of the bracket main body 3. There is a threaded connection between the bracket main body 3 and the first screw 205.

[0040] It should be noted that when the support mounting block 201 needs to be disassembled, assembled and maintained, a plurality of first screws 205 can be removed by a suitable tool, and then the support mounting block 201 can be separated from the bracket main body 3; when assembly is required, first align the support mounting block 201 with the preset opening of the bracket main body 3, and then drive a plurality of first screws 205 to rotate by a suitable tool, so that the support mounting block 201 can be installed on the bracket main body 3.

[0041] In an alternative embodiment, reinforcement plates 1 are further provided at both ends of the bracket base 4 and on the sides of the bracket main body 3. A plurality of second screws 8 in a group penetrate through one side of the reinforcement plate 1 and are threadedly connected to the bracket main body 3, and another group of a plurality of second screws 8 penetrate through the other side of the reinforcement plate 1 and are threadedly connected to the bracket base 4.

[0042] It should be noted that the reinforcement plate 1 is L-shaped and fixed to the sides of the bracket body 3 and the bracket base 4 by a plurality of second screws 8, thereby enhancing the stability of the installation of the bracket base 4.

[0043] Moreover, the reinforcement plate 1 is made of aviation aluminum alloy to reduce the risk of resonance.

[0044] In an alternative embodiment, the sizes and shapes of the A holes 6 and the B holes 7 match the positioning holes of the fuselage center block and the front wing beam.

[0045] It should be noted that the matching of the positioning holes ensures that the fuselage center block and the front wing beam can be accurately installed on the bracket body 3. This not only improves the assembly accuracy but also helps to reduce errors and unnecessary adjustments during the assembly process, thereby improving the overall assembly efficiency.

[0046] Secondly, this matching design also enhances the stability and safety of the assembly. When the fuselage center block and the front wing beam are tightly connected to the bracket body 3, their relative positions are fixed, reducing the risk of displacement or loosening in subsequent assembly steps.

[0047] In an alternative embodiment, the bracket body 3, the bracket base 4, and the adjustable legs 2 are made of high-strength and corrosion-resistant metal materials.

[0048] It should be noted that, firstly, high-strength metal materials can ensure the structural integrity and stability of the tooling when bearing the weight of aircraft components and various forces generated during the assembly process. Ensuring assembly accuracy and worker safety is of utmost importance.

[0049] Secondly, corrosion resistance is particularly important for tooling that is exposed to the outdoors or harsh environments for a long time. It can prevent the performance degradation or damage of the tooling due to oxidation, corrosion, etc., thereby extending the service life of the tooling and reducing maintenance costs.

[0050] Working principle: Firstly, find the fuselage connection center block and carefully identify the positioning holes on it. At the same time, determine the position of the A hole 6 on the bracket body 3. Select a suitable connecting bolt, accurately align the positioning hole of the fuselage connection center block with the A hole 6 of the bracket body 3. After ensuring that the two are completely coincident, use a fastening tool such as a wrench to perform the fastening operation according to the specified torque value to make the two firmly connected. Then, use the adjustable legs 2 and the adjustment assembly 5 to calibrate the position state of the bracket body 3 and the bracket base 4. During the adjustment process, auxiliary tools such as a spirit level can be used to repeatedly fine-tune the height of the adjustable legs 2 and the angle of the adjustment assembly 5 until the spirit level shows that the bracket body 3 and the bracket base 4 are in a standard vertical and horizontal state to ensure the stability of the entire bracket system. Subsequently, install the wing part. Observe the ends of the front and rear beams of the wing to find the pre-set positioning holes thereon. At the same time, identify the position of the B hole 7 on the bracket body 3. Once again, use a suitable connecting bolt to accurately align and match the positioning holes at the ends of the front and rear beams of the wing with the B hole 7 of the bracket body 3. After confirmation, use the same fastening method as before and use a wrench to firmly fasten it to make the wing closely connected to the bracket body 3. After that, since the installation accuracy of the front and rear beams of the wing has an important impact on the overall performance, at this time, fine adjustment of the knob of the adjustable leg 2 is required. When the knob of the adjustable leg 2 rotates, it will change the telescopic length of the leg, thereby affecting the local height of the bracket body 3, so as to achieve the balance adjustment of the rear beam and the front beam. During the adjustment process, data such as the height difference between the front and rear beams can be measured by a measuring tool to monitor the adjustment effect in real time until the rear beam and the front beam reach an ideal balance state.

[0051] Finally, install and fasten the automatic feed drill on the bracket body 3 to ensure that the position of the automatic feed drill is accurate and stable, and the direction of its drill bit needs to be accurately aligned with the front beam of the wing. Start the automatic feed drill and let it perform a through-hole operation along the front beam of the wing from front to back, so as to obtain a precise installation hole at the end of the front beam of the wing; The fuselage connection center block and the front beam of the wing are drilled on the same tooling, ensuring the consistency of the hole positions, avoiding potential hole position deviation hazards in the subsequent installation process, improving work efficiency, and at the same time obtaining good installation quality to ensure the safety of the aircraft.

[0052] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An auxiliary tooling for aircraft wing assembly, comprising a bracket main body (3), characterized in that, A support base (4) is provided in the middle of the rear end face of the support main body (3). An adjusting assembly (5) is provided at the end of the support base (4). A second support leg (503) is provided at the bottom adjusting end of the adjusting assembly (5). Adjustable legs (2) are symmetrically distributed at both ends of the support main body (3). A plurality of A holes (6) for installing the fuselage center block are symmetrically penetrated through both sides of the support main body (3). A plurality of B holes (7) for installing the front wing beam are also symmetrically penetrated through both sides of the support main body (3).

2. The auxiliary tooling for aircraft wing assembly according to claim 1, characterized in that The adjusting assembly (5) includes a second rotation knob (501), a second transmission rod (502), and a second transmission hole (504). The second transmission hole (504) vertically penetrates through the end of the support base (4). The second transmission rod (502) penetrates through the support base (4) through the second transmission hole (504). The second rotation knob (501) is provided at the top of the second transmission rod (502). The second support leg (503) is provided at the bottom of the second transmission rod (502).

3. The auxiliary tooling for aircraft wing assembly according to claim 2, characterized in that Both ends of the second transmission rod (502) are coaxially connected between the second rotation knob (501) and the second support leg (503).

4. The auxiliary tooling for aircraft wing assembly according to claim 2, characterized in that The adjustable leg (2) includes a support mounting block (201), a first support leg (202), a first rotation knob (203), a first transmission hole (204), and a first transmission rod (206). The support mounting block (201) is detachably connected to the side of the support main body (3). The first transmission hole (204) vertically penetrates through the support mounting block (201). The first transmission rod (206) penetrates through the support mounting block (201) through the first transmission hole (204). The top of the first transmission rod (206) is coaxially connected to the first rotation knob (203). The bottom of the first transmission rod (206) is coaxially connected to the first support leg (202).

5. An auxiliary tooling for aircraft wing assembly according to claim 4, characterized in that, Both the first transmission rod (206) and the second transmission rod (502) are threaded rods. Both the second transmission hole (504) and the first transmission hole (204) are threaded holes. The first transmission rod (206) is threadedly connected to the first transmission hole (204). The second transmission rod (502) is threadedly connected to the second transmission hole (504).

6. The auxiliary tooling for aircraft wing assembly according to claim 4, wherein, It further includes a first screw (205). A plurality of the first screws (205) penetrate through the support mounting block (201) and extend into the interior of the support main body (3). The support main body (3) is threadedly connected to the first screw (205).

7. An auxiliary tooling for aircraft wing assembly according to claim 1, characterized in that, Reinforcing plates (1) are also provided at both ends of the support base (4) and on the sides of the support main body (3). A group of a plurality of second screws (8) penetrate through one side of the reinforcing plate (1) and are threadedly connected to the support main body (3). Another group of a plurality of second screws (8) penetrate through the other side of the reinforcing plate (1) and are threadedly connected to the support base (4).

8. The auxiliary tooling for aircraft wing assembly according to claim 1, characterized in that, The sizes and shapes of the A holes (6) and the B holes (7) match the positioning holes of the fuselage center block and the front wing beam.

9. The auxiliary tooling for aircraft wing assembly according to claim 1, characterized in that, The bracket main body (3), the bracket base (4), and the adjustable leg (2) are made of high-strength and corrosion-resistant metal materials.

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