Airplane rack and compensation welding method thereof

Abstract

The invention belongs to a welding method, and provides an airplane rack and a compensation welding method thereof in order to solve the technical problems that when an airplane rack is manufactured and assembled at present, a traditional filling welding method is adopted, welding deformation is large, and final assembly welding is difficult or cannot be implemented. The method comprises the following steps: determining a part with an assembly gap between structural components or parts, obtaining a gap value corresponding to a welding part, and determining the diameter and length of round steel for filling the welding part during welding according to the gap value and the bearing requirement of the structural components or parts; and finally, the round steel and the structural component or part are welded at the corresponding welding part. And the relationship between the diameter of the round steel and the gap value is limited. The integral connecting rigidity of the structure can be guaranteed to a great extent, and the structure has good structural strength and is easy to implement.

Description

Technical Field

[0001] The present application relates to a welding method, and particularly to an aircraft stand and a compensation welding method thereof. Background Art

[0002] Aircraft manufacturing jigs, test benches, test loading fixtures, and dummy parts are welded from profiles or steel sections. Generally, there are three requirements for the processing and manufacturing of aircraft manufacturing jigs, test benches, test loading fixtures, and dummy parts: (1) Positioning requirements. The known aircraft bench structure is required to have an accurate assembly position to ensure the aircraft assembly accuracy and test loading progress. (2) Strength requirements. The known aircraft bench is required to have sufficient load-bearing capacity when in use. (3) Stiffness requirements. The aircraft bench of a known aircraft is required to have accurate stiffness to ensure that the aircraft still has sufficient processing accuracy under load and that there is reasonable load distribution during the test.

[0003] At present, the traditional filling welding method is usually adopted. However, when the components are assembled and welded to each other, due to welding deformation, there are large gaps between the components, which makes the final assembly welding difficult or impossible to implement. Summary of the invention

[0004] The present application aims to provide an aircraft stand and a compensation welding method thereof in view of the technical problems that the conventional filling welding method is used in the current aircraft stand manufacturing and assembly, resulting in large welding deformation and difficult or impossible assembly welding.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions: In a first aspect, the present application proposes a method for compensating welding of an aircraft platform, comprising: S1, in an aircraft test bench, determining a location where there is an assembly gap between structural components or parts as a welding location, and obtaining a gap value corresponding to the welding location; S2, according to the gap value and the load-bearing requirements of the structural components or parts, determine the diameter and length of the round steel used to fill the welding part during welding; the diameter of the round steel and the gap value satisfy: 1.2g≤Φ≤2.0g, where g is the gap value and Φ is the diameter of the round steel; S3, weld the round steel to the structural components or parts at the corresponding welding positions.

[0006] Furthermore, the maximum length of round steel is: The minimum gap value of the welding part is the distance between the position where the gap is 0.5 times the diameter of the round steel and the position where the gap is 0.85 times the diameter of the round steel.

[0007] Furthermore, when the round steel is welded to the structural member or part at the corresponding welding position, the weld size is determined according to the shear strength and tensile strength of the weld and the side wall strength of the welding position.

[0008] Furthermore, the weld size includes an upper weld width, an upper weld height, a lower weld width and a lower weld height.

[0009] Furthermore, the calculation method of the upper width of the weld includes:

[0010] in, is the upper width of the weld, is the wall thickness of the weldment, is the material strength, is the weld weakening factor, is the weld strength.

[0011] Furthermore, the method for calculating the upper height of the weld includes:

[0012] in, Height of the upper part of the weld.

[0013] Furthermore, the method for calculating the lower width of the weld includes:

[0014] in, The lower width of the weld.

[0015] Furthermore, the height of the lower portion of the weld is the same as the height of the upper portion of the weld.

[0016] Furthermore, the minimum values ​​of the upper width of the weld, the upper height of the weld, the lower width of the weld, and the lower height of the weld are calculated by the following formula:

[0017]

[0018]

[0019] And the height of the lower part of the weld is the same as the height of the upper part of the weld.

[0020] In a second aspect, the present application proposes an aircraft stand prepared by using the above-mentioned aircraft stand compensation welding method.

[0021] Compared with the prior art, this application has the following beneficial effects: The present application proposes a method for compensating welding of an aircraft platform. In the aircraft platform, the position where there is an assembly gap between the structural components or parts is determined, and the gap value corresponding to the welding position is obtained. Then, according to the gap value and the load-bearing requirements of the structural components or parts, the diameter and length of the round steel used to fill the welding position during welding are determined, and finally the round steel and the structural components or parts are welded at the corresponding welding position. The relationship between the diameter of the round steel and the gap value is defined. In the compensating welding method of the present application, solid round steel is used for filling, the body strength is high, the weld bearing surface of the round steel circular cross-section compensation is large, the welding strength is high, and the round steel material cost is lower than the price of other profiles, which can maximize the cost reduction. The definition of the relationship between the diameter of the round steel and the gap value can take into account both the welding tensile strength and the weld strength, and the welding deformation is small, which is easier to implement and promote. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 A schematic flow chart of a compensation welding method for an aircraft stand according to the present application; Figure 2 This is a schematic diagram of compensation welding parameters in an embodiment of the present application. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0025] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for which protection is sought, but merely represents selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0026] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0027] In the description of the embodiments of the present application, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the invented product is usually placed when used. It is only for the convenience of describing the present application and simplifying the description, and does 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 cannot be understood as a limitation on the present application. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0028] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0029] In the description of the embodiments of the present application, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0030] Aircraft test benches cover various support, positioning and testing equipment used in the process of aircraft manufacturing, assembly, testing and maintenance, which may include various support structures, positioning devices, testing equipment and tools, etc. Aircraft manufacturing jigs, test benches, test loading fixtures and dummy parts are important components.

[0031] Aircraft manufacturing jigs are important tools used to position and fix aircraft parts during the aircraft manufacturing process. Test benches are important equipment used to test and verify aircraft components or systems. They are usually used to simulate the working environment and conditions of the aircraft in actual flight, and to perform various performance tests and verifications on aircraft components or systems. Test loading fixtures are tools used to apply specific loads during the testing of aircraft components or systems. They are usually custom-designed according to test requirements and can accurately apply the required load type and size. Dummy parts are usually used to replace real aircraft components or systems for testing and verification. They usually have similar appearance and interfaces to real parts, but the internal structure and materials may be different. As key supporting equipment in the aircraft manufacturing and testing process, the design and manufacture of structures such as aircraft manufacturing jigs, test benches, test loading fixtures and dummy parts are crucial and directly related to the assembly accuracy of the aircraft, the effectiveness of the test, and the ultimate safety performance. Therefore, the following requirements are usually placed on the above structures: (1) Positioning requirements.

[0032] Accurate positioning is the basis for ensuring the correct assembly of aircraft components and is also the key to ensuring the overall performance and flight safety of the aircraft. During the aircraft manufacturing process, the installation position of each part and component must be accurate, otherwise it may cause problems such as aircraft center of gravity shift, reduced aerodynamic performance or insufficient structural strength.

[0033] (2) Strength requirements

[0034] Aircraft will be subjected to various loads during manufacturing, testing and flight, including deadweight, flight load, test load, etc. Therefore, structures such as tooling jigs and test benches must have sufficient load-bearing capacity to ensure that they will not be damaged or deformed when subjected to these loads.

[0035] (3) Stiffness requirements.

[0036] Stiffness is the ability of a structure to resist deformation. For aircraft manufacturing tooling and test equipment, insufficient stiffness will lead to excessive deformation during loading, thus affecting the machining accuracy of the aircraft and the accuracy of the test results. At the same time, reasonable load distribution is also the key to ensuring the effectiveness of the test.

[0037] In order to enable the aircraft test bench to meet the above requirements, the present application proposes an aircraft test bench and a compensation welding method thereof, which will be described in detail below in conjunction with embodiments and drawings.

[0038] like Figure 1 As shown, it is a schematic diagram of a flow chart of a compensation welding method for an aircraft stand of the present application, which may include: S1, in an aircraft test bench, determine a location where there is an assembly gap between structural components or parts as a welding location, and obtain a gap value corresponding to the welding location.

[0039] In practical applications, the joint surfaces between structural components or parts can be checked in the aircraft test bench, and precise measuring tools (such as micrometers, feeler gauges, etc.) can be used to determine the locations where assembly gaps exist and accurately measure the gap values ​​of these locations. Obtaining the gap value is the basis for the subsequent selection of compensation materials and welding compensation.

[0040] S2. Determine the diameter and length of the round steel used to fill the welding part during welding according to the gap value and the load-bearing requirements of the structural components or parts; the diameter of the round steel and the gap value satisfy the following relationship: 1.2g≤Φ≤2.0g, where g is the gap value and Φ is the diameter of the round steel.

[0041] The choice of diameter in this application satisfies 1.2g≤Φ≤2.0g. Such a limitation not only ensures that the round steel can effectively fill the gap, but also does not cause assembly difficulties or stress concentration due to excessive diameter. More importantly, the diameter selection of the round steel is directly related to the welding gap and welding strength. If the cross-section of the round steel is too small, it will affect the height of the weld and lead to insufficient welding tensile strength. If the cross-section of the round steel is too large, the distance between the upper and lower welds will be too large, which will bring additional torque and affect the strength of the weld. Therefore, while the application uses round steel for filling, the parameters of the round steel are specifically limited because the specific application scenario is aircraft manufacturing, which has stricter requirements than conventional welding scenarios. This is also a limitation that does not need to be considered in other technical fields with relatively low requirements.

[0042] In practical applications, other parameters of round steel can also be determined according to manufacturing and processing requirements.

[0043] S3, weld the round steel to the structural components or parts at the corresponding welding positions.

[0044] In practical applications, before welding, the joint surfaces of round steel and structural components or parts can be thoroughly cleaned and pretreated to remove impurities such as oil, rust, etc. to ensure welding quality. At the same time, appropriate welding materials and welding process parameters can be selected according to welding needs.

[0045] After welding is completed, the welds usually need to be cleaned, polished and inspected to ensure that the appearance and internal quality of the welds meet the requirements. At the same time, necessary corrections and adjustments can be made to the structural components or parts to ensure that they meet the design requirements and performance.

[0046] In view of the high requirements of aircraft manufacturing and assembly, in some embodiments of the present application, the diameter, length and weld size of the round steel are further optimized: For round steel diameter: The selection of round steel diameter is directly related to the welding gap and welding strength. If the cross section of the round steel is too small, it will affect the height of the weld, resulting in insufficient welding tensile strength; if the cross section of the round steel is too large, the distance between the upper and lower welds will be too large, which will bring additional torque and affect the strength of the weld. In this embodiment, the weld gap is g and the diameter of the round steel is Φ. In general, the relationship between the diameter of the round steel and the welding gap is 1.2g≤Φ≤2.0g.

[0047] It should be noted that the welding gap refers to the gap reserved between the two parts to be welded, and the size of this gap has an important influence on the welding process and welding results. If the diameter of the round steel is too small, the welding gap may not be fully filled during welding, resulting in insufficient weld height. Weld height is one of the important indicators of weld joint strength, and insufficient height will directly affect the tensile strength of the weld joint. Too small round steel may also lead to uneven heat distribution during welding, increase the risk of welding defects (such as slag inclusions, lack of fusion, etc.), and thus reduce the overall quality of the weld joint. When the diameter of the round steel is too large, the distance between the upper and lower welds formed during the welding process will increase accordingly, which not only increases the volume of the weld joint, but also may introduce unnecessary additional torque, especially when subjected to bending or torque, these additional torques may cause the weld joint to fail prematurely. In addition, the use of round steel with a diameter that is too large will also increase the consumption of welding materials, thereby increasing welding costs. At the same time, too large round steel may also cause a decrease in welding speed, affecting production efficiency.

[0048] For the length of round steel: The length of round steel is not strictly required. The maximum length is generally determined according to the gap change combined with the diameter of the round steel, that is, the distance between the position where the minimum gap of the welding part is 0.5 times the diameter of the round steel and the position where the gap is 0.85 times the diameter of the round steel. Specifically, the minimum gap of the welding part should be at least 0.5 times the diameter of the round steel, and the maximum gap should not exceed 0.85 times the diameter of the round steel. The length of the round steel is defined by the distance between these two gap positions. This design is intended to ensure that during the welding process, the round steel can fully fill the welding gap to form a uniform and strong weld. At the same time, avoid excessive gaps that lead to reduced welding quality or too small gaps that cause welding difficulties.

[0049] In actual applications, due to the ever-changing conditions on the construction site, the length of the round steel can also be considered for actual construction convenience. The length can be shortened according to the conditions on the construction site. In addition, the round steel can also be spliced ​​and welded by multiple sections of round steel, which not only improves the flexibility of construction, but also helps to reduce material waste and reduce costs.

[0050] For weld size: The weld size is mainly to ensure the welding strength, and is calculated according to the shear and tensile strength of each weld and the strength of the side wall of the welded part. In welding engineering, the design of weld size is also a key link to ensure welding strength.

[0051] In some embodiments of the present application, the calculation can be performed according to the following formula: Assume the wall thickness of the weldment is t and the material strength is , the weld strength is , the weld weakening factor is The weld weakening factor K is related to the welding base material and welding method. In practical applications, the specific value can be obtained by referring to the manual: Upper width of weld for:

[0052] Upper width of weld The calculation takes into account the influence of material strength, weld strength and weld weakening factor on the upper weld width. The coefficient of 0.6 is to adjust the deviation between the actual load-bearing capacity of the weld under shear force and the calculated value.

[0053] Weld upper height for:

[0054] Weld bottom height Height to upper weld Consistent.

[0055] Since weld height directly affects the tensile strength of the weld, these two values ​​are usually set equal and are proportional to the material strength, weld strength, and weld weakening factor.

[0056] Weld bottom width for:

[0057] The calculation of the lower width of the weld is similar to that of the upper width of the weld, but multiplied by a factor of 1.2. This is to take into account that the lower part of the weld may be subjected to greater shear forces or require a larger width to ensure strength due to thermal effects during welding.

[0058] In some other embodiments of the present application, the weld size calculated by the above formula can be used as the minimum value. In the actual construction process, since the local fine parts may not be completely filled with welding, the weld size can be appropriately adjusted and increased. This adjustment can be made based on the actual construction conditions and welding quality requirements.

[0059] The compensating welding method of the present application can select round steel of appropriate specifications for the parts with large gaps between the known aircraft platform components, and weld the round steel as a compensating part to the relevant parts, which can largely ensure the overall connection rigidity of the structure, have good structural strength, and be easy to implement. The principle is simple and easy to implement welding. The method of the present application is highly adaptable, can ensure the designed connection position, and maximize the design rigidity of the aircraft platform. After parameter design, high connection strength can be ensured. Compared with the traditional caulking method, round steel is a solid body with high body strength, and the weld bearing surface of the circular cross-section compensation is large and the welding strength is high. Furthermore, the material cost of round steel is lower than that of other profiles, which can minimize costs.

[0060] The following is a specific example of this application: The known welding position of the aircraft test bench assembly includes assembly part A and assembly part B. The thickness of the assembly part is 8mm, the material of the assembly part is Q235, and the weld strength is consistent with the material of the part. Figure 2 The figure shows a schematic diagram of compensation welding parameters.

[0061] Step 1: Measure and obtain the gap value between the components at the welding position of the aircraft bench assembly, which is 10mm ( Figure 2 (middle Y6); Step 2: According to the gap value obtained in step 1, select the round steel ( Figure 2 X2) diameter is 20mm ( Figure 2 Y3 in the middle). Using manual arc welding, the welding weakening coefficient is 0.9, and the upper size of the weld is calculated ( Figure 2 Center X1): minimum calculated width ds = 14.8mm, minimum height hs = 8.9mm; weld bottom size ( Figure 2 X3): The minimum calculated width dx = 10.7mm, the minimum height hx = 8.9mm. The actual weld size is ds = 15mm, hs = 10mm, dx = 12mm, hx = 10mm, corresponding to Figure 2 Y2, Y1, Y5 and Y4 in .

[0062] Step 3: Weld Part A and Part B to the round steel according to the structural dimensions determined in Step 2 to complete the welding compensation assembly.

[0063] Based on the above-mentioned aircraft stand compensation welding method, the present application also proposes an aircraft stand prepared by using the above-mentioned aircraft stand compensation welding method.

[0064] The above are only preferred embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A method for compensating welding of an aircraft platform, characterized in that: include: S1, in an aircraft test bench, determining a location where there is an assembly gap between structural components or parts as a welding location, and obtaining a gap value corresponding to the welding location; S2, according to the gap value and the load-bearing requirements of the structural components or parts, determine the diameter and length of the round steel used to fill the welding part during welding; the diameter of the round steel and the gap value satisfy: 1.2g≤Φ≤2.0g, where g is the gap value and Φ is the diameter of the round steel; S3, weld the round steel to the structural components or parts at the corresponding welding positions.

2. The aircraft stand compensation welding method according to claim 1, characterized in that: The maximum length of round steel is: The minimum gap value of the welding part is the distance between the position where the gap is 0.5 times the diameter of the round steel and the position where the gap is 0.85 times the diameter of the round steel.

3. The aircraft platform compensation welding method according to claim 2 is characterized in that: When the round steel is welded to the structural component or part at the corresponding welding position, the weld size is determined according to the shear strength and tensile strength of the weld and the side wall strength of the welding position.

4. The aircraft platform compensation welding method according to claim 3 is characterized in that: The weld size includes the weld upper width, the weld upper height, the weld lower width and the weld lower height.

5. The aircraft platform compensation welding method according to claim 4, characterized in that: The calculation method of the upper width of the weld includes: in, is the upper width of the weld, is the wall thickness of the weldment, is the material strength, is the weld weakening factor, is the weld strength.

6. The aircraft platform compensation welding method according to claim 5, characterized in that: The calculation method of the upper height of the weld includes: in, Height of the upper part of the weld.

7. The aircraft platform compensation welding method according to claim 6, characterized in that: The method for calculating the lower width of the weld includes: in, The lower width of the weld.

8. The aircraft platform compensation welding method according to claim 7, characterized in that: The height of the lower part of the weld is the same as the height of the upper part of the weld.

9. The aircraft platform compensation welding method according to claim 4, characterized in that: The minimum values ​​of the upper width of the weld, the upper height of the weld, the lower width of the weld and the lower height of the weld are calculated by the following formula: And the height of the lower part of the weld is the same as the height of the upper part of the weld.

10. An aircraft platform manufactured by the aircraft platform compensation welding method according to any one of claims 1 to 9.

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