Method for determining material distribution of upright post of wing assembly fixture

Abstract

The invention discloses a wing assembly fixture column material distribution determination method, which comprises the following steps: step 1, determining the structure and composition parts of a wing assembly fixture, and the geometric dimensions and use materials of each part; step 2, based on the structure of the wing assembly fixture, determining two feature points of the wing assembly fixture, which are distributed as end points at two ends of an upper beam expansion plate of the wing assembly fixture; 3, establishing a finite element calculation model of the wing assembly fixture on the basis of geometric dimensions and used materials of all parts in the wing assembly fixture structure, obtaining offset coefficients of all feature points in the wing assembly fixture under different material distributions by changing material distributions in a wing root upright post and a wing tip upright post, and establishing a finite element calculation model of the wing assembly fixture; and the material distribution of the upright posts of the wing assembly fixture is optimized. According to the technical scheme provided by the invention, the problems of poor thermal deformation and assembly stress caused by mismatching of a wing assembly fixture stand column material and a wing component material are solved.

Description

Technical Field

[0001] The present invention relates to, but is not limited to, the field of aircraft assembly jigs, and in particular to a method for determining material distribution of columns of a wing assembly jig. Background Art

[0002] The wing assembly jig is a special tooling equipment used for assembling aircraft wing components. It firmly supports the wing components during the assembly process, ensuring that the wing components (such as skin, leading and trailing edges, ribs, spars, etc.) are accurately positioned during assembly, thereby protecting the aerodynamic shape and structural strength of the wing.

[0003] The wing assembly jig is the benchmark for aircraft wing assembly precision and quality. To prevent wing component movement or deformation, current wing assembly jig structures are mostly constructed of steel. However, the aircraft wing assembly process often lasts from several weeks to several months. During this cycle, the jig undergoes thermal expansion or contraction due to ambient temperature. Wing components are mostly made of aluminum or composite materials, and their thermal deformation does not match that of the jig. This results in tension or compression of the wing components during assembly, generating assembly stress and reducing assembly precision and quality.

[0004] Therefore, in order to solve the forced deformation and assembly stress caused by temperature difference during the assembly cycle of wing products, the column material of the wing assembly jig is changed to make the deformation of the assembly jig consistent with the product deformation, reduce the product assembly stress, and improve the wing assembly quality. A method for determining the material distribution of the wing assembly jig column is proposed. Summary of the Invention

[0005] The purpose of the present invention is: in order to solve the above-mentioned problems, the present invention provides a method for determining the material distribution of the columns of a wing assembly jig, so as to solve the problem that the existing wing assembly jig generates assembly stress due to the mismatch between the thermal deformation of the wing product and the wing product, thereby reducing the product assembly accuracy and assembly quality.

[0006] The technical solution of the present invention is as follows: The present invention provides a method for determining the material distribution of a wing assembly frame column, comprising: Step 1: Determine the structure and components of the wing assembly jig, as well as the geometric dimensions and materials used for each component; Step 2: Based on the structure of the wing assembly jig, two characteristic points of the wing assembly jig are determined, which are distributed as follows: two end points of the expansion plate of the upper beam of the wing assembly jig; Step 3: Based on the geometric dimensions and materials used of each component in the wing assembly jig structure, a finite element calculation model of the wing assembly jig is established. By changing the material distribution in the wing root column and wingtip column, the offset coefficient of each characteristic point in the wing assembly jig under different material distributions is obtained, and the material distribution of the columns of the wing assembly jig is optimized.

[0007] Optionally, in the above-mentioned method for determining the material distribution of wing assembly frame columns, step 1 includes: Step 11, determining the structure and components of the wing assembly jig, which include: an upper beam, a lower beam, an upper beam expansion plate, a lower beam expansion plate, a slide rail, a wing root column, and a wing tip column. The structure is as follows: the wing root column, the upper beam, and the wing tip column are sequentially connected to form a gate-shaped frame, one end of the lower beam is fixedly connected to the ground, and its lower end face is placed on a slide rail parallel to the length direction of the lower beam, one end of the upper beam expansion plate is fixedly connected to the end of the upper beam close to the wing root column, and its upper end face is connected parallel to the upper beam via the slide rail, and one end of the lower beam expansion plate is fixedly connected to the end of the lower beam close to the wing root column, and its lower end face is connected parallel to the lower beam via the slide rail. Step 12, based on the structure of the wing assembly jig, determining the geometric dimensions of the upper beam, lower beam, upper beam expansion plate, lower beam expansion plate, wing root column and wing tip column in the wing assembly jig; Step 13, based on the structure of the wing assembly jig, determine the materials used for the upper beam, lower beam, upper beam expansion plate, lower beam expansion plate in the wing assembly jig, as well as the initial materials used for the wing root column and wingtip column.

[0008] Optionally, in the above-mentioned method for determining the material distribution of wing assembly frame columns, in step 13, the material used for each component is confirmed in the following manner: The upper and lower beams are made of Q235 steel, and the wing root and wing tip columns were originally made of Q235 steel. If the wing product is made of aluminum alloy, the upper beam expansion plate and the lower beam expansion plate are 7075 aluminum, and part of the material of the wing root column and the wing tip column is replaced with 7075 aluminum; If the wing product is a composite material, the upper beam expansion plate and the lower beam expansion plate are made of Invar steel, and part of the material of the wing root column and the wingtip column is replaced with Invar steel.

[0009] Optionally, in the above-mentioned method for determining the material distribution of wing assembly frame columns, step 3 includes: Step 31: Based on the geometric dimensions and materials of each component in the wing assembly jig structure, a finite element calculation model of the wing assembly jig is established, and some of the initial materials used in the wing root columns and wingtip columns are changed to obtain wing root columns and wingtip columns with various material distribution combinations. Temperature differences are applied to the wing assembly jigs with various material distributions. Through finite element simulation, the temperature difference of the wing assembly frame under different material distribution combinations is calculated. The displacement caused by the wing assembly jig includes the spanwise displacement and the heading displacement; Step 32, extracting the spanwise displacement and the heading displacement of each characteristic point in the wing assembly jig from the simulation calculation results in step 31; and establishing a shape characteristic equation of the wing assembly jig based on the displacement of each characteristic point of the wing assembly jig; Step 33 , calculating the offset coefficient based on the shape characteristic equation of the wing assembly jig, and obtaining the optimal option of the material distribution combination of the wing root column and the wing tip column in the wing assembly jig.

[0010] Optionally, in the above-mentioned method for determining the material distribution of the wing assembly frame columns, in step 33, The closer the calculated offset coefficient is to 1, the closer the shape characteristics of the wing assembly jig before and after deformation are, that is, the better the material distribution combination of the corresponding wing root column and wingtip column.

[0011] Optionally, in the above-mentioned method for determining the material distribution of a wing assembly frame column, In step 31, the proportion of the initial material used for the wing root column and the wing tip column is changed to 0-100%; In step 31, the temperature difference applied to the wing assembly jig is based on the working cycle and ambient temperature of the wing assembly jig. =10℃.

[0012] Optionally, in the above-mentioned method for determining the material distribution of a wing assembly frame column, The span direction is the length direction of the wing assembly jig, which is set as the x direction; the heading direction is the height direction of the wing assembly jig, which is set as the y direction; in step 32, 、 are the coordinates of the left end point of the upper beam expansion plate in the heading and span directions, 、 They are respectively the heading displacement and spanwise displacement of the left end point of the upper beam expansion plate after a temperature difference of 10°C. 、 are the coordinates of the right end point of the upper beam expansion plate in the heading and span directions, 、 They are the heading displacement and spanwise displacement of the right end point of the upper beam expansion plate after a temperature difference of 10°C.

[0013] Optionally, in the above-mentioned method for determining the material distribution of the wing assembly jig columns, the shape characteristic equation and the offset coefficient of the wing assembly jig established in step 32 are: ; ; ; in, is the initial shape characteristic between the left end point of the upper beam expansion plate and the right end point of the upper beam expansion plate, is the deformation shape characteristic between the left end point of the upper beam expansion plate and the right end point of the upper beam expansion plate after experiencing a temperature difference of 10°C, Locate the offset factor for the wing assembly jig.

[0014] Beneficial effects of the invention: In response to the assembly stress and forced deformation problems caused by the mismatch between the current wing assembly jig column material and the wing product material, the present invention provides a method for determining the material distribution of the wing assembly jig column. By determining the structure and components of the wing assembly jig, the geometric dimensions and initial material distribution of each component, a finite element calculation model of the wing assembly jig is established, the material distribution of the wing jig column is changed, the deformation coefficient of each characteristic point in the wing assembly jig under different material distributions is obtained, the column material distribution of the wing assembly jig is optimized, and the assembly stress during the wing assembly process is reduced. The method for determining the material distribution of the jig column provided by the present invention is a positive wing assembly jig design method, which significantly improves the wing assembly quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0016] Figure 1 A flow chart of a method for determining material distribution of a wing assembly frame column provided in an embodiment of the present invention; Figure 2 A schematic diagram of a wing assembly jig structure and coordinate system provided by an embodiment of the present invention; Figure 3 A diagram showing the structural dimensions of a wing assembly jig provided in an embodiment of the present invention; Figure 4 A schematic diagram of the proportions of different materials in the columns of a wing assembly jig structure provided by an embodiment of the present invention; Figure 5 This is a diagram of the deformation coefficient of the wing assembly jig structure under different proportions of column materials provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0017] To make the purpose, technical solutions and advantages of the present invention more clearly understood, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless there is a conflict, the embodiments and features in the embodiments of the present application can be combined with each other in any manner.

[0018] As explained in the background above, the wing assembly jig is the most critical positioning element in determining wing assembly quality. However, the jig's columns are made of different materials than the wing product. This leads to thermal deformation mismatches between the jig and the wing product when the factory temperature fluctuates, resulting in assembly stresses that reduce product assembly quality.

[0019] Based on the above problems, the redistribution of column material can be considered in the structural design of the wing assembly jig to ensure that the thermal deformation of the wing assembly jig and the product matches, and to ensure the product assembly accuracy and assembly quality. In response to this design idea, the present invention proposes a method for determining the material distribution of the wing assembly jig columns.

[0020] The present invention provides the following specific embodiments that can be combined with each other. For the same or similar concepts or processes, some embodiments may not be described in detail. The following embodiments of the present invention are further described in detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0021] Figure 1 A flow chart of a method for determining material distribution of a wing assembly frame column provided by an embodiment of the present invention is as follows: Figure 1 As shown, an embodiment of the present invention provides a method for determining the material distribution of a wing assembly frame column, comprising the following steps: Step 1: Determine the structure and components of the wing assembly jig, as well as the geometric dimensions and materials used for each component; Step 2: Based on the structure of the wing assembly jig, two characteristic points of the wing assembly jig are determined, which are distributed as follows: two end points of the expansion plate of the upper beam of the wing assembly jig; Step 3: Based on the geometric dimensions and materials used of each component in the wing assembly jig structure, a finite element calculation model of the wing assembly jig is established. By changing the material distribution in the wing root column and wingtip column, the offset coefficient of each characteristic point in the wing assembly jig under different material distributions is obtained, and the material distribution of the columns of the wing assembly jig is optimized.

[0022] The following describes in detail a specific implementation of the method for determining the material distribution of the wing assembly frame columns provided by an embodiment of the present invention.

[0023] like Figure 1 As shown, the method for determining the material distribution of the wing assembly frame columns provided in the embodiment of the present invention is implemented by the following steps: Step 1: Determine the structure and components of the wing assembly jig, including the upper beam, lower beam, upper beam expansion plate, lower beam expansion plate, slide rail, wing root column and wing tip column, wherein the wing root column, upper beam and wing tip column are sequentially connected to form a gate-shaped frame, one end of the lower beam is fixedly connected to the ground, and its lower end face is placed on a slide rail parallel to the length direction of the lower beam, one end of the upper beam expansion plate is fixedly connected to the end of the upper beam close to the wing root column, and its upper end face is connected in parallel to the upper beam through the slide rail, one end of the lower beam expansion plate is fixedly connected to the end of the lower beam close to the wing root column, and its lower end face is connected in parallel to the lower beam through the slide rail. Figure 2 , which is a schematic diagram of the structure of a wing assembly jig and a schematic diagram of a coordinate system provided by an embodiment of the present invention; Step 2: Based on the structure of the wing assembly jig, determine the geometric dimensions of the upper beam, lower beam, upper and lower beam expansion plates, wing root column and wing tip column in the wing assembly jig, such as Figure 3 FIG. 1 is a diagram showing the structural size distribution of a wing assembly jig provided by an embodiment of the present invention; Step three: Based on the structure of the wing assembly jig, determine the materials used for the assembly jig upper beam, lower beam, upper beam expansion plate, lower beam expansion plate, as well as the initial materials used for the wingtip column and wingroot column.

[0024] In this step, the materials used for the assembly jig's upper and lower beams, upper and lower beam expansion plates, and the initial materials used for the wing root and wingtip columns are confirmed as follows: the upper and lower beams are made of Q235 steel, and the wing root and wingtip columns are initially made of Q235 steel. If the wing product is an aluminum alloy, the upper and lower beam expansion plates are made of 7075 aluminum, and the wing root and wingtip columns are partially replaced with 7075 aluminum. If the wing product is a composite material, the upper and lower beam expansion plates are made of Invar steel, and the wing root and wingtip columns are partially replaced with Invar steel. In this embodiment, the wing product is an aluminum alloy, and the wing root and wingtip columns are partially redistributed with 7075 aluminum.

[0025] Step 4: Based on the wing assembly jig structure, determine two characteristic points of the assembly jig structure, namely, the two end points of the expansion plate of the wing assembly jig upper beam; Step 5: Based on the geometric dimensions and materials of each component in the wing assembly jig structure, a finite element calculation model of the wing assembly jig is established. The initial materials of the wing root and wing tip columns are changed to obtain wing root and wing tip columns with a variety of material distribution combinations. A temperature difference is applied to the wing assembly jigs with various material distributions. Through finite element simulation, the temperature difference of the wing assembly frame under different material distribution combinations is calculated. The displacement caused by the displacement includes the span and heading displacement of the wing assembly jig; the span is the length direction of the wing assembly jig, which is the x direction; the heading is the height direction of the wing assembly jig, which is the y direction, and the proportion of the material used in the wing root column and the wing tip column is changed from 0 to 100%. Based on the working cycle and ambient temperature of the wing assembly jig, the temperature difference applied to the wing assembly jig is =10℃, in this embodiment, the material distribution combination of the wing root column and the wing tip column is changed to 15 groups, such as Figure 4 The figure shows the proportion of different materials in the columns of a wing assembly frame structure provided by an embodiment of the present invention. The black framed part is aluminum, and the rest is steel. The specific proportions are shown in the following table.

[0026] Step 6: Extract the displacements of the span and heading directions of the two wing assembly jig structural feature points from the simulation results in step 5. 、 are the coordinates of the left end point of the upper beam expansion plate in the heading and span directions, 、 They are the heading and spanwise displacement changes of the left end point of the upper beam expansion plate after a temperature difference of 10°C. 、 are the coordinates of the right end point of the upper beam expansion plate in the heading and span directions, 、 They are respectively the heading and spanwise displacement changes of the right end point of the upper beam expansion plate after a temperature difference of 10°C. In this embodiment, the coordinate values ​​and coordinate changes of the end points of the upper beam expansion plate are shown in the following table:

[0027] Step 7: Based on the displacement of the structural characteristic points of the wing assembly jig, the shape characteristic equation and the offset coefficient equation for the positioning of the wing assembly jig are established as follows: ; ; ; in, is the initial shape characteristic between the left end point of the upper beam expansion plate and the right end point of the upper beam expansion plate, is the deformation shape characteristic between the left end point of the upper beam expansion plate and the right end point of the upper beam expansion plate after experiencing a temperature difference of 10°C, is the positioning offset coefficient of the wing assembly jig. The positioning offset coefficient of the wing assembly jig is obtained as:

[0028] Step 8: Based on the wing assembly jig positioning offset coefficient equation, the optimal material distribution of the wing assembly jig column is obtained. The closer the deformation coefficient is to 1, the better the column material distribution is, such as Figure 5 Figure 2 shows the deformation coefficients of the wing assembly jig structure at different column material ratios according to an embodiment of the present invention. It can be seen that the positioning offset coefficient values ​​for groups 3 and 10 are identical to those of the initial shape. This indicates that the optimal material distribution combinations for the wing root and wingtip columns corresponding to the wing assembly jig in this embodiment are: an aluminum ratio of 0.428571 for the root column, with the wingtip column material remaining unchanged, or an aluminum ratio of 0.714286 for the root column and 0.285714 for the wingtip column.

[0029] Although the embodiments disclosed herein are as described above, the contents are merely provided to facilitate understanding of the present invention and are not intended to limit the present invention. Any person skilled in the art may make any modifications and variations in the form and details of the embodiments without departing from the spirit and scope of the present invention. However, the scope of patent protection of the present invention shall remain subject to the scope defined by the appended claims.

Claims

1. A method for determining the material distribution of wing assembly frame columns, characterized in that: The following steps are involved: Step 1: Determine the structure and components of the wing assembly jig, as well as the geometric dimensions and materials used for each component; Step 2: Based on the structure of the wing assembly jig, two characteristic points of the wing assembly jig are determined, which are distributed as follows: two end points of the expansion plate of the upper beam of the wing assembly jig; Step 3: Based on the geometric dimensions and materials used of each component in the wing assembly jig structure, a finite element calculation model of the wing assembly jig is established. By changing the material distribution in the wing root column and wingtip column, the offset coefficient of each characteristic point in the wing assembly jig under different material distributions is obtained, and the material distribution of the columns of the wing assembly jig is optimized.

2. A method for determining the material distribution of wing assembly frame columns according to claim 1, characterized in that: The step 1 comprises: Step 11, determining the structure and components of the wing assembly jig, which include: an upper beam, a lower beam, an upper beam expansion plate, a lower beam expansion plate, a slide rail, a wing root column, and a wing tip column. The structure is as follows: the wing root column, the upper beam, and the wing tip column are sequentially connected to form a gate-shaped frame, one end of the lower beam is fixedly connected to the ground, and its lower end face is placed on a slide rail parallel to the length direction of the lower beam, one end of the upper beam expansion plate is fixedly connected to the end of the upper beam close to the wing root column, and its upper end face is connected parallel to the upper beam via the slide rail, and one end of the lower beam expansion plate is fixedly connected to the end of the lower beam close to the wing root column, and its lower end face is connected parallel to the lower beam via the slide rail. Step 12, based on the structure of the wing assembly jig, determining the geometric dimensions of the upper beam, lower beam, upper beam expansion plate, lower beam expansion plate, wing root column and wing tip column in the wing assembly jig; Step 13, based on the structure of the wing assembly jig, determine the materials used for the upper beam, lower beam, upper beam expansion plate, lower beam expansion plate in the wing assembly jig, as well as the initial materials used for the wing root column and wingtip column.

3. The method for determining the material distribution of a wing assembly frame column according to claim 2, characterized in that: In step 13, the materials used for each component are confirmed as follows: The upper and lower beams are made of Q235 steel, and the wing root and wing tip columns were originally made of Q235 steel. If the wing product is made of aluminum alloy, the upper beam expansion plate and the lower beam expansion plate are 7075 aluminum, and part of the material of the wing root column and the wing tip column is replaced with 7075 aluminum; If the wing product is a composite material, the upper beam expansion plate and the lower beam expansion plate are made of Invar steel, and part of the material of the wing root column and the wingtip column is replaced with Invar steel.

4. The method for determining the material distribution of a wing assembly frame column according to claim 2, wherein: The step 3 includes: Step 31: Based on the geometric dimensions and materials of each component in the wing assembly jig structure, a finite element calculation model of the wing assembly jig is established, and some of the initial materials used in the wing root columns and wingtip columns are changed to obtain wing root columns and wingtip columns with various material distribution combinations. Temperature differences are applied to the wing assembly jigs with various material distributions. Through finite element simulation, the temperature difference of the wing assembly frame under different material distribution combinations is calculated. The displacement caused by the wing assembly jig includes the spanwise displacement and the heading displacement; Step 32, extracting the spanwise displacement and the heading displacement of each characteristic point in the wing assembly jig from the simulation calculation results in step 31; and establishing a shape characteristic equation of the wing assembly jig based on the displacement of each characteristic point of the wing assembly jig; Step 33 , calculating the offset coefficient based on the shape characteristic equation of the wing assembly jig, and obtaining the optimal option of the material distribution combination of the wing root column and the wing tip column in the wing assembly jig.

5. The method for determining the material distribution of a wing assembly frame column according to claim 4, characterized in that: In step 33 , the closer the calculated offset coefficient is to 1, the closer the shape characteristics of the wing assembly jig before and after deformation are, that is, the better the material distribution combination of the corresponding wing root column and wingtip column is.

6. The method for determining the material distribution of a wing assembly frame column according to claim 4, characterized in that: In step 31, the proportion of the initial material used for the wing root column and the wing tip column is changed to 0-100%; In step 31, the temperature difference applied to the wing assembly jig is based on the working cycle and ambient temperature of the wing assembly jig. =10℃.

7. The method for determining the material distribution of a wing assembly frame column according to claim 4, characterized in that: The span direction is the length direction of the wing assembly jig, which is set as the x direction; the heading direction is the height direction of the wing assembly jig, which is set as the y direction; in step 32, 、 are the coordinates of the left end point of the upper beam expansion plate in the heading and span directions, 、 They are respectively the heading displacement and spanwise displacement of the left end point of the upper beam expansion plate after a temperature difference of 10°C. 、 are the coordinates of the right end point of the upper beam expansion plate in the heading and span directions, 、 They are the heading displacement and spanwise displacement of the right end point of the upper beam expansion plate after a temperature difference of 10°C.

8. The method for determining the material distribution of a wing assembly frame column according to claim 7, characterized in that: The shape characteristic equation and offset coefficient for the wing assembly jig positioning established in step 32 are: ； ； ； in, is the initial shape characteristic between the left end point of the upper beam expansion plate and the right end point of the upper beam expansion plate, is the deformation shape characteristic between the left end point of the upper beam expansion plate and the right end point of the upper beam expansion plate after experiencing a temperature difference of 10°C, Locate the offset factor for the wing assembly jig.

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