A large-scale discrete aircraft tooling ground two-way thermal expansion compensation equipment and method

Abstract

The present invention discloses a large-scale discrete aircraft tooling ground two-way thermal expansion compensation equipment and method. The equipment includes four support plates, two transition plates, multiple bottom plates, a first expansion plate, a second expansion plate, a transverse slide rail, a longitudinal slide rail, and a foundation; the compensation structure is arranged according to the structural characteristics of the aircraft tooling, and a large-scale discrete aircraft tooling is arranged on the upper surface of the support plate of the compensation structure. The present application utilizes the method of releasing expansion by a double-layer unidirectional linear guide rail, and uses a local hard connection structure as a stable reference area, solving the problem of thermal expansion difference caused by inconsistent materials of the tooling structure arranged on a large area of the ground, and having general applicability to the development of large-size and high-precision discrete tooling and its product assembly.

Description

Technical Field

[0001] This application relates to the technical field of aircraft assembly, in particular to a ground two-way thermal expansion compensation device and method for large discrete aircraft tooling. Background Art

[0002] Large process equipment (referred to as tooling), especially aircraft assembly process equipment, generally uses a steel structure, and its supporting foundation generally uses a reinforced concrete structure. In aircraft production, the processing and assembly objects are generally made of materials such as aluminum alloy, composite materials, and titanium alloy. It is difficult to control the temperature in the production space of the factory building, especially in a large-sized aircraft assembly workshop with a large dimensional space. Due to the different expansion length changes caused by temperature changes between the object product and the process equipment, errors occur in the processing and assembly of products at different temperatures, directly affecting the instability of the accuracy and quality of the processed and assembled object products. This instability of accuracy and quality will directly lead to the matching, connection, and stress of the downstream related structures, directly affecting the quality of aircraft products.

[0003] Currently, to solve the problems of aircraft assembly process equipment and the assembled aircraft products, methods such as single-direction thermal expansion plates, materials with overall consistency, and coordinated standard workpieces are mainly used. Due to the problem of large system manufacturing costs, it is difficult for large assembly process equipment to be adapted with the same materials for object products such as composite materials and titanium alloys. However, the problem of accuracy differences affected by temperature thermal expansion is also a problem that must be solved.

[0004] One type of process equipment is a discrete structure supported on the foundation. The pillars of this type of process equipment are distributed pointwise on the upper surface of the process equipment foundation. For this type of tooling, the foundation is its positioning and measurement reference. For this type of structure with a relatively small width, generally, single-direction expansion materials can be used to solve the problem. However, for this type of structure with a width dimension exceeding 10 m, the two-way thermal expansion of the ground is a problem that must be solved. Based on this problem, there is an urgent need to find a low-cost ground two-way compensation method to support the development of the assembly process equipment for large aircraft products and the assembly measurement of aircraft products. Summary of the Invention

[0005] The purpose of this application is to provide a ground two-way thermal expansion compensation device and method for large discrete aircraft tooling, which are suitable for the two-way thermal expansion compensation of large discrete aircraft assembly process equipment supported on the ground and similar situations.

[0006] To achieve the above objectives, the following technical solutions are adopted in this application:

[0007] A ground two-way thermal expansion compensation device for a large discrete aircraft tooling, comprising four support plates, two transition plates, multiple bottom plates, a first expansion plate, a second expansion plate, a transverse slide rail, a longitudinal slide rail, and a foundation; the foundation is an integral reinforced concrete structure, arranged below the ground plane, and its upper surface is flush with the ground plane. The upper surface of the foundation is provided with transverse grooves and longitudinal grooves arranged in a grid-like and staggered manner. The transverse grooves and longitudinal grooves are perpendicular to each other and have a consistent interval. Multiple bottom plates are fixed at the bottoms of the openings of the transverse grooves and longitudinal grooves. The multiple bottom plates are connected and fixed into an integral plate-like structure. Multiple transverse slide rails are laid on the upper surfaces of the bottom plates in all the transverse grooves. The first expansion plate and the second expansion plate have the same structure as the bottom plate structure connected into an integral body. The first expansion plate is connected to the multiple transverse slide rails through sliders. The transverse end of the first expansion plate is fixed on the bottom plate through a transition plate. Multiple longitudinal slide rails are laid on the upper surfaces of the first expansion plates in all the longitudinal grooves. The second expansion plate is connected to the multiple longitudinal slide rails through sliders. The longitudinal middle part of the second expansion plate is fixed on the first expansion plate through a transition plate. The support plates are arranged on the upper surfaces of the four corners of the second expansion plate, and the large discrete aircraft tooling is placed on the support plates.

[0008] Further, the multiple bottom plates are connected through lug structures arranged on the side surfaces of the bottom plates, and the connection structure cannot protrude from the upper surface of the bottom plates.

[0009] Further, the materials of the transition plates, the first expansion plate, and the second expansion plate are the same as those of the aircraft products.

[0010] A method for compensation using a ground two-way thermal expansion compensation device for a large discrete aircraft tooling includes the following steps:

[0011] 1. Arrange the compensation structure according to the structural characteristics of a ground two-way thermal expansion compensation method for a large discrete aircraft tooling, and place the large discrete aircraft tooling on the upper surface of the support plates of the compensation structure;

[0012] 2. Arrange structural global measurement reference points on the upper surface of the support plates or on the fixed large discrete aircraft tooling on the upper surface of the support plates;

[0013] 3. Respectively take the middle positions of the transverse and longitudinal transition plates as the X and Y starting hard references, and take the upper surface of the support plates as the Z-direction hard reference to establish an initial global coordinate system;

[0014] 4. The first expansion plate and the second expansion plate expand and extend from the hard references of the transverse and longitudinal transition plates to both ends. Take the thermal expansion coefficients of their materials as the X and Y expansion compensation coefficients, and take the material temperature of the second expansion plate as the basis for X and Y non-linear expansion compensation temperature;

[0015] 5. Arrange a global measurement reference point system with enveloping and continuity on the first expansion plate, support plate, and large discrete aircraft tooling, construct a global coordinate system based on this reference point system, and assign coordinates to the measurement points;

[0016] 6. Establish a local coordinate system by selecting more than 3 reference points as common points in the longitudinal direction of the transition plates in the transverse and longitudinal directions, and measure the large discrete aircraft tooling and its assembled object products.

[0017] Furthermore, the material temperature of the second expansion plate refers to the measured material temperature on the upper surface of the second expansion plate at both ends of the transverse and longitudinal transition plates.

[0018] The advantage of this application lies in the method of releasing expansion using a double-layer unidirectional linear guide rail, using a local hard connection structure as a stable reference area, solving the problem of thermal expansion differences caused by inconsistent materials of the large-area ground layout tooling structure, and having general applicability to the development of large-size high-precision discrete tooling and its product assembly.

[0019] The following further describes this application in detail with reference to the accompanying drawings and embodiments. Description of the Drawings

[0020] Figure 1 Structural schematic diagram of a ground two-way thermal expansion compensation method for a large discrete aircraft tooling;

[0021] Figure 2 Longitudinal cross-sectional schematic diagram of the compensation structure;

[0022] Figure 3 Longitudinal compensation schematic diagram;

[0023] Figure 4 Transverse compensation schematic diagram.

[0024] Explanation of the numbers in the figure: 1. Large discrete aircraft tooling; 2. Local coordinate system; 3. Support plate; 4. Transition plate; 5. Base plate; 6. First expansion plate; 7. Second expansion plate; 8. Transverse slide rail; 9. Longitudinal slide rail; 10. Foundation; 11. Transverse groove; 12. Longitudinal groove; 13. Global measurement reference point; 14. Initial global coordinate system; 15. Global measurement reference point system; 16. Global coordinate system. Detailed Implementation Manner

[0025] Refer to Figures 1 to 4 , in aircraft manufacturing, there are some large discrete aircraft toolings 1. Due to the limitation of the passage of ground transportation vehicles, such toolings can only be arranged on both sides of the vehicle passage. At the same time, due to product obstacles in the middle position, their measurement can only use a local coordinate system 2, and the thermal expansion of large-size toolings has a greater impact on product assembly and measurement accuracy.

[0026] A ground two-way thermal expansion compensation equipment for large discrete aircraft tooling is mainly used for the two-way assembly compensation of the tooling to the product for large discrete aircraft tooling 1 with large length and width dimensions, including four support plates 3, two transition plates 4, multiple bottom plates 5, a first expansion plate 6, a second expansion plate 7, a transverse slide rail 8, a longitudinal slide rail 9, and a foundation 10; the foundation 10 is an integral reinforced concrete structure, arranged below the ground plane, and its upper surface is flush with the ground plane. The upper surface of the foundation 10 is provided with transverse grooves 11 and longitudinal grooves 12 arranged in a grid-like and staggered manner. The transverse grooves 11 and the longitudinal grooves 12 are perpendicular to each other and have a consistent interval. Multiple bottom plates 5 are fixed at the bottom of the openings of the transverse grooves 11 and the longitudinal grooves 12. Multiple bottom plates 5 are connected and fixed to form an integral plate-like structure. Multiple transverse slide rails 8 are laid on the upper surface of the inner bottom plates of all the transverse grooves 11. The first expansion plate 6 and the second expansion plate 7 have the same structure as the bottom plates 5 connected into a whole. The first expansion plate 6 is connected to multiple transverse slide rails 8 through sliders. The transverse end of the first expansion plate 6 is fixed on the bottom plate 5 through the transition plate 4. Multiple longitudinal slide rails 9 are laid on the upper surface of the first expansion plate 6 in all the longitudinal grooves 12. The second expansion plate 7 is connected to multiple longitudinal slide rails 9 through sliders. The longitudinal middle part of the second expansion plate 7 is fixed on the first expansion plate 6 through the transition plate 4. The support plates 3 are arranged on the upper surfaces of the four corners of the second expansion plate 7, and the large discrete aircraft tooling 1 is placed on the support plates 3.

[0027] Multiple bottom plates 5 are connected through lug structures arranged on the side surfaces of the bottom plates 5, and the connection structure cannot protrude from the upper surface of the bottom plates 5.

[0028] The materials of the transition plate 4, the first expansion plate 6, and the second expansion plate 7 are the same as those of the aircraft product.

[0029] A method for compensation using a ground two-way thermal expansion compensation equipment for large discrete aircraft tooling includes the following steps:

[0030] 1. Arrange the compensation structure according to the structural characteristics of a ground two-way thermal expansion compensation method for large discrete aircraft tooling, and set the large discrete aircraft tooling 1 on the upper surface of the support plate 3 of the compensation structure;

[0031] 2. Arrange the structural global measurement reference points 13 on the upper surface of the support plate 3 or on the large discrete aircraft tooling 1 fixed on the upper surface of the support plate 3;

[0032] 3. Respectively take the middle positions of the transverse and longitudinal transition plates 4 as the X and Y starting hard references, and take the upper surface of the support plate 3 as the Z-direction hard reference to establish the initial global coordinate system 14;

[0033] 4. The first expansion plate 6 and the second expansion plate 7 expand and extend towards both ends starting from the hard reference of the transverse and longitudinal transition plate 4. The material thermal expansion coefficients of the first expansion plate 6 and the second expansion plate 7 are used as the X and Y expansion compensation coefficients, and the material temperature of the second expansion plate 7 is used as the basis for the X and Y non-linear expansion compensation temperature;

[0034] 5. A global measurement reference point system 15 with envelopability and continuity is arranged on the first expansion plate 6, the support plate 3, and the large discrete aircraft tooling 1. Based on this reference point system, a global coordinate system 16 is constructed, and all measurement point coordinates are assigned values;

[0035] 6. A local coordinate system 2 is established by selecting more than 3 reference points as common points in the longitudinal direction of the transverse and longitudinal transition plate 4, and the large discrete aircraft tooling 1 and its assembled object product are measured.

[0036] The material temperature of the second expansion plate 7 refers to the measured material temperature on the upper surface of the second expansion plate 7 at both ends of the transverse and longitudinal transition plate 4.

Claims

1. A large-scale discrete aircraft tooling ground two-way thermal expansion compensation equipment, characterized in that It includes four support plates, two transition plates, multiple base plates, a first expansion plate, a second expansion plate, a transverse slide rail, a longitudinal slide rail, and a foundation; the materials of the transition plates, the first expansion plate, and the second expansion plate are the same as those of the aircraft product. The foundation is an integral reinforced concrete structure, which is set below the ground plane, and its upper surface is flush with the ground plane. The upper surface of the foundation is provided with transverse grooves and longitudinal grooves arranged in a grid-like and staggered manner. The transverse grooves and the longitudinal grooves are perpendicular to each other and have a consistent interval. Multiple base plates are fixed at the bottoms of the openings of the transverse grooves and the longitudinal grooves. The multiple base plates are connected and fixed to form an integral plate-like structure. Multiple transverse slide rails are laid on the upper surfaces of the base plates in all the transverse grooves. The first expansion plate and the second expansion plate have the same structure as the integral base plate structure. The first expansion plate is connected to the multiple transverse slide rails through sliders. The transverse end of the first expansion plate is fixed to the base plate through a transition plate. Multiple longitudinal slide rails are laid on the upper surfaces of the first expansion plates in all the longitudinal grooves. The second expansion plate is connected to the multiple longitudinal slide rails through sliders. The longitudinal middle part of the second expansion plate is fixed to the first expansion plate through a transition plate. The support plates are arranged on the upper surfaces of the four corners of the second expansion plate, and the large discrete aircraft tooling is placed on the support plates.

2. The large-scale discrete aircraft tooling ground two-way thermal expansion compensation equipment according to claim 1, characterized in that The multiple base plates are connected through lug structures arranged on the side surfaces of the base plates, and the connection structure cannot protrude from the upper surface of the base plates.

3. A method for compensation using the large-scale discrete aircraft tooling ground two-way thermal expansion compensation equipment according to claim 1, characterized in that It includes the following steps: 3-1 Arrange the compensation structure according to the structural characteristics of a ground two-way thermal expansion compensation device for a large discrete aircraft tooling, and set the large discrete aircraft tooling on the upper surface of the support plate of the compensation structure; 3-2 Arrange the global measurement reference points of the structure on the large discrete aircraft tooling fixed on the upper surface of the support plate; 3-3 Respectively take the middle positions of the transverse and longitudinal transition plates as the X and Y starting hard references, and take the upper surface of the support plate as the Z-direction hard reference to establish the initial global coordinate system; 3-4 The first expansion plate and the second expansion plate expand and extend towards both ends starting from the hard references of the transverse and longitudinal transition plates. Take the thermal expansion coefficients of their materials as the X and Y expansion compensation coefficients, and take the material temperature of the second expansion plate as the basis for the X and Y non-linear expansion compensation temperature; 3-5 Arrange a global measurement reference point system with envelopability and continuity on the first expansion plate, the support plate, and the large discrete aircraft tooling, construct the global coordinate system based on this reference point system, and assign values to the coordinates of the measurement points; 3-6 Establish a local coordinate system that includes more than 3 reference points selected from the long directions of the transverse and longitudinal transition plates as common points, and measure the large discrete aircraft tooling and its assembled object products.

4. The method for compensation using the large-scale discrete aircraft tooling ground two-way thermal expansion compensation equipment according to claim 3, characterized in that The material temperature of the second expansion plate mentioned refers to the measured material temperature on the upper surface of the second expansion plate at the two end positions of the transverse and longitudinal transition plates.

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