Aircraft wing leading edge component preassembling and hole forming tool

Abstract

The utility model relates to an aircraft wing leading edge component preassembling and drilling tool which comprises a framework, a positioning support, a product positioning beam, a lifting assembly and a drilling sample plate, the product positioning beam is fixed to the top of the framework through the positioning support, and an aircraft wing leading edge component is arranged at the top of the product positioning beam. A step surrounding the aircraft wing leading edge component is arranged on the top face of the product positioning beam, the shape of the step is consistent with the aerodynamic shape of the aircraft wing leading edge component, an assembly gap is formed between the step and the aircraft wing leading edge component, and the drilling sample plate is arranged on the product positioning beam on the outer side of the step. The aircraft wing leading edge component and the drilling sample plate are detachably connected with the step, and the lifting assembly is arranged at the bottom of the framework. The utility model has the beneficial effects that various assembly technical parameters can be conveniently repaired and evaluated to reach the standard, and then holes can be formed, so that the problems of poor matching between the wing leading edge component and the wing main body component and high product rejection rate are solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft assembly, and in particular relates to a pre-assembly and hole-making tool for aircraft wing leading edge components. Background Art

[0002] Assembly is a crucial process in the aircraft manufacturing industry, and aircraft wings are among the most challenging large components to manufacture. Aircraft wings require high precision, high strength, high rigidity, long life, and fatigue resistance. These requirements pose significant challenges to wing assembly technology, and any assembly error will directly impact the aircraft's flight performance and safety.

[0003] Aircraft wing leading edges are typically manufactured using composite material molding. Because composite materials are typically cured at high temperatures, the thermal expansion coefficients of composite tooling materials and the final product differ. Furthermore, the wing leading edge's typically V-shaped structure can cause springback after molding. Consequently, the actual dimensions and shape of the final product after molding and bonding can differ significantly from the theoretical dimensions. Therefore, directly machining and drilling the wing leading edge according to the theoretical dimensions can lead to poor compatibility between the wing leading edge and the main wing component, potentially preventing assembly. This can result in a high scrap rate and failure to meet manufacturing requirements. Utility Model Content

[0004] The purpose of the utility model is to overcome the shortcomings of the existing technology and provide a pre-assembly and hole-making tool for the leading edge components of an aircraft wing, which can facilitate the hole-making after the various assembly technical parameters are repaired and evaluated to meet the standards, thereby solving the problems of poor matching between the leading edge components of the wing and the main wing components and the high product scrap rate.

[0005] The purpose of this utility model is achieved through the following technical solutions:

[0006] A pre-assembly and hole-making tool for aircraft wing leading edge components, comprising a frame, a positioning support, a product positioning beam, a lifting assembly, and a drilling template. The product positioning beam is fixed to the top of the frame through the positioning support. The aircraft wing leading edge component is arranged on the top of the product positioning beam. The top surface of the product positioning beam is provided with a step surrounding the aircraft wing leading edge component. The shape of the step is consistent with the aerodynamic shape of the aircraft wing leading edge component, and an assembly gap is provided between the step and the aircraft wing leading edge component. The drilling template is provided on the product positioning beam outside the step. The aircraft wing leading edge component and the drilling template are both detachably connected to the step. The lifting assembly is provided at the bottom of the frame.

[0007] Furthermore, the width of the assembly gap between the aircraft wing leading edge component and the step is 1.5 mm.

[0008] Furthermore, the skeleton includes a supporting base frame and a supporting stand frame. The supporting stand frame is arranged in the middle of the supporting base frame, and the product positioning beam is fixed to the top of the supporting stand frame through a positioning support.

[0009] Furthermore, the lifting assembly includes four lifting columns, which are fixed on the supporting base frame, and the tops of the lifting columns are provided with lifting rings.

[0010] Furthermore, the supporting base is provided with reference blocks for establishing a measurement coordinate system, four reference blocks are provided and three of the reference blocks are provided with inspection reference holes.

[0011] Furthermore, the step is provided with four fine threaded holes for positioning the aircraft wing leading edge component and the drilling template.

[0012] Furthermore, a plurality of rivet mounting holes for drilling holes in the leading edge components of the aircraft wing are provided on the step and the drilling template, and the rivet mounting holes on the step and the drilling template correspond one to one.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] 1. The utility model can adjust and evaluate various assembly technical parameters, so that holes can be made only after the various assembly technical parameters between the aircraft wing leading edge component and the product positioning beam meet the standards, which greatly improves the matching and accuracy between the aircraft wing leading edge component and the wing main body component and reduces the scrap rate of the product.

[0015] 2. The present invention sets up an inspection benchmark. After the aircraft wing leading edge component and the product positioning beam are finally assembled, the measuring equipment can establish a measurement coordinate system through the inspection benchmark, and then directly inspect various parameter indicators of the aerodynamic shape of the aircraft wing leading edge component.

[0016] 3. The utility model has a simple overall structure, convenient operation, and low manufacturing cost. The product positioning beam is a detachable replacement part and can be applied to the leading edge components of aircraft wings with different structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the overall structure of the pre-installation and hole-making tooling in the present invention;

[0018] Figure 2 for Figure 1 A schematic diagram of the structure enlargement at point A;

[0019] Figure 3 for Figure 1 A magnified schematic diagram of the structure at point B in FIG;

[0020] Figure 4 This is a schematic diagram of the assembly of the aircraft wing leading edge component in the present invention.

[0021] In the figure: 1. Positioning support; 2. Product positioning beam; 3. Drilling template; 4. Step; 5. Support base; 6. Support frame; 7. Lifting column; 8. Lifting ring; 9. Reference block; 10. Inspection reference hole; 11. Fine threaded hole; 12. Rivet mounting hole. DETAILED DESCRIPTION

[0022] The present invention will be further described below in conjunction with the accompanying drawings, but the protection scope of the present invention is not limited to the following description.

[0023] like Figure 1-Figure 3 As shown, a tool for pre-assembling and drilling holes in aircraft wing leading edge components comprises a frame, a positioning support 1, a product positioning beam 2, a lifting assembly, and a drilling template 3. The product positioning beam 2 is fixed to the top of the frame via the positioning support 1. When drilling holes in the aircraft wing leading edge component, the aircraft wing leading edge component is assembled on top of the product positioning beam 2, thereby simulating the actual installation state of the aircraft wing leading edge component. The drilling template 3 is used for drilling holes after the aircraft wing leading edge component is assembled on the product positioning beam 2. The lifting assembly is used to lift and transport the entire tool.

[0024] like Figure 1 As shown, the skeleton includes a support base 5 and a support stand 6, which is fixed to the middle of the support base 5. The product positioning beam 2 is fixed to the top of the support stand 6 via a positioning support 1. The positioning support 1 is connected to the product positioning beam 2 and the support stand 6 via bolts, making the product positioning beam 2 a detachable and replaceable component suitable for aircraft wing leading edge components of different structures. The lifting assembly is located at the bottom of the skeleton and includes four lifting columns 7, which are fixed to the support base 5 via bolts. The lifting columns 7 are fixed with lifting rings 8 on the top.

[0025] like Figure 1 、 Figure 2 As shown, a step 4 is integrally formed on the top surface of the product positioning beam 2. The shape of the step 4 is consistent with the aerodynamic shape of the aircraft wing leading edge component. When the aircraft wing leading edge component is assembled on the product positioning beam 2, the step 4 surrounds the aircraft wing leading edge component, and an assembly gap is provided between the step 4 and the aircraft wing leading edge component. After the aircraft wing leading edge component is assembled, by testing whether the assembly gap between the aircraft wing leading edge component and the step 4 meets the assembly technical requirements, it can be determined whether the shape allowance of the aircraft wing leading edge component needs to be adjusted. At the same time, it is also necessary to test whether the step difference between the aircraft wing leading edge component and the step 4 meets the assembly technical requirements. In this embodiment, the assembly technical requirements between the aircraft wing leading edge component and the step 4 include an assembly gap width of 1.5mm and a step difference of ±0.1mm.

[0026] like Figure 2 、 Figure 3As shown, the drilling template 3 is mounted on the product positioning beam 2 outside the step 4, and both the aircraft wing leading edge component and the drilling template 3 are detachably connected to the step 4. Specifically, the step 4 is provided with fine threaded holes 11 for positioning the aircraft wing leading edge component and the drilling template 3. In this embodiment, four fine threaded holes 11 are provided. In addition, both the step 4 and the drilling template 3 are provided with multiple rivet mounting holes 12 for drilling holes in the aircraft wing leading edge component. The rivet mounting holes 12 on the step 4 and the drilling template 3 correspond one-to-one.

[0027] like Figure 1 As shown, a reference block 9 is also fixed on the supporting base frame 5. In this embodiment, four reference blocks 9 are provided, and three of the reference blocks 9 are provided with inspection reference holes 10. Through the arrangement of the reference blocks 9 and the inspection reference holes 10, it is possible to establish a measurement coordinate system for the leading edge component of the aircraft wing after it is positioned on the product positioning beam 2, and then directly inspect various parameter indicators of the aerodynamic shape of the leading edge component of the aircraft wing.

[0028] The assembly of the aircraft wing leading edge component on the pre-assembly and hole-making tool of the utility model is as follows Figure 4 As shown, the specific assembly and hole making steps are as follows:

[0029] The first step is to pre-machine four positioning holes corresponding to the fine threaded holes 11 on the aircraft wing leading edge component, install the aircraft wing leading edge component on the product positioning beam 2, make the positioning holes correspond to the fine threaded holes 11, and then use positioning screws to connect the positioning holes and the fine threaded holes 11, thereby realizing the positioning and fixation of the aircraft wing leading edge component on the product positioning beam 2; then use a feeler gauge to check whether the assembly clearance between the aircraft wing leading edge component and the step 4 meets the assembly technical requirement of 1.5mm, if not, the outer shape allowance of the aircraft wing leading edge component is repaired until the repair meets the standard; after the repair meets the standard, use a feeler gauge to place it flat on the aerodynamic shape of the aircraft wing leading edge component, measure the step difference between the aircraft wing leading edge component and the step 4, and then evaluate whether the aircraft wing leading edge component meets the assembly technical requirements based on the measured parameters.

[0030] In the second step, if all the assembly technical parameters of the aircraft wing leading edge component meet the standards in the first step, the positioning screws are removed, and then the drilling template 3 is pressed against the aircraft wing leading edge component, and the aircraft wing leading edge component and the drilling template 3 are positioned and fixed on the product positioning beam 2 again by the positioning screws; after confirming that the assembly status is correct, the aircraft wing leading edge component is drilled through the rivet mounting holes 12 on the drilling template 3 and the step 4.

[0031] In the third step, the aircraft wing leading edge component is completely riveted to the product positioning beam 2 through the cooperation of rivets and rivet mounting holes 12, and then a measuring coordinate system is established through the inspection reference hole 10 on the reference block 9 using a measuring device to measure the aerodynamic shape of the aircraft wing leading edge component, and based on the measured data, it is evaluated whether the aerodynamic shape of the aircraft wing leading edge component meets the assembly technical requirements.

[0032] Based on the structure of the above-mentioned aircraft wing leading edge component pre-assembly and hole-making tooling and the specific assembly and hole-making steps, the utility model can repair and evaluate various assembly technical parameters, so that the holes can be made only after the various assembly technical parameters between the aircraft wing leading edge component and the product positioning beam 2 meet the standards, which greatly improves the matching and accuracy of the aircraft wing leading edge component and the wing main body component and reduces the scrap rate of the product.

[0033] Finally, although the above description has shown and described the embodiments of the present invention, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A pre-assembly and hole-making tool for aircraft wing leading edge components, characterized by: The invention comprises a skeleton, a positioning support (1), a product positioning beam (2), a lifting assembly, and a drilling template (3); the product positioning beam (2) is fixed to the top of the skeleton through the positioning support (1); the aircraft wing leading edge component is arranged on the top of the product positioning beam (2); a step (4) surrounding the aircraft wing leading edge component is provided on the top surface of the product positioning beam (2); the shape of the step (4) is consistent with the aerodynamic shape of the aircraft wing leading edge component, and an assembly gap is provided between the step (4) and the aircraft wing leading edge component; the drilling template (3) is arranged on the product positioning beam (2) outside the step (4); the aircraft wing leading edge component and the drilling template (3) are both detachably connected to the step (4); and the lifting assembly is arranged at the bottom of the skeleton.

2. The aircraft wing leading edge component pre-assembly and hole-making tool according to claim 1, characterized in that: The width of the assembly gap between the aircraft wing leading edge component and the step (4) is 1.5 mm.

3. The aircraft wing leading edge component pre-assembly and hole-making tool according to claim 1, characterized in that: The skeleton comprises a supporting base frame (5) and a supporting stand frame (6), wherein the supporting stand frame (6) is arranged in the middle of the supporting base frame (5), and the product positioning beam (2) is fixed to the top of the supporting stand frame (6) through a positioning support (1).

4. The aircraft wing leading edge component pre-assembly and hole-making tool according to claim 3, characterized in that: The lifting assembly comprises four lifting columns (7), the lifting columns (7) are fixed on the supporting base frame (5), and the tops of the lifting columns (7) are provided with lifting rings (8).

5. The aircraft wing leading edge component pre-assembly and hole-making tool according to claim 3, characterized in that: A reference block (9) for establishing a measurement coordinate system is provided on the supporting base frame (5), four reference blocks (9) are provided, and three of the reference blocks (9) are provided with inspection reference holes (10).

6. The aircraft wing leading edge component pre-assembly and hole-making tool according to claim 1, characterized in that: The step (4) is provided with fine threaded holes (11) for positioning the aircraft wing leading edge component and the drilling template (3), and there are four fine threaded holes (11).

7. The aircraft wing leading edge component pre-assembly and hole-making tool according to claim 1, characterized in that: The step (4) and the drilling template (3) are both provided with a plurality of rivet mounting holes (12) for drilling holes in the leading edge components of an aircraft wing, and the rivet mounting holes (12) on the step (4) and the drilling template (3) correspond one to one.

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