Airplane stringer multi-combination structural member forming equipment

Abstract

The utility model belongs to the technical field of airplane stringer machining, and particularly relates to airplane stringer multi-combination structural part forming equipment. The airplane stringer forming device comprises a bearing table, an airplane stringer forming part is detachably installed on the bearing table, the bearing table comprises an upper table top, a supporting frame structure and supporting legs, the upper table top is fixedly installed at the top of the supporting frame structure, and the supporting legs are fixedly installed at the bottom of the supporting frame structure. The aircraft stringer forming device comprises three sets of aircraft stringer forming components, forming notches in the aircraft stringer forming components are different, each aircraft stringer forming component comprises a fixed mounting block, a first forming block and a second forming block, and a mounting plate is arranged at the bottom of each fixed mounting block. According to the utility model, various specifications of aircraft stringers can be pressed and formed according to the size and the size of the required aircraft stringers, the process operation problem can be effectively reduced, the difficulty of pressing and forming stringer materials is reduced, and the part manufacturing efficiency is effectively improved.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft stringer processing technology, and relates to a forming equipment for multi-combination structural components of aircraft stringers. Background Technology

[0002] A stringer is a long, strip-shaped structural member in an aircraft used to enhance the strength and rigidity of the fuselage or wing. It is typically installed inside the aircraft skin and tightly connected to it, forming a monolithic structure. Stringers are generally divided into fuselage stringers and wing stringers. Fuselage stringers are usually installed inside the aircraft fuselage, arranged along its length, and primarily help the aircraft withstand various forces during takeoff, landing, and flight. Wing stringers are usually installed inside the aircraft wing, arranged along its length, and primarily help the wing withstand aerodynamic forces, engine thrust, and landing gear reaction forces.

[0003] To ensure that the stringers can be stably installed on the frame, the stringers are generally designed with multiple bends. When processing such stringers, the sheet material usually needs to be pressed multiple times to form the stringers. When using conventional pressing equipment to press the sheet material into stringers, only one pressing point can be pressed on the sheet material at a time. Each different pressing point requires a corresponding pressing machine, which makes the stringer pressing operation both time-consuming and labor-intensive, reducing the pressing efficiency. Utility Model Content

[0004] The purpose of this invention is to address the above-mentioned problems by providing a molding equipment for multi-combination structural components of aircraft stringers.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a multi-combination structural component forming equipment for aircraft stringers, comprising a support platform on which aircraft stringer forming components are detachably mounted. The support platform includes an upper surface, a support frame structure, and support feet. The upper surface is fixedly mounted on the top of the support frame structure, and the support feet are fixedly mounted on the bottom of the support frame structure. The aircraft stringer forming components are arranged in three sets, and the forming grooves on each aircraft stringer forming component are different. Each aircraft stringer forming component includes a fixed mounting block, a first forming block, and a second forming block. An mounting plate is provided at the bottom of the fixed mounting block. The fixed mounting block and the mounting plate are integrally formed. The fixed mounting block is an inverted T-shape. The first forming block and the second forming block are mounted on the fixed mounting block.

[0006] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the upper surface of the bearing platform is provided with a forming component mounting groove, the mounting plate at the bottom of the fixed mounting block is located in the forming component mounting groove, three sets of mounting plates are installed side by side in the forming component mounting groove, and the edges of the mounting plates are fixedly installed by fixing strips.

[0007] In the aforementioned aircraft stringer multi-combination structural component forming equipment, the supporting frame structure includes crossbeams and longitudinal beams. The crossbeams and longitudinal beams have hollow interiors and are welded and fixed to each other.

[0008] In the aforementioned aircraft stringer multi-combination structural component forming equipment, hollow openings are provided on the sides of both the crossbeam and the longitudinal beam, and six sets of support legs are provided, with the support legs fixedly installed in pairs on both sides and in the middle of the crossbeam.

[0009] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the fixed mounting block is provided with a first mounting groove and a second mounting groove on both sides. The first forming block is fixedly installed in the first mounting groove, and the second forming block is fixedly installed in the second mounting groove.

[0010] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the two sides of the support frame structure are provided with fixing mechanisms. The fixing mechanisms include fixing beams and connecting rings. The fixing beams are fixedly installed inside the support frame structure. Connecting ears are fixedly provided on both sides of the fixing beams. The connecting ears are movably connected to the connecting rings through pins.

[0011] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the upper surface of the fixed mounting block is provided with a forming groove, which is composed of a first arc-shaped part and a second arc-shaped part, and the first arc-shaped part and the second arc-shaped part have different structures.

[0012] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the upper surface of the first forming block is provided with a forming groove, and the groove of the first arc-shaped part is flush with the upper forming groove of the first forming block.

[0013] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the upper surface of the second forming block is provided with a forming groove, and the groove of the second arc-shaped part is flush with the upper forming groove of the second forming block.

[0014] In the above-mentioned aircraft stringer multi-combination structural component forming equipment, the first forming block and the second forming block are both composed of two component blocks, and the two component blocks are connected by a connecting plate.

[0015] Compared with existing technologies, the advantages of this utility model are:

[0016] 1. This utility model features an aircraft stringer forming component that is detachably installed on a support platform. The aircraft stringer forming component is provided in three sets, and the forming grooves on each aircraft stringer forming component are different. It can press and form various specifications according to the required size and dimensions of the aircraft stringer, which can effectively reduce process operation problems, reduce the difficulty of pressing and forming the stringer, and effectively improve the manufacturing efficiency of parts.

[0017] 2. The aircraft stringer forming component of this utility model includes a fixed mounting block, a first forming block and a second forming block. The first forming block and the second forming block adopt flexible core molds, which effectively solves the problems of difficult pressure transmission and difficult demolding caused by conventional metal core molds, and improves the internal quality of the parts.

[0018] Other advantages, objectives and features of this invention will be partly apparent from the following description, and partly understood by those skilled in the art through study and practice of this invention. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0020] Figure 2 This is a top view of the structure of this utility model.

[0021] Figure 3 This is a side view of the structure of this utility model.

[0022] Figure 4 This is a schematic diagram of the bottom structure of this utility model.

[0023] Figure 5 This is a utility model Figure 1 Enlarged structural diagram at point A in the middle.

[0024] Figure 6 This is a utility model Figure 4 Enlarged structural diagram at point B.

[0025] In the diagram: 1. Support platform; 2. Upper platform; 3. Support frame structure; 4. Aircraft stringer molding component; 5. Fixed mounting block; 6. Support leg; 7. First molding block; 8. Second molding block; 9. Mounting plate; 10. Component mounting slot; 11. Fixing strip; 12. Crossbeam; 13. Longitudinal beam; 14. First mounting slot; 15. Second mounting slot; 16. Opening; 17. Fixed beam; 18. Connecting ring; 19. Connecting lug; 20. First arc-shaped part; 21. Second arc-shaped part; 22. Connecting plate. Detailed Implementation

[0026] The present invention will be further described below with reference to the accompanying drawings.

[0027] like Figure 1-6As shown, an aircraft stringer multi-assembly structural component forming equipment includes a support platform 1. Aircraft stringer forming components 4 are detachably mounted on the support platform 1. The support platform 1 includes an upper surface 2, a support frame structure 3, and support legs 6. The upper surface 2 is fixedly mounted on the top of the support frame structure 3, and the support legs 6 are fixedly mounted on the bottom of the support frame structure 3. Three sets of aircraft stringer forming components 4 are provided, and the forming grooves on each aircraft stringer forming component 4 are different. Each aircraft stringer forming component 4 includes a fixed mounting block 5, a first forming block 7, and a second forming block 8. A mounting plate 9 is provided at the bottom of the fixed mounting block 5. The fixed mounting block 5 and the mounting plate 9 are integrally formed. The fixed mounting block 5 is an inverted T-shape. The first forming block 7 and the second forming block 8 are mounted on the fixed mounting block 5.

[0028] In this embodiment, the aircraft stringer forming component 4 is provided in three sets, which can be pressed into various specifications according to the required size and dimensions of the aircraft stringer, effectively reducing process operation problems.

[0029] Furthermore, the upper surface of the support platform 1 is provided with a component mounting groove 10, the mounting plate 9 at the bottom of the fixed mounting block 5 is located in the component mounting groove 10, and three sets of mounting plates 9 are installed side by side in the component mounting groove 10. The edges of the mounting plates 9 are fixedly installed by fixing strips 11.

[0030] In this embodiment, the aircraft stringer forming component 4 is easy to disassemble and fix, facilitating later maintenance.

[0031] Furthermore, the supporting frame structure 3 includes a crossbeam 12 and a longitudinal beam 13, the crossbeam 12 and the longitudinal beam 13 having a hollow interior, and the crossbeam 12 and the longitudinal beam 13 being welded and fixed to each other.

[0032] In this embodiment, the crossbeam 12 and the longitudinal beam 13 can improve the strength of the supporting frame structure 3.

[0033] Furthermore, both the crossbeam 12 and the longitudinal beam 13 have hollowed-out openings 16 on their sides, and the support legs 6 are provided in six sets, with each set of support legs 6 fixedly installed in pairs on both sides and in the middle of the crossbeam 12.

[0034] In this embodiment, both the crossbeam 12 and the longitudinal beam 13 have hollowed-out openings 16 on their sides, which can achieve a lightweight design and reduce material consumption.

[0035] Furthermore, the fixed mounting block 5 is provided with a first mounting groove 14 and a second mounting groove 15 on both sides, the first molding block 7 is fixedly installed in the first mounting groove 14, and the second molding block 8 is fixedly installed in the second mounting groove 15.

[0036] In this embodiment, the first molding block 7 and the second molding block 8 are detachably connected to the fixed mounting block 5 to avoid difficulties in demolding and to prevent the quality of the parts from being reduced due to forced demolding.

[0037] Furthermore, the support frame structure 3 is provided with fixing mechanisms on both sides. The fixing mechanisms include fixing beams 17 and connecting rings 18. The fixing beams 17 are fixedly installed inside the support frame structure 3. Connecting ears 19 are fixedly provided on both sides of the fixing beams 17. The connecting ears 19 are movably connected to the connecting rings 18 through pins.

[0038] In this embodiment, the fixing mechanism can prevent the material from deviating during the feeding process, thus preventing a decrease in quality.

[0039] Furthermore, the upper surface of the fixed mounting block 5 is provided with a molding groove, which is composed of a first arc-shaped part 20 and a second arc-shaped part 21, and the structures of the first arc-shaped part 20 and the second arc-shaped part 21 are different.

[0040] Specifically, the upper surface of the first molding block 7 is provided with a molding groove, the groove of the first arc-shaped part 20 is flush with the upper molding groove of the first molding block 7, the upper surface of the second molding block 8 is provided with a molding groove, and the groove of the second arc-shaped part 21 is flush with the upper molding groove of the second molding block 8.

[0041] In this embodiment, the first arc-shaped portion 20 and the second arc-shaped portion 21 can be used together with the first molding block 7 and the second molding block 8 as molding surfaces, which can ensure the flatness of the processing surface, reduce internal and external manufacturing defects, and improve the part qualification rate.

[0042] Furthermore, both the first molding block 7 and the second molding block 8 are composed of two sets of molding blocks, and the two sets of molding blocks are connected by a connecting plate 22, which makes installation convenient.

[0043] The working principle of this utility model is as follows:

[0044] This invention installs the forming equipment below the hydraulic press. The support platform 1 can be fixed by the fixing mechanism. The metal parts to be pressed are placed on the upper platform 2. The machine presses the required stringers on the aircraft stringer forming parts 4. There are three sets of aircraft stringer forming parts 4, and the forming grooves on each aircraft stringer forming part 4 are different. Various specifications can be pressed and formed according to the required size and dimensions of the aircraft stringer. This can effectively reduce process operation problems, reduce the difficulty of pressing and forming the stringers, and effectively improve the parts manufacturing efficiency.

[0045] The aircraft stringer forming component 4 includes a fixed mounting block 5, a first forming block 7, and a second forming block 8. The first forming block 7 and the second forming block 8 adopt flexible core molds, which effectively solves the problems of pressure transmission difficulties and demolding difficulties caused by conventional metal core molds, and improves the internal quality of the parts.

[0046] The specific embodiments described herein are merely illustrative examples illustrating the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications or additions to the described specific embodiments or use similar methods to replace them, without departing from the spirit of this utility model.

[0047] Although this document frequently uses terms such as 1. support platform; 2. upper platform; 3. supporting frame structure; 4. aircraft stringer molding component; 5. fixed mounting block; 6. support foot; 7. first molding block; 8. second molding block; 9. mounting plate; 10. component mounting groove; 11. fixing strip; 12. crossbeam; 13. longitudinal beam; 14. first mounting groove; 15. second mounting groove; 16. opening; 17. fixing beam; 18. connecting ring; 19. connecting ear; 20. first arc-shaped part; 21. second arc-shaped part; 22. connecting plate, the possibility of using other terms is not excluded. The use of these terms is merely for the convenience of describing and explaining the essence of this utility model; interpreting them as any additional limitation would contradict the spirit of this utility model.

Claims

1. An aircraft longeron multi-composite structure forming apparatus comprising a support table (1), characterized in that, The aircraft longeron forming part (4) is detachably mounted on the bearing table (1), the bearing table (1) comprises an upper table (2), a supporting frame structure (3) and supporting feet (6), the upper table (2) is fixedly mounted on the top of the supporting frame structure (3), the supporting feet (6) are fixedly mounted on the bottom of the supporting frame structure (3), the aircraft longeron forming part (4) is provided with three groups, and the forming notches on each aircraft longeron forming part (4) are different, the aircraft longeron forming part (4) comprises a fixed mounting block (5), a first forming block (7) and a second forming block (8), the bottom of the fixed mounting block (5) is provided with a mounting plate (9), the fixed mounting block (5) is integrally formed with the mounting plate (9), the fixed mounting block (5) is an inverted T-shaped, the first forming block (7) and the second forming block (8) are mounted on the fixed mounting block (5).

2. The aircraft stringer multi-composite structure forming apparatus of claim 1, wherein, The upper surface of the bearing table (1) is provided with a part mounting groove (10), the mounting plate (9) at the bottom of the fixed mounting block (5) is located in the part mounting groove (10), three groups of mounting plates (9) are installed side by side in the part mounting groove (10), and the edges of the mounting plates (9) are fixedly installed through fixing strips (11).

3. The aircraft stringer multi-composite structure forming apparatus of claim 2, wherein, The supporting frame structure (3) comprises a cross beam (12) and a longitudinal beam (13), the cross beam (12) and the longitudinal beam (13) are hollow structures, and the cross beam (12) and the longitudinal beam (13) are fixedly welded with each other.

4. The aircraft stringer multi-composite structure forming apparatus of claim 3, wherein, The side surfaces of the cross beam (12) and the longitudinal beam (13) are provided with hollow openings (16), the supporting feet (6) are provided with six groups, and the supporting feet (6) are fixedly installed at the positions on both sides and in the middle of the cross beam (12) respectively.

5. The aircraft stringer multi-composite structure forming apparatus of claim 4, wherein, The two sides of the fixed mounting block (5) are provided with a first mounting groove (14) and a second mounting groove (15), the first forming block (7) is fixedly installed in the first mounting groove (14), and the second forming block (8) is fixedly installed in the second mounting groove (15).

6. The aircraft stringer multi-composite structure forming apparatus of claim 5, wherein, The two sides of the supporting frame structure (3) are provided with a fixing mechanism, the fixing mechanism comprises a fixing beam (17) and a connecting ring (18), the fixing beam (17) is fixedly installed in the inside of the supporting frame structure (3), connecting ears (19) are fixedly arranged on the two sides of the fixing beam (17), and the connecting ears (19) are movably connected with the connecting ring (18) through a pin shaft.

7. The aircraft stringer multi-composite structure forming apparatus of claim 6, wherein, The upper surface of the fixed mounting block (5) is provided with a forming notch, the forming notch is composed of a first arc-shaped part (20) and a second arc-shaped part (21), and the structures of the first arc-shaped part (20) and the second arc-shaped part (21) are different.

8. The aircraft stringer multi-composite structure forming apparatus of claim 7, wherein, The upper surface of the first forming block (7) is provided with a forming notch, the notch of the first arc-shaped part (20) is flush with the upper forming notch of the first forming block (7).

9. The aircraft stringer multi-composite structure forming apparatus of claim 8, wherein, The upper surface of the second forming block (8) is provided with a forming notch, the notch of the second arc-shaped part (21) is flush with the upper forming notch of the second forming block (8).

10. The aircraft stringer multi-composite structure forming apparatus of claim 9, wherein, The first forming block (7) and the second forming block (8) are both combined by two groups of forming blocks, and the two groups of forming blocks are connected through a connecting plate (22).

Images