Jig and manufacturing method for bonding and riveting of aircraft composite components

Abstract

The present invention relates to a bonding and riveting tooling for aerospace composite components and a manufacturing method thereof. The aerospace composite components have the characteristics of a narrow and long structure. The existing tooling has different materials and expansion coefficients from those of the composite products. When the temperature changes, different dimensional changes will occur between the tooling and the composite products, with a certain difference. In view of these deficiencies, the present invention provides a bonding and riveting tooling for aerospace composite components and a manufacturing method thereof, which mainly consists of a shaft pin positioning component, a pressing and positioning component, a main positioning component, a positioning and locking component, a secondary positioning component, a pressing component, a locking component, a drill template component, a bottom frame, etc. In various positioning components, the components for positioning and rigidly connecting the composite components are made of the same material as the composite material, that is, the expansion coefficients are the same, effectively solving the problem of the influence of different tooling dimensions and composite materials caused by temperature changes. It ensures more accurate installation positioning of the composite components during bonding and riveting, improves efficiency and qualification rate.

Description

Technical Field

[0001] The present invention relates to an adhesive bonding and riveting tooling for aircraft composite material components and a manufacturing method thereof. Background Art

[0002] Composite materials have characteristics such as good thermal stability, high specific strength and high specific modulus, high fatigue resistance, and strong fracture resistance, and are widely used in the fields of aviation, aerospace, automotive, medical, etc. Common process methods for assembling composite material parts include adhesive bonding, riveting, etc. Generally, due to the inconsistency with the composite material, the temperature changes in the adhesive bonding and riveting tooling, and there is a certain difference in the change amount between the composite material and the tooling. The larger and longer the product, the more prominent this difference becomes. Summary of the Invention

[0003] The technical problem to be solved by the present invention is that due to different materials and different expansion coefficients between the composite bonding and riveting tooling and the composite parts, when the temperature changes, dimensional change differences occur between the tooling and the composite products during the operation of the tooling. The influence of temperature change on the expansion coefficients of the tooling and the composite parts on the tooling and the composite parts themselves, and the mutual influence between the tooling and the composite materials lead to a decrease in the accuracy of the composite parts and the assembly accuracy, and there is no effective method to control it, resulting in an increase in defective products and production costs. Since the total length of the composite product is 6400 mm and the width is 300 mm, and the structure has the characteristics of being narrow and long, and the product accuracy positional tolerance is Φ0.1 mm. For this situation, the length change amount due to temperature change is relatively large, and the width change amount can be ignored. It is necessary to effectively ensure the free change of the composite product in the length direction with temperature change. Moreover, for larger and longer tooling, this dimensional difference is more prominent. The total length of the tooling of the present invention is up to 6800 mm. To ensure the product accuracy positional tolerance of Φ0.1 mm, the original structure tooling needs to be re-adjusted and detected before each use, wasting time, manpower and other resources, resulting in increased costs and decreased production efficiency. In order to improve product quality and work efficiency and eliminate the influence caused by the material difference between the tooling and the composite parts, the same material with the same expansion coefficient as that of the composite material is used. The present invention uses a carbon fiber board to connect with the tooling positioning component. The expansion coefficients of the same material are the same, effectively solving the problem that during the bonding and riveting process of the composite parts, at the same temperature, due to different materials, the expansion coefficients of the tooling and the composite parts are different, which affects the quality and accuracy of the composite parts. And during the bonding and riveting process of the composite parts, the temperature has a certain change range. Due to different materials and different expansion coefficient changes of the tooling and the composite parts, the influence on the quality and accuracy of the composite parts is greater. Using the same material for the tooling material and the composite parts fundamentally eliminates the influence of temperature change on the installation positioning and assembly accuracy of the bonding and riveting of the composite parts due to different materials between the bonding and riveting tooling and the composite parts, ensures more accurate installation positioning of the bonding and riveting and other assembly work of the composite parts, effectively reduces the influence of different materials on the quality and accuracy of the tooling and the composite parts, improves the assembly efficiency, increases the qualified rate, and effectively reduces the production cost.

[0004] The object of the present invention is to provide a bonding and riveting tooling for aerospace composite parts and a manufacturing method. Since the total length of the composite material product is 6400 mm and the width is 300 mm, it effectively ensures the free change of the composite material product in the length direction with temperature changes and ensures the product accuracy and position tolerance of Φ0.1 mm. The main positioning of the main positioning component uses a circular hole as the positioning reference, and the secondary positioning component uses an oblong hole for positioning in the long direction. The composite material part is clamped by the positioning unit. In various positioning components, the elements for positioning and rigidly connecting the composite material part are made of the same material as the composite material, that is, the expansion coefficients are the same, effectively solving the problem of the influence of different tooling sizes and composite materials due to temperature changes.

[0005] The technical solution adopted by the present invention to solve its technical problems is as follows:

[0006] A bonding and riveting tooling for aerospace composite parts mainly consists of 10 pin positioning components (1), 5 pressing and positioning components (2), 2 main positioning components (3), a positioning and locking component (4), a secondary positioning component (5), 3 pressing components (6), a locking component (7), a bottom frame (8), a support (9), a flipping mechanism (10), a base connecting plate (11), a clamping mechanism (12), and 5 drill template components (13); the outer dimension of the bonding and riveting tooling for aerospace composite parts is 6800×610×1250 mm. To ensure the product accuracy and position tolerance of Φ0.1 mm, the pin positioning component (1), the pressing and positioning component (2), the main positioning component (3), the positioning and locking component (4), the secondary positioning component (5), the pressing component (6), the locking component (7), and the drill template component (13) are respectively rigidly connected to the bottom frame (8) by pins and screws through the support (9);

[0007] The shaft pin positioning assembly (1) consists of a support (9), a flipping mechanism (10), a first connecting plate (1-1), a retaining plate (1-2), a first bushing (1-3), and a manual screw (1-4). The flipping mechanism (10) is rigidly connected to the support (9) and the first connecting plate (1-1) by screws and locating pins. The first connecting plate (1-1) is adjusted and locked by the manual screw (1-4). The retaining plate (1-2) and the first connecting plate (1-1) are rigidly connected by two screws through the first bushing (1-3). The first bushing (1-3) is connected to the first connecting plate (1-1) by interference fit. The bushing (1-3) and the manual screw (1-4) are connected by clearance fit. The first connecting plate (1-1) positions the composite material component. The retaining plate (1-2) is made of the same material as the composite material component and locks the composite material component by the manual screw (1-4). The flipping mechanism (10) is an off-the-shelf part. The flipping mechanism (10) enables the shaft pin positioning assembly (1) to have two working positions. The first working position is the position for making way for installing the composite material component, and the second working position is the positioning position. The pressing and positioning assembly (2) consists of a support (9), a second connecting plate (2-1), a second locating pin (2-2), a locking knurled nut (2-3), a locking handwheel (2-5), a connecting block (2-4), and a second bushing (2-6). The support (9) is firmly connected to the second connecting plate (2-1) by screws and locating pins. The second bushing (2-6) is connected to the second connecting plate (2-1) by interference fit. The second connecting plate (2-1) is rigidly connected to the connecting block (2-4) by a locating pin and the locking handwheel (2-5). The second locating pin (2-2) is connected with the second bushing (2-6) by clearance fit using the same material as the composite material component for positioning the composite material component. The locking knurled nut (2-3) is rigidly connected to the connecting block (2-4) by threads for clamping the composite material component.

[0008] The main positioning assembly (3) consists of a support (9), a third connecting plate (3-1), a third locating pin (3-4), a third bushing (3-2), and a rubber pad (3-3). The support (9) is rigidly connected to the third connecting plate (3-1) by screws and locating pins. The third connecting plate (3-1) is rigidly connected to the rubber pad (3-3) by screws. The third bushing (3-2) is connected to the third connecting plate (3-1) by interference fit. The third locating pin (3-4) is connected with the third bushing (3-2) by clearance fit using the same material as the composite material component. The third locating pin (3-4) is used for positioning the composite material component.

[0009] The positioning and locking assembly (4) consists of a support (9), connecting plate four (4-1), positioning block four (4-2), knurled locking nut four (4-3), locking handwheel four (4-4), and connecting block four (4-5). The support (9), positioning block four (4-2), and connecting plate four (4-1) are rigidly connected by screws and positioning pins. The connecting plate four (4-1) and connecting block four (4-5) are rigidly connected by a positioning pin and locking handwheel four (4-4). The knurled locking nut four (4-3) is rigidly connected to the connecting block four (4-5) by a thread and is used to clamp the composite material component.

[0010] The secondary positioning assembly (5) consists of a support (9), connecting plate five (5-1), positioning pin five (5-2), and slotted bush (5-3). The support (9) and connecting plate five (5-1) are rigidly connected by screws and positioning pins. The slotted bush (5-3) is connected to the connecting plate five (5-1) by an interference fit. The positioning pin five (5-2) is positioned and connected to the slotted bush (5-3) with a clearance fit using the same material as the composite material component. The positioning pin five (5-2) is used to position the composite material component.

[0011] The pressing assembly (6) consists of a support (9), a horizontal manual operating mechanism (6-1), a horizontal clamping block (6-2), and connecting plate six (6-3). The support (9) and connecting plate six (6-3) are rigidly connected by screws and positioning pins. The connecting plate six (6-3) and the horizontal manual operating mechanism (6-1) are rigidly connected by a thread. The horizontal manual operating mechanism (6-1) and the horizontal clamping block (6-2) are rigidly connected by a thread. The rotation of the horizontal manual operating mechanism (6-1) drives the horizontal clamping block (6-2) to move horizontally and is used to press the composite material component.

[0012] The locking assembly (7) consists of a support (9), a clamping mechanism (12), connecting plate seven (7-1), and angle seat (7-2). The support (9) and connecting plate seven (7-1) are rigidly connected by screws and positioning pins. The angle seat (7-2) is rigidly connected to the connecting plate seven (7-1) by screws. One end of the clamping mechanism (12) is supported on the connecting plate seven (7-1), and the other end rigidly clamps the composite material component through an adjusting screw.

[0013] The bottom frame (8) is composed of a composite material substrate (8-1), a first frame cross plate (8-2), a floor adjusting support (8-3), a frame longitudinal plate (8-4), and a second frame cross plate (8-5). The first frame cross plate (8-2), the frame longitudinal plate (8-4), and the second frame cross plate (8-5) are rigidly connected by welding to form a frame structure. The frame longitudinal plate (8-4) is rigidly connected to the floor adjusting support (8-3) by an adjustable screw. The first frame cross plate (8-2), the frame longitudinal plate (8-4), and the second frame cross plate (8-5) are all made of square steel. The composite material substrate (8-1) is rigidly connected to the first frame cross plate (8-2), the frame longitudinal plate (8-4), and the second frame cross plate (8-5) by positioning pins and screws;

[0014] The support (9) is composed of a support longitudinal plate (9-1), 4 support longitudinal plate screw holes (9-2), 2 bottom support longitudinal plate positioning pin holes (9-3), 4 support bottom plate screw holes (9-4), 2 support bottom plate positioning pin holes (9-5), a support bottom plate (9-6), and a support bottom plate stiffening rib plate (9-7). The support longitudinal plate (9-1), the support bottom plate (9-6), and the support bottom plate stiffening rib plate (9-7) are rigidly connected by welding to form an L-shaped structure;

[0015] The drill template assembly (13) consists of drill template 1 (13-1), drill template 2 (13-2), drill template 3 (13-3), drill template 4 (13-4), drill template 5 (13-5), manual locking mechanism (13-6), long pin positioning mechanism (13-7), base connecting plate (11), drilling connecting plate (13-9), support (9), and clamping mechanism (12). According to the design requirements of the composite material product, the corresponding number of drill templates and drilling size requirements are designed. This composite material product requires five drill templates, namely drill template 1 (13-1), drill template 2 (13-2), drill template 3 (13-3), drill template 4 (13-4), and drill template 5 (13-5), which are rigidly connected to the drilling connecting plate (13-9) using positioning pins and screws respectively. The support (9) is rigidly connected to the base connecting plate (11) and the drilling connecting plate (13-9) using positioning pins and screws. The base connecting plate (11) is rigidly connected to the bottom frame (8) through the manual locking mechanism (13-6) and the long pin positioning mechanism (13-7). The clamping mechanism (12) is rigidly clamped and connected to the composite material product through drill template 1 (13-1), drill template 2 (13-2), drill template 3 (13-3), drill template 4 (13-4), and drill template 5 (13-5) using screws. Before riveting, the composite material product is drilled through the drill templates. Drill template 1 (13-1), drill template 2 (13-2), drill template 3 (13-3), drill template 4 (13-4), and drill template 5 (13-5) respectively consist of 4 threaded holes for installing the drilling connecting plate (13-10), 2 positioning pin holes 1 (13-11), drill die holes (13-12) consistent with the requirements of the composite material product, drill template matrix (13-13), and weight-reducing notches. The drilling connecting plate (13-9) consists of 2 positioning pin holes 1 (13-11), 4 threaded holes for installing the support (13-14), 2 threaded holes for installing the manual locking mechanism (13-15), 2 mating holes for the long pin positioning mechanism (13-16), drilling connecting plate matrix (13-17), and weight-reducing notches. The base connecting plate (11) consists of 2 threaded holes for installing the manual locking mechanism (13-15), 2 mating holes for the long pin positioning mechanism (13-16), 2 threaded holes for the long pin positioning mechanism (13-18), base connecting plate matrix (13-19), and 2 positioning pin holes 2 (13-20).

[0016] The manufacturing method of the bonding and riveting tooling for aerospace composite material components specifically includes the following technological steps:

[0017] (1) Rigidly connect the shaft pin positioning component (1), pressing and positioning component (2), main positioning component (3), positioning and locking component (4), secondary positioning component (5), pressing component (6), locking component (7), and drill template component (13) to the bottom frame (8) using support (9), positioning pins, and screws respectively;

[0018] (2) Position the composite material part with the third positioning pin (3-4) of the main positioning component (3), the secondary positioning component (5) and the fifth positioning pin (5-2).

[0019] (3) Open the clamping mechanism (12) and the pressing component (6). Install the composite material part on the tooling. The rubber pad (3-3) supports the composite material part. The third positioning pin (3-4) and the fifth positioning pin (5-2) are inserted for positioning. Clamp with the clamping mechanism (12). Use the horizontal manual control mechanism (6-1) of the pressing component (6) to drive the horizontal clamping block (6-2) to move horizontally. One end of the clamping mechanism (12) of the locking component (7) is supported on the seventh connecting plate (7-1), and the other end rigidly clamps the composite material part through the adjusting screw to complete the positioning and pressing of the composite material part.

[0020] (4) Positioning and clamping of the fork ear part of the composite material part: The wing nut in the flipping mechanism (10) of the shaft pin positioning component (1) locks and releases to control two working positions. The flipping mechanism (10) is an off-the-shelf component. When the wing nut in the flipping mechanism (10) is loosened, it controls the first working position, which is the working position for making way for installing the composite material part. When the wing nut in the flipping mechanism (10) is locked, it controls the second working position, which is the positioning working position. It is mainly positioned by the retaining plate (1-2) and the end face of the first connecting plate (1-1), and tightened with the manual screw (1-4). The number of shaft pin positioning components (1) is 10, which mainly positions the fork ear part of the composite material part to complete the positioning and clamping of 10 shaft pin positioning components (1).

[0021] (5) Positioning and clamping of the rudder beam part of the composite material part: The second positioning pin (2-2) and the fourth positioning block (4-2) position the ribbed part of the composite material part, and lock with the second locking handwheel (2-5) and the fourth locking handwheel (4-4), and further lock with the second knurled locking nut (2-3) and the fourth knurled locking nut (4-3). After the positioning and clamping of the ribbed part are completed, the components for positioning and clamping the ribbed part are 5 pressing and positioning components (2) and 1 positioning and locking component (4), with a total of 6 pieces, to complete the positioning and installation of the rudder beam part of the composite material.

[0022] (6) Drilling of composite material components: The first drilling template (13-1), the second drilling template (13-2), the third drilling template (13-3), the fourth drilling template (13-4), and the fifth drilling template (13-5) of the drilling template assembly (13) are respectively installed on the bottom frame (8) by using a drilling connection plate (13-9), a support (9), a base connection plate (11), a manual locking mechanism (13-6), and a long pin positioning mechanism (13-7) to perform the drilling work. After the drilling is completed, the first drilling template (13-1), the second drilling template (13-2), the third drilling template (13-3), the fourth drilling template (13-4), the fifth drilling template (13-5), the drilling connection plate (13-9), the support (9), the base connection plate (11), the manual locking mechanism (13-6), the long pin positioning mechanism (13-7), etc. of the drilling template assembly (13) are disassembled, and then the riveting work is carried out;

[0023] (7) After the riveting work is completed, open the butterfly nut in the shaft pin positioning component (1), open the flipping mechanism (10) along the rotating shaft, open the clamping mechanism (12) and the horizontal manual operating mechanism (6-1), pull out the second positioning pin (2-2), the third positioning pin (3-4), and the fifth positioning pin (5-2), and unscrew and remove the manual screw (1-4), the second locking handwheel (2-5), the second locking knurled nut (2-3), the fourth locking knurled nut (4-3), and the fourth locking handwheel (4-4) to remove the lower part of the composite material component. Description of the Drawings

[0024] Figure 1 is a three-dimensional structural schematic diagram of the present invention.

[0025] Figure 2 is a structural schematic diagram of the shaft pin positioning component (1) of the present invention.

[0026] Figure 3 is a structural schematic diagram of the pressing and positioning component (2) of the present invention.

[0027] Figure 4 is a schematic diagram of the structural composition of the main positioning component (3) of the present invention.

[0028] Figure 5 is a schematic diagram of the structural composition of the positioning and locking component (4) of the present invention.

[0029] Figure 6 is a schematic diagram of the structural composition of the secondary positioning component (5) of the present invention.

[0030] Figure 7 is a schematic diagram of the structural composition of the pressing component (6) of the present invention.

[0031] Figure 8 is a schematic diagram of the structural composition of the locking component (7) of the present invention.

[0032] Figure 9 It is a schematic diagram of the structure composition of the bottom frame (8) of the present invention.

[0033] Figure 10 It is a schematic diagram of the structure composition of the support (9) of the present invention.

[0034] Figure 11 It is a schematic diagram of the structure composition of the drill template assembly (13) of the present invention.

[0035] Figure 12 It is a schematic diagram of the structure composition of the first drill template (13-1) of the present invention.

[0036] Figure 13 It is a schematic diagram of the structure composition of the second drill template (13-2) of the present invention.

[0037] Figure 14 It is a schematic diagram of the structure composition of the third drill template (13-3) of the present invention.

[0038] Figure 15 It is a schematic diagram of the structure composition of the fourth drill template (13-4) of the present invention.

[0039] Figure 16 It is a schematic diagram of the structure composition of the fifth drill template (13-5) of the present invention.

[0040] Figure 17 It is a schematic diagram of the structure composition of the base connecting plate (11) of the present invention.

[0041] Figure 18 It is a schematic diagram of the structure composition of the drilling connecting plate (13-9) of the present invention.

[0042] Figure 19 It is a schematic diagram of the structure composition of the manual locking mechanism (13-6) of the present invention.

[0043] Figure 20 It is a schematic diagram of the structure composition of the long pin positioning mechanism (13-7) of the present invention.

[0044] 1 - Axle pin positioning component, 2 - Pressing and positioning component, 3 - Main positioning component, 4 - Positioning and locking component, 5 - Secondary positioning component, 6 - Pressing and positioning component, 7 - Locking and positioning component, 8 - Bottom frame, 9 - Support, 10 - Flipping mechanism, 11 - Base connecting plate, 12 - Clamping mechanism, 13 - Drill template assembly Detailed implementation manners

[0045] The technical solution adopted by the present invention to solve its technical problems is:

[0046] Figure 1It is a schematic diagram of the three-dimensional structure of the present invention. An outer contour dimension of a riveting tooling for aircraft composite material products is 6800×610×1250 mm. It mainly consists of 10 pin positioning components (1), 5 pressing and positioning components (2), 2 main positioning components (3), a positioning and locking component (4), a secondary positioning component (5), 3 pressing components (6), a locking component (7), a bottom frame (8), a support (9), a flipping mechanism (10), a base connecting plate (11), a clamping mechanism (12), and 5 drill template components (13). The pin positioning component (1), the pressing and positioning component (2), the main positioning component (3), the positioning and locking component (4), the secondary positioning component (5), the pressing component (6), and the locking component (7) are rigidly connected to the bottom frame (8) by dowel pins and screws respectively. Since the total length of the composite material product is 6400 mm and the width is 300 mm, the structure has the characteristics of being narrow and long. The product precision positional tolerance is Φ0.1 mm, effectively ensuring the free change of the composite material product in the length direction with temperature change. The main positioning of the main positioning component uses a round hole as the positioning reference, and the secondary positioning component uses an oblong hole in the long direction for positioning. The composite material component is clamped by a positioning unit, and the positioning unit is an aviation composite material component bonding and riveting tooling with a carbon fiber board connection structure form.

[0047] Figure 2 It is a schematic diagram of the structure of the pin positioning component (1) of the present invention. The pin positioning component (1) consists of a support (9), a flipping mechanism (10), a connecting plate 1 (1-1), a retaining plate (1-2), a bushing 1 (1-3), and a manual screw (1-4). The flipping mechanism (10) is rigidly connected to the support (9) and the connecting plate 1 (1-1) by screws and positioning pins. The connecting plate 1 (1-1) is adjusted and locked by the manual screw (1-4). The retaining plate (1-2) is rigidly connected to the connecting plate 1 (1-1) by two screws through the bushing 1 (1-3). The bushing 1 (1-3) is connected to the connecting plate 1 (1-1) by interference fit, and the bushing 1 (1-3) is connected to the manual screw (1-4) by clearance fit. The connecting plate 1 (1-1) positions the composite material component, and the retaining plate (1-2) locks the composite material component by the manual screw (1-4) using the same material as the composite material component. The flipping mechanism (10) is an off-the-shelf part. The flipping mechanism (10) enables the pin positioning component (1) to have 2 working positions. The first working position is the position for making way for installing the composite material component, and the second working position is the positioning position.

[0048] Figure 3It is a schematic structural diagram of the pressing and positioning assembly (2) of the present invention. The pressing and positioning assembly (2) is composed of a support (9), a second connecting plate (2-1), a second positioning pin (2-2), a second lock knurled nut (2-3), a second lock handwheel (2-5), a second connecting block (2-4), and a second bushing (2-6). The support (9) and the second connecting plate (2-1) are fixedly connected by screws and positioning pins. The second bushing (2-6) and the second connecting plate (2-1) are connected by interference fit. The second connecting plate (2-1) and the second connecting block (2-4) are rigidly connected by a positioning pin and the second lock handwheel (2-5). The second positioning pin (2-2) is connected with a clearance fit to the second bushing (2-6) using the same material as the composite material part, and is used to position the composite material part. The second lock knurled nut (2-3) is rigidly connected to the second connecting block (2-4) by a thread and is used to clamp the composite material part.

[0049] Figure 4 It is a schematic structural diagram of the main positioning assembly (3) of the present invention. The main positioning assembly (3) is composed of a support (9), a third connecting plate (3-1), a third positioning pin (3-4), a third bushing (3-2), and a rubber pad (3-3). The support (9) and the third connecting plate (3-1) are rigidly connected by screws and positioning pins. The third connecting plate (3-1) and the rubber pad (3-3) are rigidly connected by screws. The third bushing (3-2) and the third connecting plate (3-1) are connected by interference fit. The third positioning pin (3-4) is connected with a clearance fit to the third bushing (3-2) using the same material as the composite material part, and the third positioning pin (3-4) is used to position the composite material part.

[0050] Figure 5 It is a schematic structural diagram of the positioning and locking assembly (4) of the present invention. The positioning and locking assembly (4) is composed of a support (9), a fourth connecting plate (4-1), a fourth positioning block (4-2), a fourth lock knurled nut (4-3), a fourth lock handwheel (4-4), and a fourth connecting block (4-5). The support (9), the fourth positioning block (4-2) and the fourth connecting plate (4-1) are rigidly connected by screws and positioning pins. The fourth connecting plate (4-1) and the fourth connecting block (4-5) are rigidly connected by a positioning pin and the fourth lock handwheel (4-4). The fourth lock knurled nut (4-3) is rigidly connected to the fourth connecting block (4-5) by a thread and is used to clamp the composite material part.

[0051] Figure 6It is a schematic diagram of the structure composition of the secondary positioning component (5) of the present invention. The secondary positioning component (5) is composed of a support (9), a fifth connecting plate (5-1), a fifth positioning pin (5-2), and an oblong hole bushing (5-3). The support (9) and the fifth connecting plate (5-1) are rigidly connected by screws and positioning pins. The oblong hole bushing (5-3) and the fifth connecting plate (5-1) are connected by interference fit. The fifth positioning pin (5-2) is positioned and connected with clearance fit with the oblong hole bushing (5-3) using the same material as the composite material component. The fifth positioning pin (5-2) is used to position the composite material component.

[0052] Figure 7 It is a schematic diagram of the structure composition of the pressing component (6) of the present invention. The pressing component (6) is composed of a support (9), a horizontal manual operating mechanism (6-1), a horizontal clamping block (6-2), and a sixth connecting plate (6-3). The support (9) and the sixth connecting plate (6-3) are rigidly connected by screws and positioning pins. The sixth connecting plate (6-3) and the horizontal manual operating mechanism (6-1) are rigidly connected by threads. The horizontal manual operating mechanism (6-1) and the horizontal clamping block (6-2) are rigidly connected by threads. The rotation of the horizontal manual operating mechanism (6-1) drives the horizontal movement of the horizontal clamping block (6-2) to press the composite material component.

[0053] Figure 8 It is a schematic diagram of the structure composition of the locking component (7) of the present invention. The locking component (7) is composed of a support (9), a clamping mechanism (12), a seventh connecting plate (7-1), and an angle seat (7-2). The support (9) and the seventh connecting plate (7-1) are rigidly connected by screws and positioning pins. The angle seat (7-2) and the seventh connecting plate (7-1) are rigidly connected by screws. One end of the clamping mechanism (12) is supported on the seventh connecting plate (7-1), and the other end rigidly clamps the composite material component through an adjusting screw.

[0054] Figure 9 It is a schematic diagram of the structure composition of the bottom frame (8) of the present invention. The bottom frame (8) is composed of a composite material substrate (8-1), a first frame cross plate (8-2), a floor adjusting support (8-3), a frame longitudinal plate (8-4), and a second frame cross plate (8-5). The first frame cross plate (8-2), the frame longitudinal plate (8-4), and the second frame cross plate (8-5) are welded and rigidly connected to form a frame structure. The frame longitudinal plate (8-4) and the floor adjusting support (8-3) are rigidly connected by adjustable screws. The first frame cross plate (8-2), the frame longitudinal plate (8-4), and the second frame cross plate (8-5) are all made of square steel materials. The composite material substrate (8-1) and the first frame cross plate (8-2), the frame longitudinal plate (8-4), and the second frame cross plate (8-5) are rigidly connected by positioning pins and screws.

[0055] Figure 10It is a schematic diagram of the structure composition of the support (9) of the present invention. The support (9) is composed of a support longitudinal plate (9-1), 4 support longitudinal plate screw holes (9-2), 2 support bottom longitudinal plate positioning pin holes (9-3), 4 support bottom plate screw holes (9-4), 2 support bottom plate positioning pin holes (9-5), a support bottom plate (9-6), and a support bottom plate stiffening rib plate (9-7). The support longitudinal plate (9-1), the support bottom plate (9-6), and the support bottom plate stiffening rib plate (9-7) are rigidly connected by welding to form an L-shaped structure.

[0056] Figure 11 It is a schematic diagram of the structure composition of the drill template assembly (13) of the present invention. Figure 12 It is a schematic diagram of the structure composition of the first drill template (13-1) of the present invention. Figure 13 It is a schematic diagram of the structure composition of the second drill template (13-2) of the present invention. Figure 14 It is a schematic diagram of the structure composition of the third drill template (13-3) of the present invention. Figure 15 It is a schematic diagram of the structure composition of the fourth drill template (13-4) of the present invention. Figure 16 It is a schematic diagram of the structure composition of the fifth drill template (13-5) of the present invention. Figure 17 It is a schematic diagram of the structure composition of the base connecting plate (11) of the present invention. Figure 18 It is a schematic diagram of the structure composition of the drilling connecting plate (13-9) of the present invention. Figure 19 It is a schematic diagram of the structure composition of the manual locking mechanism (13-6) of the present invention. Figure 20It is a schematic diagram of the structural composition of the long pin positioning mechanism (13-7) of the present invention. The drill template assembly (13) is composed of drill template one (13-1), drill template two (13-2), drill template three (13-3), drill template four (13-4), drill template five (13-5), manual locking mechanism (13-6), long pin positioning mechanism (13-7), base connecting plate (11), drilling connecting plate (13-9), support (9), and clamping mechanism (12). According to the design requirements of the composite material product, the corresponding number of drill templates and drilling size requirements are designed. This composite material product requires five drill templates, namely drill template one (13-1), drill template two (13-2), drill template three (13-3), drill template four (13-4), and drill template five (13-5), which are rigidly connected to the drilling connecting plate (13-9) by positioning pins and screws respectively. The support (9) is rigidly connected to the base connecting plate (11) and the drilling connecting plate (13-9) by positioning pins and screws. The base connecting plate (11) is rigidly connected to the bottom frame (8) through the manual locking mechanism (13-6) and the long pin positioning mechanism (13-7). The clamping mechanism (12) is rigidly clamped and connected to the composite material part by screws through drill template one (13-1), drill template two (13-2), drill template three (13-3), drill template four (13-4), and drill template five (13-5). Before riveting, the composite material product is drilled through the drill template. Drill template one (13-1), drill template two (13-2), drill template three (13-3), drill template four (13-4), and drill template five (13-5) are respectively composed of 4 threaded holes for installing the drilling connecting plate (13-10), 2 positioning pin holes one (13-11), drill die holes (13-12) consistent with the requirements of the composite material product, drill template matrix (13-13), and weight reduction notches. The drilling connecting plate (13-9) is composed of 2 positioning pin holes one (13-11), 4 threaded holes for installing the support (13-14), 2 threaded holes for installing the manual locking mechanism (13-15), 2 mating holes for the long pin positioning mechanism (13-16), drilling connecting plate matrix (13-17), and weight reduction notches. The base connecting plate (11) is composed of 2 threaded holes for installing the manual locking mechanism (13-15), 2 mating holes for the long pin positioning mechanism (13-16), 2 threaded holes for the long pin positioning mechanism (13-18), base connecting plate matrix (13-19), and 2 positioning pin holes two (13-20). The manual locking mechanism (13-6) is rigidly connected by a cross-shaped handwheel (13-22) and a screw (13-23). The long pin positioning mechanism (13-7) is composed of a long pin positioning guide sleeve (13-23), a positioning long pin (13-23), and a one-word manual arm (13-22). The positioning long pin (13-23) is rigidly connected to the one-word manual arm (13-22), and the long pin positioning guide sleeve (13-23) is connected to the positioning long pin (13-23) by a clearance fit.After positioning and drilling the composite material product by riveting, remove the drill template assembly (13). The composite material product is riveted under the structures such as the pin positioning assembly (1), the pressing and positioning assembly (2), the main positioning assembly (3), the positioning and locking assembly (4), the secondary positioning assembly (5), the pressing assembly (6), the locking assembly (7), and the bottom frame (8). And the manual locking mechanism (13-6) and the long pin positioning mechanism (13-7) with quick-change method are used to improve the assembly and disassembly efficiency with the bottom frame (8).;

[0057] The manufacturing method of the bonding and riveting tooling for aerospace composite material parts specifically includes the following technological steps:

[0058] (1) Rigidly connect the pin positioning assembly (1), the pressing and positioning assembly (2), the main positioning assembly (3), the positioning and locking assembly (4), the secondary positioning assembly (5), the pressing assembly (6), the locking assembly (7), and the drill template assembly (13) to the bottom frame (8) respectively by using the support (9) with dowel pins and screws;

[0059] (2) Position the composite material part with the positioning pin three (3-4) of the main positioning assembly (3) and the positioning pin five (5-2) of the secondary positioning assembly (5); (3) Open the clamping mechanism (12) and the pressing assembly (6). Install the composite material part on the tooling. The rubber pad (3-3) supports the composite material part. The positioning pin three (3-4) and the positioning pin five (5-2) are inserted and tightened for positioning. Clamp with the clamping mechanism (12). Drive the horizontal clamping block (6-2) to move horizontally by rotating the horizontal manual operating mechanism (6-1) of the pressing assembly (6). One end of the clamping mechanism (12) of the locking assembly (7) is supported on the connecting plate seven (7-1), and the other end rigidly clamps the composite material part through the adjusting screw to complete the positioning and pressing work of the composite material part;

[0060] (4) Positioning and clamping of the fork ear part of the composite material part: The butterfly nut in the flipping mechanism (10) of the pin positioning assembly (1) locks and unlocks to control two working positions. The flipping mechanism (10) is an off-the-shelf part. The butterfly nut in the flipping mechanism (10) unlocks to control the first working position, which is the working position for making way for installing the composite material part. The butterfly nut in the flipping mechanism (10) locks to control the second working position, which is the positioning working position. It is mainly positioned by the stop piece (1-2) and the end face of the connecting plate one (1-1), and tightened with the manual screw (1-4). The number of the pin positioning assemblies (1) is 10, which mainly positions the fork ear part of the composite material part to complete the positioning and clamping of 10 pin positioning assemblies (1);

[0061] (5) Positioning and clamping of the rudder beam part of the composite material component: The positioning pin two (2-2) and the positioning block four (4-2) position the rib part of the composite material component, and the locking handwheel two (2-5) and the locking handwheel four (4-4) are locked. The locking knurled nut two (2-3) and the locking knurled nut four (4-3) are locked. The positioning and clamping of the rib part are completed. The components for positioning and clamping the rib part are 5 pressing and positioning components (2) and 1 positioning and locking component (4), with a total quantity of 6 pieces, completing the positioning and installation of the rudder beam part of the composite material;

[0062] (6) Drilling of the composite material component: The drill templates one (13-1), two (13-2), three (13-3), four (13-4), and five (13-5) of the drill template assembly (13) are respectively installed on the bottom frame (8) by using the drill connection plate (13-9), the support (9), the base connection plate (11), the manual locking mechanism (13-6), and the long pin positioning mechanism (13-7) for drilling work. After drilling, remove the drill templates one (13-1), two (13-2), three (13-3), four (13-4), five (13-5), the drill connection plate (13-9), the support (9), the base connection plate (11), the manual locking mechanism (13-6), the long pin positioning mechanism (13-7), etc. of the drill template assembly (13), and then carry out riveting work;

[0063] (7) After the riveting work is completed, open the wing nut in the shaft pin positioning component (1), open the flipping mechanism (10) along the rotating shaft, open the clamping mechanism (12) and the horizontal manual control mechanism (6-1), pull out the positioning pin two (2-2), positioning pin three (3-4), and positioning pin five (5-2), and screw out and remove the manual screw (1-4), locking handwheel two (2-5), locking knurled nut two (2-3), locking knurled nut four (4-3), and locking handwheel four (4-4) to remove the lower part of the composite material component.

Claims

1. An adhesive bonding and riveting tooling for aerospace composite components, mainly composed of 10 pin positioning components (1), 5 pressing and positioning components (2), 2 main positioning components (3), a positioning and locking component (4), a secondary positioning component (5), 3 pressing components (6), a locking component (7), a bottom frame (8), a support (9), a flipping mechanism (10), a base connecting plate (11), a clamping mechanism (12), and 5 drill template components (13); the outer dimension of the aerospace composite riveting tooling is 6800×610×1250mm. To ensure the product precision position tolerance of Φ0.1mm, the pin positioning component (1), the pressing and positioning component (2), the main positioning component (3), the positioning and locking component (4), the secondary positioning component (5), the pressing component (6), the locking component (7), and the drill template component (13) are respectively rigidly connected to the support (9) and the bottom frame (8) by dowel pins and screws; the support (9) consists of a support longitudinal plate (9-1), 4 support longitudinal plate screw holes (9-2), 2 support bottom longitudinal plate positioning pin holes (9-3), 4 support bottom plate screw holes (9-4), 2 support bottom plate positioning pin holes (9-5), a support bottom plate (9-6), and a support bottom plate stiffening rib plate (9-7). The support longitudinal plate (9-1), the support bottom plate (9-6), and the support bottom plate stiffening rib plate (9-7) are rigidly connected to form an L-shaped structure by welding. The pin positioning component (1) consists of a support (9), a flipping mechanism (10), a connecting plate one (1-1), a retaining piece (1-2), a bushing one (1-3), and a manual screw (1-4). The flipping mechanism (10) is rigidly connected to the support (9) and the connecting plate one (1-1) by screws and positioning pins. The connecting plate one (1-1) is adjusted and locked by the manual screw (1-4). The retaining piece (1-2) is rigidly connected to the connecting plate one (1-1) by two screws through the bushing one (1-3). The bushing one (1-3) is connected to the connecting plate one (1-1) by interference fit, and the bushing one (1-3) is connected to the manual screw (1-4) by clearance fit. The connecting plate one (1-1) positions the composite component, and the retaining piece (1-2) locks the composite component by the manual screw (1-4) using the same material as the composite component. The flipping mechanism (10) is an off-the-shelf component. The flipping mechanism (10) enables the pin positioning component (1) to have 2 working positions. The first working position is the position for making way for installing the composite component, and the second working position is the positioning position. The pressing and positioning assembly (2) is composed of a support (9), a second connecting plate (2-1), a second positioning pin (2-2), a second lock knurled nut (2-3), a second lock handwheel (2-5), a second connecting block (2-4), and a second bushing (2-6). The support (9) and the second connecting plate (2-1) are fixedly connected by screws and positioning pins. The second bushing (2-6) and the second connecting plate (2-1) are connected by interference fit. The second connecting plate (2-1) and the second connecting block (2-4) are rigidly connected by a positioning pin and the second lock handwheel (2-5). The second positioning pin (2-2) is connected by clearance fit positioning with the second bushing (2-6) using the same material as the composite material part, and is used to position the composite material part. The second lock knurled nut (2-3) is rigidly connected to the second connecting block (2-4) by threads and is used to clamp the composite material part. The main positioning assembly (3) is composed of a support (9), a third connecting plate (3-1), a third positioning pin (3-4), a third bushing (3-2), and a rubber pad (3-3). The support (9) and the third connecting plate (3-1) are rigidly connected by screws and positioning pins. The third connecting plate (3-1) and the rubber pad (3-3) are rigidly connected by screws. The third bushing (3-2) and the third connecting plate (3-1) are connected by interference fit. The third positioning pin (3-4) is connected by clearance fit with the third bushing (3-2) using the same material as the composite material part, and the third positioning pin (3-4) is used to position the composite material part. The secondary positioning assembly (5) is composed of a support (9), a fifth connecting plate (5-1), a fifth positioning pin (5-2), and an oblong hole bushing (5-3). The support (9) and the fifth connecting plate (5-1) are rigidly connected by screws and positioning pins. The oblong hole bushing (5-3) and the fifth connecting plate (5-1) are connected by interference fit. The fifth positioning pin (5-2) is connected by clearance fit positioning with the oblong hole bushing (5-3) using the same material as the composite material part, and the fifth positioning pin (5-2) is used to position the composite material part.

2. The bonding and riveting tooling for aerospace composite material components according to claim 1, wherein: The positioning and locking assembly (4) is composed of a support (9), a fourth connecting plate (4-1), a fourth positioning block (4-2), a fourth lock knurled nut (4-3), a fourth lock handwheel (4-4), and a fourth connecting block (4-5). The support (9), the fourth positioning block (4-2) and the fourth connecting plate (4-1) are rigidly connected by screws and positioning pins. The fourth connecting plate (4-1) and the fourth connecting block (4-5) are rigidly connected by a positioning pin and the fourth lock handwheel (4-4). The fourth lock knurled nut (4-3) is rigidly connected to the fourth connecting block (4-5) by threads and is used to clamp the composite material part.

3. The bonding and riveting tooling for aerospace composite material components according to claim 1, wherein: The pressing component (6) consists of a support (9), a horizontal manual operating mechanism (6-1), a horizontal clamping block (6-2), and a connecting plate VI (6-3). The support (9) is rigidly connected to the connecting plate VI (6-3) by screws and positioning pins. The connecting plate VI (6-3) is rigidly connected to the horizontal manual operating mechanism (6-1) by threads. The horizontal manual operating mechanism (6-1) is rigidly connected to the horizontal clamping block (6-2) by threads. The rotation of the horizontal manual operating mechanism (6-1) drives the horizontal movement of the horizontal clamping block (6-2) to press the composite material component. The locking component (7) consists of a support (9), a clamping mechanism (12), a connecting plate VII (7-1), and an angle seat (7-2). The support (9) is rigidly connected to the connecting plate VII (7-1) by screws and positioning pins. The angle seat (7-2) is rigidly connected to the connecting plate VII (7-1) by screws. One end of the clamping mechanism (12) is supported on the connecting plate VII (7-1), and the other end rigidly clamps the composite material component through an adjusting screw.

4. The bonding and riveting tooling for aerospace composite components according to claim 1, wherein: The bottom frame (8) consists of a composite material substrate (8-1), a frame cross plate I (8-2), a floor adjusting support (8-3), a frame longitudinal plate (8-4), and a frame cross plate II (8-5). The frame cross plate I (8-2), the frame longitudinal plate (8-4), and the frame cross plate II (8-5) are welded to each other to form a rigid frame structure. The frame longitudinal plate (8-4) is rigidly connected to the floor adjusting support (8-3) by adjustable screws. The frame cross plate I (8-2), the frame longitudinal plate (8-4), and the frame cross plate II (8-5) are all made of square steel. The composite material substrate (8-1) is rigidly connected to the frame cross plate I (8-2), the frame longitudinal plate (8-4), and the frame cross plate II (8-5) by positioning pins and screws.

5. The bonding and riveting tooling for aircraft composite material components according to claim 1, characterized in that: The drill template assembly (13) consists of a first drill template (13-1), a second drill template (13-2), a third drill template (13-3), a fourth drill template (13-4), a fifth drill template (13-5), a manual locking mechanism (13-6), a long pin positioning mechanism (13-7), a base connecting plate (11), a drilling connecting plate (13-9), a support (9), and a clamping mechanism (12). According to the design requirements of the composite material product, the corresponding number of drill templates and drilling size requirements are designed. This composite material product requires five drill templates, namely the first drill template (13-1), the second drill template (13-2), the third drill template (13-3), the fourth drill template (13-4), and the fifth drill template (13-5), which are respectively rigidly connected to the drilling connecting plate (13-9) by positioning pins and screws. The support (9) is rigidly connected to the base connecting plate (11) and the drilling connecting plate (13-9) by positioning pins and screws. The base connecting plate (11) is rigidly connected to the bottom frame (8) through the manual locking mechanism (13-6) and the long pin positioning mechanism (13-7). The clamping mechanism (12) is rigidly clamped and connected to the composite material product through the first drill template (13-1), the second drill template (13-2), the third drill template (13-3), the fourth drill template (13-4), and the fifth drill template (13-5). Before riveting, the composite material product is drilled through the drill templates. The first drill template (13-1), the second drill template (13-2), the third drill template (13-3), the fourth drill template (13-4), and the fifth drill template (13-5) respectively consist of 4 threaded holes for installing the drilling connecting plate (13-10), 2 first positioning pin holes (13-11), drill die holes (13-12) consistent with the requirements of the composite material product, a drill template matrix (13-13), and weight-reducing notches. The drilling connecting plate (13-9) consists of 2 first positioning pin holes (13-11), 4 threaded holes for installing the support (13-14), 2 threaded holes for installing the manual locking mechanism (13-15), 2 mating holes for the long pin positioning mechanism (13-16), a drilling connecting plate matrix (13-17), and weight-reducing notches. The base connecting plate (11) consists of 2 threaded holes for installing the manual locking mechanism (13-15), 2 mating holes for the long pin positioning mechanism (13-16), 2 threaded holes for the long pin positioning mechanism (13-18), a base connecting plate matrix (13-19), and 2 second positioning pin holes (13-20).

6. The manufacturing method of the bonding and riveting tooling for the aviation composite material component according to claim 1, wherein: The manufacturing method of the bonding and riveting tooling for aerospace composite material components specifically includes the following technological steps: (1) Rigidly connect the shaft pin positioning assembly (1), the pressing and positioning assembly (2), the main positioning assembly (3), the positioning and locking assembly (4), the secondary positioning assembly (5), the pressing assembly (6), the locking assembly (7), and the drill template assembly (13) to the bottom frame (8) by using the support (9) with positioning pins and screws respectively; (2) Position the composite material component with the third positioning pin (3-4) of the main positioning assembly (3) and the fifth positioning pin (5-2) of the secondary positioning assembly (5); (3) Open the clamping mechanism (12) and the pressing component (6). Install the composite material component on the tooling. The rubber pad (3-3) supports the composite material component. Insert the positioning pin three (3-4) and the positioning pin five (5-2) for positioning. Clamp with the clamping mechanism (12), rotate the horizontal manual operating mechanism (6-1) of the pressing component (6) to drive the horizontal clamping block (6-2) to move horizontally, and support one end of the clamping mechanism (12) of the locking component (7) on the connecting plate seven (7-1), and rigidly clamp the composite material component with the adjusting screw at the other end to complete the positioning and pressing of the composite material component; (4) Positioning and clamping of the fork ear part of the composite material component: The butterfly nut in the flipping mechanism (10) of the shaft pin positioning component (1) locks and unlocks to control two working positions. The flipping mechanism (10) is an off-the-shelf component. When the butterfly nut in the flipping mechanism (10) is loosened, it controls the first working position, which is the position for making way for installing the composite material component. When the butterfly nut in the flipping mechanism (10) is locked, it controls the second working position, which is the positioning position. It is mainly positioned by the retaining plate (1-2) and the end face of the connecting plate one (1-1), and tightened with the manual screw (1-4). The number of shaft pin positioning components (1) is 10, which mainly position the fork ear part of the composite material component to complete the positioning and clamping of 10 shaft pin positioning components (1); (5) Positioning and clamping of the rudder beam part of the composite material component: The positioning pin two (2-2) and the positioning block four (4-2) position the ribbed part of the composite material component, and lock with the locking handwheel two (2-5) and the locking handwheel four (4-4), and lock with the locking knurled nut two (2-3) and the locking knurled nut four (4-3). After the positioning and clamping of the ribbed part are completed, the components for positioning and clamping the ribbed part are 5 pressing and positioning components (2) and 1 positioning and locking component (4), with a total of 6 pieces, to complete the positioning and installation of the rudder beam part of the composite material; (6) Drilling of the composite material component: The drill templates one (13-1), two (13-2), three (13-3), four (13-4), and five (13-5) of the drill template component (13) are respectively installed on the bottom frame (8) by using the drilling connecting plate (13-9), support (9), base connecting plate (11), manual locking mechanism (13-6), and long pin positioning mechanism (13-7) for drilling work; After drilling, disassemble the drill templates one (13-1), two (13-2), three (13-3), four (13-4), five (13-5), drilling connecting plate (13-9), support (9), base connecting plate (11), manual locking mechanism (13-6), long pin positioning mechanism (13-7), etc. of the drill template component (13), and then carry out riveting work; After the riveting work is completed, open the wing nut in the shaft pin positioning component (1), open the flipping mechanism (10) along the rotating shaft, open the clamping mechanism (12) and the horizontal manual control mechanism (6-1), pull out the second positioning pin (2-2), the third positioning pin (3-4), and the fifth positioning pin (5-2), unscrew and remove the manual screw (1-4), the second locking handwheel (2-5), the second locking knurled nut (2-3), the fourth locking knurled nut (4-3), and the fourth locking handwheel (4-4), and remove the lower composite material component.

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