An aircraft closed angle beam forming tool

Abstract

The present application belongs to the field of aviation composite material forming technology, and discloses a kind of aircraft closed angle beam forming tool.The aircraft closed angle beam forming tool sets forming assembly into thin-walled structure, reduces the volume and weight of tool, and further reduces the heat capacity of tool itself, ensures the cooling effect of closed angle beam, reduces internal stress, and improves the forming quality of closed angle beam;forming assembly and supporting assembly can be hoisted in blocks when demolding, so that the closed angle can be avoided when the tool is demolded, and extrusion and bumping of the closed angle beam during demolding can be avoided, reducing the damage of the closed angle beam during demolding, and further improving the quality of the product.

Description

Technical Field

[0001] This invention relates to the field of aerospace composite material molding technology, and in particular to a molding fixture for aircraft closed-angle beams. Background Technology

[0002] In the manufacturing process of aerospace composite beams, changes in the aircraft's aerodynamic surfaces result in closed-angle structures for the composite beam products. Furthermore, composite beam parts are generally slender, therefore the molding fixtures for composite beams are also slender. Typically, the length-to-width ratio of the steel molding fixture exceeds 10:1. Commonly used composite beam molding fixtures include hollow and solid structures. However, during use, hollow fixtures, under the combined effects of their own weight and vacuum pressure, are prone to causing excessive deformation of the composite beam, leading to dimensional deviations. Solid steel fixtures, on the other hand, affect the heat transfer rate, thus impacting the internal stress distribution of the composite beam and causing microcracks within the composite part, resulting in substandard product quality.

[0003] Therefore, there is an urgent need for a tooling for forming closed-angle beams for aircraft to solve the above problems. Summary of the Invention

[0004] The purpose of this invention is to provide a tooling for forming closed-angle beams of aircraft, which can reduce the heat capacity of the tooling itself, perform segmented demolding, and ensure the quality of the closed-angle surface.

[0005] To achieve this objective, the present invention adopts the following technical solution:

[0006] A forming fixture for an aircraft closed-angle beam is provided, comprising a forming assembly including a first forming part, a second forming part, and a plurality of connecting parts. Both the first forming part and the second forming part are L-shaped structures, with the bending angle of the L-shaped structure being the forming angle. The first forming part includes a first pressing part and a first protrusion, the first protrusion protruding from the bottom of the side of the first pressing part facing the second forming part and abutting against the second forming part. The second forming part includes a second pressing part and a second protrusion, the second protrusion protruding from the top of the side of the second pressing part facing the first forming part, the upper surface of the first protrusion abutting against the lower surface of the second protrusion. The plurality of connecting parts are threaded and connected to the first protrusion and the second protrusion.

[0007] A support assembly, detachably connected to the molding assembly, is supported between the first molded part and the second molded part;

[0008] A lifting assembly is attached above the molding assembly and is used to connect the molding assembly and an external lifting device.

[0009] As an optional solution for forming a closed-angle beam for aircraft, the second protrusion is spaced apart from the first forming part by a distance of 0.4mm-1mm.

[0010] As an optional solution for the forming tooling of the aircraft closed-angle beam, the thickness of the first protrusion and the second protrusion are both greater than 20 mm, and the width of the first protrusion and the second protrusion are both greater than 35 mm.

[0011] As an optional solution for the forming tooling of the aircraft closed-angle beam, the first forming part further includes a first lifting part, which is connected to the end of the first pressing part away from the first protrusion at a forming angle. The second forming part further includes a second lifting part, which is connected to the end of the second pressing part away from the second protrusion at a forming angle. Multiple reinforcing ribs are provided between the first lifting part and the first pressing part, and between the second lifting part and the second pressing part.

[0012] As an optional solution for the forming tooling of aircraft closed-angle beams, the support assembly includes a first connecting part, a second connecting part, a third connecting part, and a support member. The first connecting part is connected to the first lifting part, the second connecting part is connected to the second lifting part, the third connecting part is connected to the first forming part and the second forming part, and the support member is connected between the first connecting part, the second connecting part, and the third connecting part.

[0013] As an optional solution for the forming tooling of aircraft closed-angle beams, the first forming part is provided with a first positioning hole, the third connecting part is provided with a second positioning hole, and the support assembly also includes a positioning element, which passes through the first positioning hole and the second positioning hole.

[0014] As an optional solution for aircraft closed-angle beam forming tooling, the support assembly also includes a lifting ring structure, which is connected to the top of the first connecting part and the second connecting part.

[0015] As an optional solution for the aircraft closed-angle beam forming fixture, the aircraft closed-angle beam forming fixture further includes a lifting assembly. The lifting assembly includes a first fixing member, a second fixing member, and a lifting member. The first fixing member includes a fixing part and a lifting part. The fixing part is connected to the first forming part. The lifting part is located above the second forming part. The lifting part is provided with a through hole. The second fixing member is fixed to the second forming part. A portion of the second fixing member is located between the lifting part and the second forming part. The second fixing member is provided with a threaded hole. The lifting member passes through the through hole and is threadedly connected to the threaded hole.

[0016] As an optional solution for aircraft closed-angle beam forming tooling, the lifting assembly is characterized in that it further includes a limiting member, which is disposed between the second fixing member and the lifting part.

[0017] As an optional solution for aircraft closed-angle beam forming tooling, the limiting component is equipped with a handle.

[0018] The beneficial effects of this invention are:

[0019] This invention provides a molding fixture for an aircraft closed-angle beam. The molding assembly includes a first molding part and a second molding part, both of which are L-shaped. The bending angle of the first molding part and the second molding part is the molding angle of the closed-angle beam. It is used for the laying and curing of composite materials. The first protrusion and the second protrusion can abut against each other. Multiple connecting parts are connected to the first protrusion and the second protrusion through the connection, so that the first molding part and the second molding part can be fixed, ensuring the connection stability of the molding assembly during molding. Furthermore, the support assembly is supported between the first molding part and the second molding part to further ensure the structural stability of the molding assembly and the quality of the closed-angle surface. When molding is completed, the first molding part and the second molding part can be lifted separately by the lifting assembly to achieve demolding. The aircraft closed-angle beam forming fixture features a thin-walled structure for the forming components, reducing the fixture's volume and weight, thereby reducing its own heat capacity, ensuring effective cooling of the closed-angle beam, reducing internal stress, and improving the forming quality of the closed-angle beam. The forming components and support components can be transported separately during demolding, allowing the fixture to avoid the closed-angle angle during demolding, preventing squeezing and bumping of the closed-angle beam, reducing damage to the closed-angle beam during demolding, and further improving product quality. Attached Figure Description

[0020] Figure 1 This is a diagram showing the composition of the aircraft closed-angle beam forming fixture provided by the present invention;

[0021] Figure 2 This is a cross-sectional view of the first and second forming parts of the aircraft closed-angle beam forming fixture provided by the present invention.

[0022] Figure 3 yes Figure 2 Enlarged view of point C in the middle;

[0023] Figure 4 This is an exploded view of the forming component of the aircraft closed-angle beam forming tooling provided by the present invention;

[0024] Figure 5 This is a schematic diagram of the structure of the first forming part of the aircraft closed-angle beam forming tooling provided by the present invention.

[0025] Figure 6 This is a schematic diagram of the forming component of the aircraft closed-angle beam forming tooling provided by the present invention.

[0026] Figure 7 This is a schematic diagram of the structure of the support component of the aircraft closed-angle beam forming fixture provided by the present invention;

[0027] Figure 8 This is a cross-sectional view of the support component of the aircraft closed-angle beam forming fixture provided by the present invention;

[0028] Figure 9 This is an exploded view of the lifting assembly of the aircraft closed-angle beam forming fixture provided by the present invention.

[0029] Figure 10 This is an assembly diagram of the lifting assembly and forming assembly of the aircraft closed-angle beam forming fixture provided by the present invention.

[0030] Figure 11 This is a schematic diagram of the lifting assembly of the aircraft closed-angle beam forming fixture provided by the present invention.

[0031] In the picture:

[0032] 100. Molding component; 110. First molded part; 111. First pressing section; 112. First protrusion; 113. First lifting section; 120. Second molded part; 121. Second pressing section; 122. Second protrusion; 123. Second lifting section; 130. Connector; 131. Connecting pin; 132. Connecting bolt; 133. Bushing; 134. Wire thread insert; 140. Reinforcing rib; 141. Supporting rib; 142. Lifting rib; 150. First reference hole; 160. Second reference hole;

[0033] 200, Support assembly; 210, First connecting part; 220, Second connecting part; 230, Third connecting part; 240, Support member; 250, Positioning member; 260, Lifting ring structure; 261, Lifting plate; 262, Lifting ring; 270, Shape-holding member;

[0034] 300. Lifting assembly; 310. Lifting beam; 320. Lifting connector;

[0035] 400, Lifting assembly; 410, First fixing member; 411, Fixing part; 412, Lifting part; 413, Through hole; 420, Second fixing member; 430, Lifting member; 440, Limiting member; 441, Handle. Detailed Implementation

[0036] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0037] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0038] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0039] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0040] like Figures 1 to 11 As shown, the aircraft closed-angle beam forming fixture of this embodiment includes a forming component 100 and a plurality of connecting parts 130. The forming component 100 is used for pressing the closed-angle beam and includes a first forming part 110, a second forming part 120, and a plurality of connecting parts 130. Both the first forming part 110 and the second forming part 120 are L-shaped structures, and the bending angle of the L-shaped structure is the forming angle. That is, the contour shape of the outer side and bottom surface of the first forming part 110 and the second forming part 120 matches the shape of the closed-angle beam to be manufactured, so as to allow the composite material to be laid and cured. By setting the first forming part 110 and the second forming part 120 as L-shaped structures, the forming component 100 forms a thin-walled structure, reducing the volume and weight of the fixture, thereby reducing the heat capacity of the fixture itself, ensuring the cooling effect of the closed-angle beam, reducing internal stress, and improving the forming quality of the closed-angle beam.

[0041] The molding assembly 100 is configured as a first molding part 110 and a second molding part 120 that are separate from each other, so that the first molding part 110 and the second molding part 120 can be lifted and transported separately during demolding. This allows the tooling to avoid the closed angle during demolding, prevents the closed angle beam from being squeezed and bumped during demolding, reduces the damage to the closed angle beam during demolding, and further improves the quality of the product.

[0042] Specifically, the first molding part 110 includes a first pressing part 111 and a first protrusion 112. The first protrusion 112 protrudes from the bottom of the side of the first pressing part 111 facing the second molding part 120 and abuts against the second molding part 120. The second molding part 120 includes a second pressing part 121 and a second protrusion 122. The second protrusion 122 protrudes from the top of the side of the second pressing part 121 facing the first molding part 110. The upper surface of the first protrusion 112 abuts against the lower surface of the second protrusion 122. A plurality of connectors 130 are inserted and connected to the first protrusion 112 and the second protrusion 122, so that the first molding part 110 and the second molding part 120 can be well fixed, ensuring the connection stability of the molding assembly 100 during pressing.

[0043] In this embodiment, to ensure the molding accuracy of the molding surface, the height difference between the bottom surface of the first protrusion 112 and the bottom surface of the second molding part 121 is no greater than 0.1 mm, thereby ensuring the flatness of the molding surface and thus ensuring the flatness requirement of the surface after the closed-angle beam is formed. For example, the height difference between the bottom surface of the first protrusion 112 and the bottom surface of the second molding part 121 is 0.02 mm, 0.05 mm, 0.08 mm, 0.1 mm, etc. Furthermore, the contact surfaces of the first protrusion 112 and the second molding part 121 cannot achieve complete alignment, resulting in processing error gaps. To ensure a tight contact and prevent the molding composite material from entering these gaps, the width of the contact gap is controlled to be no greater than 0.1 mm, further improving the molding quality of the closed-angle beam. For example, the width of the contact gap between the first protrusion 112 and the second molding part 121 is 0.02 mm, 0.05 mm, 0.08 mm, 0.1 mm, etc.

[0044] Optionally, the second protrusion 122 is spaced apart from the first molding portion 111 by a distance of 0.4mm-1mm. This provides adjustment space for common uncontrollable manufacturing factors such as manufacturing tolerances and stress release, offsetting the impact of local manufacturing conditions on the mold closing process and improving the manufacturing feasibility of the first molded part 110 and the second molded part 120. For example, the distance between the second protrusion 122 and the first molding portion 111 is 0.4mm, 0.6mm, 0.8mm, 1mm, etc.

[0045] Furthermore, the first molded part 110 also includes a first lifting part 113, which is connected at a forming angle to the end of the first pressing part 111 away from the first protrusion 112. The second molded part 120 also includes a second lifting part 123, which is connected at a forming angle to the end of the second pressing part 121 away from the second protrusion 122. Multiple reinforcing ribs 140 are provided between the first lifting part 113 and the first pressing part 111, and between the second lifting part 123 and the second pressing part 121, thereby ensuring the structural strength of the first molded part 110 and the second molded part 120, preventing deformation under external load, and extending the service life of the tooling.

[0046] Preferably, the multiple reinforcing ribs 140 include multiple supporting ribs 141 and multiple hoisting ribs 142. The supporting ribs 141 are used to connect with the supporting assembly 200 to enhance the supporting effect of the supporting assembly 200 during forming. The hoisting ribs 142 are used to connect with the hoisting assembly 300 to ensure safety during hoisting.

[0047] It should be noted that during the demolding process, in order to reduce the squeezing and collision between the first molded part 110 and the second molded part 120 and the closed-angle beam, such as Figure 3 As shown, the contact surfaces of the first protrusion 112 and the second molding portion 121, as well as the two opposing surfaces of the second protrusion 122 and the first molding portion 111, are all set as inclined surfaces, and the inclination angle A is less than the maximum closed angle B of the composite beam. This facilitates the removal of the second molded part 120 from between the closed angle beam and the first molded part 110 along the inclined surface during demolding. In this embodiment, the difference between the angle A of the inclined surface and the maximum closed angle B of the composite beam is 3°-6°. For example, the difference between A and B can be set to 3°, 4°, 5°, 6°, etc.

[0048] The molding process involves the following four different operating conditions:

[0049] (1) In the hot autoclave forming process, double pressure is applied inside the bag and inside the can, and its own weight is applied. The bottom plane is in sliding contact, and the main positioning hole of the mold surface is a fixed constraint. The analysis results should ensure that the maximum stress is less than 20% of the material yield stress and the maximum strain is less than the theoretical profile of the tooling surface.

[0050] (2) Preforming condition: Under the support of supporting components, preforming pressure and its own weight are applied. The maximum stress must be less than 20% of the material yield stress and the maximum strain must be less than the theoretical profile of the tooling surface.

[0051] (3) During the lifting operation, when the profile is connected to the support components, apply a load of twice the gravity. The analysis results should ensure that the maximum stress is less than 40% of the material's elastic limit stress.

[0052] (4) In the static condition, the support components are fixed and a load of twice the gravity is applied. The analysis results should ensure that the material yield stress is 20% and the maximum strain is less than the theoretical profile of the tooling surface.

[0053] To ensure that the molding assembly 100 has good structural strength under all working conditions, in this embodiment, the thickness of the first molding part 111 and the second molding part 121 is greater than 40mm, and the thickness of the first protrusion 112 and the second protrusion is the same and greater than 20mm, so that the molding assembly 100 has good rigidity when there are no supporting members inside; the thickness of the first lifting part 113 and the second lifting part 123 is greater than 30mm, the thickness of the reinforcing rib 140 is greater than 15mm, and the interval between two adjacent reinforcing ribs 140 is not greater than 1000mm, to ensure the structural strength of the molding assembly during lifting.

[0054] Furthermore, referring to Figure 4 As shown, the multiple connectors 130 include multiple connecting pins 131 and multiple connecting bolts 132. Multiple connecting holes are provided on both the first protrusion 112 and the second protrusion 122. The connecting pins 131 can be inserted into the connecting holes to achieve positioning between the first protrusion 112 and the second protrusion 122. A bushing 133 is provided around the connecting pin 131 to ensure its structural strength and extend its service life. A wire thread insert 134 is provided in some of the connecting holes, and the connecting bolts 132 can be threadedly connected to the wire thread insert 134 to fix the first protrusion 112 and the second protrusion 122, enhancing the threaded connection strength and facilitating replacement.

[0055] Optionally, the width of the first protrusion 112 and the second protrusion 122 is not less than 35mm, such that the distance between the center of the connecting hole and the edge of the first protrusion 112, and the distance between the center of the connecting hole and the edge of the second protrusion 122, are greater than 1.5 times the diameter of the connecting hole, ensuring the structural strength of the first protrusion 112 and the second protrusion 122, and thus ensuring the service life of the first protrusion 112 and the second protrusion 122. For example, the width of the first protrusion 112 and the second protrusion 122 can be set to 35mm, 36mm, 40mm, etc.

[0056] Furthermore, referring to Figure 6As shown, a first reference hole 150 is provided on the molding surface of the molding component 100, and a second reference hole 160 is provided on the outer wall surface of the first lifting part 113 and the second lifting part 123. When the molding surface is placed upwards, both the first reference hole 150 and the second reference hole 160 can be used to collect and measure data. When the molding surface is placed downwards, a coordinate system can be established using the second reference hole 160 to establish reference coordinates for the molding component 100 at different placement angles, facilitating dimensional inspection during closed-angle beam molding. Optionally, both the first reference hole 150 and the second reference hole 160 are provided with shoulder bushings to ensure hole diameter accuracy and usage accuracy. The measured coordinate values ​​of the references need to be marked on an appropriate area of ​​the tooling using labels. The measured values ​​are used for tooling inspection to establish a coordinate system, and the labels facilitate replacement and updates.

[0057] Continue to refer to Figure 7 and Figure 8 As shown, the aircraft closed-angle beam forming fixture provided in this embodiment also includes a support component 200. The support component 200 is detachably connected between the first forming part 110 and the second forming part 120. In the preforming process, under the action of the preforming pressure applied to the forming component 100 and the weight of the aircraft closed-angle beam forming fixture itself, the support component 200 is supported between the first forming part 110 and the second forming part 120, ensuring the structural stability of the forming component 100 and realizing the stable forming of the closed-angle beam.

[0058] Specifically, the support assembly 200 includes a first connecting portion 210, a second connecting portion 220, a third connecting portion 230, and multiple support members 240. The first connecting portion 210 is connected to the first lifting portion 113, the second connecting portion 220 is connected to the second lifting portion 123, and the third connecting portion 230 is connected to the first forming portion 111 and the second forming portion 121. The multiple support members 240 are spaced apart from each other and connected between the first connecting portion 210, the second connecting portion 220, and the third connecting portion 230, thereby forming a stable support. In this embodiment, the first connecting portion 210 and the first lifting portion 113, the second connecting portion 220 and the second lifting portion 123, the third connecting portion 230 and the first forming portion 111, and the third connecting portion 230 and the second lifting portion 123 are all bolted together, resulting in a simple structure and easy installation.

[0059] In actual production, due to the structural diversity of closed-angle beams, the first connecting part 210 and the second connecting part 220 are set at an angle. Therefore, the support assembly 200 also includes a shaping member 270, which is connected between the ends of the first connecting part 210 and the second connecting part 220 that are close to each other, thereby providing local support for the small end structure of the support assembly 200, improving the structural strength of the support assembly 200, and preventing local indentation when force is applied.

[0060] Furthermore, the first molding part 111 is provided with a first positioning hole, the third connecting part 230 is provided with a second positioning hole, and the support assembly 200 also includes a positioning member 250, which passes through the first positioning hole and the second positioning hole, thereby realizing the positioning of the support assembly 200 and the molding assembly 100, and facilitating the quick assembly and installation of the support assembly 200 and the molding assembly 100.

[0061] Furthermore, the support assembly 200 also includes a lifting ring structure 260, which is connected to the top of the first connecting portion 210 and the second connecting portion 220. Specifically, the lifting ring structure 260 includes a lifting plate 261 and lifting rings 262. The lifting plate 261 is connected to the top of the first connecting portion 210 and the second connecting portion 220, and multiple lifting rings 262 are distributed on the outside of the first connecting portion 210 and the second connecting portion 220. The lifting rings 262 can be connected to lifting equipment for lifting and transferring the support assembly 200.

[0062] Continue to refer to Figure 9 and Figure 10 As shown, the aircraft closed-angle beam forming fixture also includes a lifting assembly 400. The lifting assembly 400 includes a first fixing member 410, a second fixing member 420, and a lifting member 430. The first fixing member 410 includes a fixing part 411 and a lifting part 412. The fixing part 411 is connected to the first forming part 111, and the lifting part 412 is located above the second forming part 121. The lifting part 412 is provided with a through hole 413. The second fixing member 420 is fixed to the second forming part 121. Part of the second fixing member 420 is located between the lifting part 412 and the second forming part 121. The second fixing member 420 is provided with a threaded hole. The lifting member 430 passes through the through hole 413 and is threadedly connected to the threaded hole. By setting up the lifting component 400, when demolding is completed after molding, the lifting component 430 is rotated to gradually lift the second fixing component 420, thereby slowly separating the first molding component 110 and the second molding component 120, reducing the probability of collision with the closed angle beam due to excessive movement during demolding, and improving the quality of the product.

[0063] Optionally, the lifting assembly 400 is connected to the reinforcing rib 140, ensuring not only a reliable connection but also effective force application. Furthermore, the length and height of the first fixing member 410 and the second fixing member 420 are both less than 200mm, saving installation space and reducing manufacturing costs.

[0064] Preferably, the center line of the threaded hole 413 is set parallel to the inclined surface of the second protrusion 122, so that when the second protrusion 122 is lifted, the second protrusion 122 can tilt at a certain angle away from the closed angle beam, further avoiding bumps and scratches to the product and ensuring the quality of the product.

[0065] Furthermore, the lifting assembly 400 also includes a limiting member 440, which is disposed between the second fixing member 420 and the lifting part 412 to limit the stroke of the second fixing member 420. The thickness of the limiting member 440 can be adjusted according to usage requirements. Optionally, the limiting member 440 is provided with a handle 441 for easy hand assembly.

[0066] Continue to refer to Figure 11 As shown, the lifting assembly 300 is connected above the molding assembly 100 and is used to connect the molding assembly 100 and the external lifting device to ensure that the molding assembly 100 does not undergo excessive deformation during the segmented demolding and segmented hoisting processes, so as to protect the stability of the molding assembly 100.

[0067] Specifically, the lifting assembly 300 includes a lifting beam 310 and lifting connectors 320. Multiple lifting connectors 320 are evenly distributed on the lifting beam 310. The lifting connectors 320 are connected to the forming assembly 110 to realize the lifting of the forming assembly 100.

[0068] The specific steps for using the aircraft closed-angle beam forming fixture provided in this embodiment are as follows:

[0069] The first step is to clean, position, and securely connect the molding component 100 and the support component 200 on the platform. The platform needs to be properly protected to prevent the molding component 100 from being scratched.

[0070] The second step is to connect the support component 200 to the molding component 100;

[0071] The third step involves using molding component 100 to prepare and mold composite beams, and completing tooling status checks, drilling, and cleaning.

[0072] Fourth step, install the lifting assembly 400 to loosen the second molding part 120 from the first molding part 110;

[0073] Fifth step: Using the lifting assembly 300 in conjunction with the workshop overhead crane, lift and demold the second molded part 120 and the first molded part 110 in sequence and place them on the designated plane;

[0074] Step 6: Clean the tooling, assemble and connect, and repeat steps 2 to 5 to enter the next work cycle. When the molding work is completed, put it into the warehouse and seal it.

[0075] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A tooling for forming a closed-angle beam of an aircraft, characterized in that, include: A molding assembly (100) includes a first molding part (110), a second molding part (120), and a plurality of connecting parts (130). Both the first molding part (110) and the second molding part (120) are L-shaped structures, with the bending angle of the L-shaped structure being the molding angle. The first molding part (110) includes a first forming portion (111) and a first protrusion (112). The first protrusion (112) protrudes from the first forming portion (111) and faces the second molding part (120). The bottom of the first protrusion (112) abuts against the second molded part (120). The second molded part (120) includes a second pressed part (121) and a second protrusion (122). The second protrusion (122) protrudes from the top of the side of the second pressed part (121) facing the first molded part (110). The upper surface of the first protrusion (112) abuts against the lower surface of the second protrusion (122). A plurality of the connecting members (130) are connected to the first protrusion (112) and the second protrusion (122). A support assembly (200) is detachably connected between the first molded part (110) and the second molded part (120); A lifting assembly (300) is connected above the molding assembly (100) and is used to connect the molding assembly (100) and an external lifting device; The aircraft closed-angle beam forming fixture also includes a lifting assembly (400), which includes a first fixing member (410), a second fixing member (420), and a lifting member (430). The first fixing member (410) includes a fixing part (411) and a lifting part (412). The fixing part (411) is connected to the first forming part (111). The lifting part (412) is located above the second forming part (121). The lifting part (412) is provided with a through hole (413). The second fixing member (420) is fixed to the second forming part (121). Part of the second fixing member (420) is located between the lifting part (412) and the second forming part (121). The second fixing member (420) is provided with a threaded hole. The lifting member (430) passes through the through hole (413) and is threadedly connected to the threaded hole.

2. The aircraft closed-angle beam forming fixture according to claim 1, characterized in that, The second protrusion (122) is spaced apart from the first molding part (111) by a distance of 0.4mm-1mm.

3. The aircraft closed-angle beam forming fixture according to claim 1, characterized in that, The thickness of the first protrusion (112) and the second protrusion (122) is greater than 20 mm, and the width of the first protrusion (112) and the second protrusion (122) is greater than 35 mm.

4. The aircraft closed-angle beam forming fixture according to claim 1, characterized in that, The first molded part (110) further includes a first lifting part (113), which is connected to the end of the first pressing part (111) away from the first protrusion (112) at the molding angle. The second molded part (120) further includes a second lifting part (123), which is connected to the end of the second pressing part (121) away from the second protrusion (122) at the molding angle. Multiple reinforcing ribs (140) are provided between the first lifting part (113) and the first pressing part (111) and between the second lifting part (123) and the second pressing part (121).

5. The aircraft closed-angle beam forming fixture according to claim 4, characterized in that, The support assembly (200) includes a first connecting part (210), a second connecting part (220), a third connecting part (230), and a support member (240). The first connecting part (210) is connected to the first hoisting part (113), the second connecting part (220) is connected to the second hoisting part (123), the third connecting part (230) is connected to the first forming part (111) and the second forming part (121), and the support member (240) is connected between the first connecting part (210), the second connecting part (220), and the third connecting part (230).

6. The aircraft closed-angle beam forming fixture according to claim 5, characterized in that, The first forming part (111) is provided with a first positioning hole, the third connecting part (230) is provided with a second positioning hole, and the support assembly (200) further includes a positioning member (250), which passes through the first positioning hole and the second positioning hole.

7. The aircraft closed-angle beam forming fixture according to claim 5, characterized in that, The support assembly (200) also includes a lifting ring structure (260) connected to the top of the first connecting portion (210) and the second connecting portion (220).

8. The aircraft closed-angle beam forming fixture according to claim 1, characterized in that, The lifting assembly (400) further includes a limiting member (440) disposed between the second fixing member (420) and the lifting part (412).

9. The aircraft closed-angle beam forming fixture according to claim 8, characterized in that, The limiting member (440) is provided with a handle (441).

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