Main beam for aircraft, manufacturing method of main beam, mold and aircraft comprising main beam

Abstract

The invention provides a main beam for an aircraft, a manufacturing method of the main beam, a mold and the aircraft comprising the main beam. The main beam comprises a core material which is a closed rectangular frame in the cross section of the main beam; the edge strip laying layer is arranged on the inner side and / or the outer side of the core material and extends in the cross section of the main beam in the transverse direction; the web laying layer is arranged on the inner side and / or the outer side of the core material and extends in the longitudinal direction in the cross section of the main beam. The main beams and the core material are closed rectangular frames and have the characteristic of integration, the web plate laying layers and the edge strip laying layers are arranged on the two sides of the core material, plate splicing is not needed, the structural efficiency is greatly improved, and the overall structural weight is reduced on the premise that the strength, rigidity and stability are met.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular, to a main beam for an aircraft, a manufacturing method for a main beam for an aircraft, a mold, and an aircraft. Background Art

[0002] The main beam is a main component of the aircraft frame and needs to have a certain strength, toughness, and stiffness to withstand the full weight of the aircraft and various forces before and after flight.

[0003] Common main beams include circular tube main beams, truss main beams, and rectangular cross-section main beams. The wall panels of circular tube main beams all adopt laminated plate structures. Under the premise of meeting the strength, the stability is insufficient and it is easy to lose stability; for truss main beams, theoretically the structural efficiency is very high, but because a large number of short stringers need to be assembled, a large amount of assembly weight gain and assembly work are introduced, and assembly defects are likely to occur, resulting in extremely low actual structural efficiency and prone to quality accidents; the existing rectangular cross-section main beams are assembled by splicing foam sandwich structure plates, which are not easy to lose stability, but the plate splicing increases a large area of separation surfaces. To complete the assembly under the premise of meeting the connection strength, it is necessary to thicken and transition the laying area, which causes a large amount of weight gain and reduces the structural efficiency.

[0004] Therefore, it is necessary to propose a new technical solution to solve at least one of the above technical problems. Summary of the Invention

[0005] In order to overcome at least one aspect of the technical problems in the prior art, the present disclosure is proposed.

[0006] According to one aspect of an embodiment of the present disclosure, there is provided a main beam for an aircraft, including: a core material, which is a closed rectangular frame in the cross-section of the main beam; flange laminates, arranged on the inner side and / or the outer side of the core material, and extending transversely in the cross-section of the main beam; and web laminates, arranged on the inner side and / or the outer side of the core material, and extending longitudinally in the cross-section of the main beam.

[0007] According to another aspect of the embodiments of the present disclosure, a manufacturing method for a main beam of an aircraft is provided, including: providing a mold and a core material, the mold having an internal space with a rectangular cross-section, the mold including a plurality of modules, the plurality of modules including a horizontally extending top module, the core material having a closed rectangular frame cross-section, the core material including a plurality of core segments, the plurality of core segments including a horizontally extending top segment; laying at least one layer of prepreg cloth along the inner surfaces of the remaining modules of the mold except the top module, a portion of the at least one layer of prepreg cloth extending out of the inner surfaces of the remaining modules forming a first reserved section, each layer of the prepreg cloth including a ply and a bonding material; laying the remaining segments of the plurality of core segments except the top segment along the inner surface of the at least one layer of prepreg cloth; continuing to lay at least one layer of the prepreg cloth along the inner surface of the remaining segments, a portion of the at least one layer of prepreg cloth extending out of the inner surface of the remaining segments forming a second reserved section; arranging a support material inside the mold; laying the first reserved section on the surface of the support material, laying the top segment on the surface of the first reserved section, and laying the second reserved section on the surface of the top segment; installing the top module, and connecting each layer structure through the bonding material to form the main beam.

[0008] According to another aspect of the embodiments of the present disclosure, a mold for the above method is provided, the mold having an internal space with a rectangular cross-section, the mold including a plurality of modules, the plurality of modules including a horizontally extending top module and remaining modules.

[0009] According to another aspect of the embodiments of the present disclosure, an aircraft is provided, including the above main beam. Description of the Drawings

[0010] The above and other aspects and features of the present disclosure will be clearly presented from the following description of embodiments in conjunction with the drawings, where:

[0011] Figure 1 is a schematic cross-sectional view of a main beam of an aircraft according to an embodiment of the present disclosure;

[0012] Figure 2 is a schematic view of the splicing of the core material according to an embodiment of the present disclosure;

[0013] Figure 3 and Figure 4 is a schematic view of the mold according to an embodiment of the present disclosure;

[0014] Figure 5 shows a schematic view of the usage mode of the mold according to an embodiment of the present disclosure;

[0015] Figure 6Schematic diagram of a mold in a preparation state according to an embodiment of the present disclosure;

[0016] Figure 7 Schematic diagram of the first state of the main beam manufacturing process according to an embodiment of the present disclosure;

[0017] Figure 8 Is Figure 7 Partial enlarged view of;

[0018] Figure 9 Schematic diagram of the second state of the main beam manufacturing process according to an embodiment of the present disclosure;

[0019] Figure 10 Is Figure 9 Partial enlarged view of;

[0020] Figure 11 Schematic diagram of the third state of the main beam manufacturing process according to an embodiment of the present disclosure;

[0021] Figure 12 Schematic diagram of the fourth state of the main beam manufacturing process according to an embodiment of the present disclosure;

[0022] Figure 13 Schematic diagram of the fifth state of the main beam manufacturing process according to an embodiment of the present disclosure;

[0023] Figure 14 Schematic diagram of the sixth state of the main beam manufacturing process according to an embodiment of the present disclosure.

[0024] In the figure:

[0025] 1, core material; 2 - 4, web plies; 5 - 8, flange plies; 11, first section; 12, corner section; 13, second section; 14, first section; 15, second section; 16, corner section; 17, vertical end face; 18, inclined end face; 9, mold; 91, top module; 92, corner module; 93, side module; 94, bottom module; 95, side module; 96, corner module; 901, release cloth; 902, prepreg cloth; 903, isolation layer; 904, pressure bag; 905, inflatable bag; 906, support layer; 907, internal lap joint. Detailed implementation manners

[0026] The following description of the embodiments of the present disclosure with reference to the accompanying drawings is intended to explain the overall inventive concept of the present disclosure and should not be construed as a limitation to the present disclosure. All other embodiments obtained by those skilled in the art based on the embodiments in the present disclosure fall within the scope of protection of the present disclosure.

[0027] In an embodiment of the present disclosure, the main beam is a strip-shaped component with a length direction. When the main beam is cut by a plane perpendicular to its length direction, the resulting cross-section is the cross-section of the main beam. In an embodiment of the present disclosure, the transverse and longitudinal directions of the main beam are defined based on the position of the main beam during the level flight of the aircraft (see Figure 1 , the transverse direction is the "up" or "down" direction in the figure, and the longitudinal direction is the "left" or "right" direction in the figure). As those skilled in the art can understand, the main beam can be rotated 90° to define the transverse and longitudinal directions of the main beam. In the present disclosure, the "layer structure" may refer to the spar ply, the web ply, or the core material.

[0028] Figure 1 is a schematic diagram of the cross-section of the main beam for an aircraft according to an embodiment of the present disclosure. As Figure 1 shown, the main beam includes a core material 1, web plies 2-4, and spar plies 5-8. The core material 1 is a closed rectangular frame. Optionally, the above rectangular frame may include rounded corners. In an embodiment of the present disclosure, the core material 1 exhibits an integrated characteristic, and its thickness, strength, and other characteristics are substantially uniform in the closed direction. The core material 1 can be directly integrally formed or can be spliced by multiple core material sections, where the gaps are filled with bonding materials and are subjected to processes such as pressurization and temperature rise curing to achieve performance similar to that of integral forming (the strength at the section joint is not lower than the strength of the core material itself).

[0029] Figure 1 In, the web plies 2-4 and the spar plies 5-8 are arranged on the outside of the core material 1 in a laminated manner. The web plies 2-4 extend longitudinally, and the spar plies 5-8 extend transversely.

[0030] Figure 1 In, the web ply and the spar ply are also arranged on the inner side of the core material 1, and the distribution of the plies on both the inner and outer sides of the core material 1 is symmetric with respect to the core material 1. The reference numerals of the plies on the inner side of the core material 1 are omitted in the figure. In an alternative embodiment, the distribution of the plies on both the inner and outer sides of the core material 1 can be asymmetric. It is easy to understand that Figure 1 the cross-section of the main beam in is also a closed rectangular frame.

[0031] In an embodiment of the present disclosure, the web ply and the spar ply are used to provide structural strength and stiffness, and the core material is used to provide stability support to prevent the web ply and the spar ply from buckling. Further, the web ply can be used to provide torsional stiffness, and the spar ply can be used to provide bending stiffness. Exemplarily, the material of the core material is a foam material, such as PVC foam, PMI foam, etc., the material of the web ply is, for example, a woven fabric material, and the material of the spar ply is, for example, a unidirectional tape material. In addition, some of the spar plies can also use woven fabric, and each spar ply can include a ply containing unidirectional tape.

[0032] The number and position of the web ply and the spar ply are not limited toFigure 1 In such a case, it can be designed and adjusted according to actual requirements.

[0033] Figure 1 In [description], in the thickness direction of the rectangular frame, a bonding material is filled between adjacent layer structures. For example, a bonding material is provided between the core material 1 and the web ply 2, and a bonding material is provided between the web ply 2 and the web ply 3. The bonding material is used to connect different layer structures. Exemplarily, the bonding material is epoxy resin. In addition, other bonding materials can also be used.

[0034] In the embodiments of the present disclosure, in the closing direction of the rectangular frame, the flange ply and the corresponding web ply are butted or lapped at adjacent positions. Taking Figure 1 the web ply 2 and the flange ply 5 in [description] as an example, at their adjacent position (the upper left corner of the rectangular frame in the figure), the web ply 2 is located above the flange ply 5, forming a lapped structure. Taking Figure 1 the web ply 3 and the flange ply 8 in [description] as an example, at their adjacent position (the upper left corner of the rectangular frame in the figure), they are in the same layer and the ends are adjacent, forming a butted structure. When the flange ply and the web ply are made of the same material, they can adopt a butted structure, so that they can be formed using the same layer of prepreg cloth during the manufacturing process. When the flange ply and the web ply are made of the same material, they can also adopt an integral structure without setting seams.

[0035] Figure 1 In [description], all four corners of the core material 1 are rounded. In the closing direction of the rectangular frame, the joint between the flange ply and the web ply is spaced a certain distance from the rounded corner. For example, the joints between the web ply 2 and the flange ply 5, and the web ply 3 and the flange ply 8 in the above text are both located on the straight line segment outside the rounded corner, thus being spaced a certain distance from the rounded corner, which is beneficial to reducing the risk of defects caused by the rounded corner.

[0036] Figure 1 In [description], the flange ply located on the upper edge of the rectangular frame has an internal joint, and each flange ply is divided into multiple ply segments based on the internal joint. For example, the flange plies 5, 6, 7, and 8 all have internal joints in the form of laps in the central region, and each of the above flange plies is separated into two ply segments based on the corresponding internal joint. The internal joint of the flange ply is related to the manufacturing process of the main beam.

[0037] In an alternative embodiment, although not shown, the joint between different core material segments can be spaced a certain distance from the joint between the flange ply and the corresponding web ply, so that the core material seam and the ply seam are staggered in the closing direction of the rectangular frame, which is beneficial to improving the structural strength.

[0038] Figure 2 is a splicing schematic diagram of the core material according to an embodiment of the present disclosure. AsFigure 2 As shown in Figure 2 , the core material includes core material sections 11 - 16, where core material sections 11 and 14 are the first sections extending horizontally, core material sections 13 and 15 are the second sections extending longitudinally, and their lower ends have corner sections, and core material sections 12 and 16 are separate corner sections. The end faces of each core material section include two forms: vertical end faces (the end face is perpendicular to the adjacent surface) and inclined end faces (the end face is not perpendicular to the adjacent surface). Exemplarily, Figure 2 in Figure 2 , the end face 17 is a vertical end face, and the end face 18 is an inclined end face.

[0039] In Figure 2 , the vertical end faces are arranged on the upper edge of the rectangular frame, such as the two end faces of core material section 11, and the corresponding end faces of core material sections 12 and 16. Its function is to avoid bevel damage to the vacuum bag for vacuum pumping during the manufacturing process. The inclined end faces are arranged at the remaining positions, and their function is to reduce the seam gap between the core material sections on the premise of reducing the machining accuracy requirements. Further, as shown in Figure 2 , from the inside to the outside of the rectangular frame, the end face of core material section 14 is inclined in the direction that reduces the lateral width of the first section. During the manufacturing process, the above structure enables the flat core material section 14 to press against the corner parts of core material sections 13 and 15 when pressurized (see the pressurization direction in Figure 5 ), promoting the compression of the corner parts and reducing the risk of defects caused by insufficient compression of the corner parts.

[0040] The number of core material sections can be set according to actual needs. Exemplarily, in Figure 2 , core material sections 12 and 16 can be combined with core material sections 13 and 15 into a whole respectively. The corner sections of core material sections 13 and 15 can also be separated to become independent core material sections.

[0041] In Figure 2 , in order to match the airfoil of the wing, core material section 11 has a certain inclination angle relative to the horizontal direction. This feature is also shown in Figure 5 , and this feature is not shown in other drawings.

[0042] For the main beam in the embodiments of the present disclosure, the core material is a closed rectangular frame, which has the characteristic of integration. The web ply and flange ply are arranged on both sides of the core material, and there is no need for plate splicing, which greatly improves the structural efficiency and reduces the overall structural weight on the premise of meeting strength, stiffness, and stability.

[0043] The embodiments of the present disclosure also provide a manufacturing method for the main beam of an unmanned aerial vehicle, including the following steps:

[0044] Step 100, provide a mold and a core material. The mold has an internal space with a rectangular cross-section and includes a plurality of modules. The plurality of modules include a horizontally extending top module. The core material has a closed rectangular frame cross-section and includes a plurality of core material sections. The plurality of core material sections include a horizontally extending top section.

[0045] Figure 3 and Figure 4 are schematic views of a mold according to an embodiment of the present disclosure. As Figure 3 shown, the mold has an internal space with a rectangular cross-section and includes a horizontally extending top module 91 and the remaining modules. Figure 3 Among them, the top module 91 is in a separated state and the remaining modules are in a spliced state. As Figure 4 shown, each module is in a separated state, and the remaining modules other than the top module 91 are further divided into a bottom module 94, side modules 93, 95, and corner modules 92, 96.

[0046] The number of modules of the mold 9 can be set according to actual needs. In Figure 4 , the corner modules 92, 96 can be combined with the side modules 93, 95 into a whole respectively. In addition, the corner segments of the side modules 93, 95 can be separated to become independent modules.

[0047] By splitting the remaining modules into multiple modules, the difficulty of demolding the workpiece can be reduced, and the damage to the workpiece structure during the demolding process can be avoided.

[0048] In Figure 3 and Figure 4 , raised portions are further provided on the tops of the corner modules 92, 96, and the raised portions are used to place the reserved part of the prepreg cloth.

[0049] For the distribution of the core material sections in this embodiment, reference can be made to Figure 2 , where the core material section 11 is the top section.

[0050] Figure 5 shows a schematic view of the usage mode of a mold according to an embodiment of the present disclosure. As Figure 5 shown, when the mold 9 is in a spliced state, the core material 1 is surrounded inside (edge strip plies and web plies are also laid on both sides of the core material, which are omitted in the figure), and pressure is applied from the inside of the mold to the outside to compact the core material and other layer structures on the inner surface of the mold 9, so as to complete the manufacture of the main beam.

[0051] In an alternative embodiment, as Figure 5 shown, the horizontal length of the top section 11 of the core material 1 is less than the horizontal length of the top module 91. Thus, after laying the top section 11 of the core material 1, the joints at both ends of the top section 11 can be observed through the top opening of the mold 9, which is beneficial to timely detecting and handling defects. AsFigure 5 As shown, the end of the top section 11 is spaced apart from the corresponding top opening of the mold by a certain distance, for example, 3 mm to 5 mm (including the end values).

[0052] Figure 6 is a schematic view of a mold in a preparation state according to an embodiment of the present disclosure. As Figure 6 shown, before step 200, the mold is first assembled, and the seams between the modules are inspected. If the seams do not meet the requirements (for example, greater than a preset value, and the preset value is, for example, 0.2 mm), transition materials can be filled in the seams.

[0053] Step 200: Lay at least one layer of prepreg cloth along the inner surface of the remaining modules of the mold except the top module. The part of the at least one layer of prepreg cloth extending out of the inner surface of the remaining modules forms a first reserved section. Each layer of prepreg cloth includes a ply and a bonding material.

[0054] Exemplarily, the prepreg cloth is, for example, a carbon fiber prepreg cloth. The prepreg cloth may include a fabric and an epoxy resin, or include a unidirectional tape and an epoxy resin.

[0055] Figure 7 is a schematic view of the first state of the main beam manufacturing process according to an embodiment of the present disclosure, Figure 8 is Figure 7 a partial enlarged view of. As Figure 7 and Figure 8 shown, the following operations are performed based on the remaining modules of the mold excluding the top module. A release cloth 901 is provided at the edge of the protruding part of the corner module 96 to protect the prepreg cloth 902 from being scratched by the mold. The prepreg cloth 902 is laid on the inner surface of the mold. Among them, the part of the prepreg cloth 902 extending beyond the inner surface of the mold forms a first reserved section, and the first reserved section is laid on the outer surface of the corner module 96. An isolation layer 903 is laid on the surface of the first reserved section. After the above layer structure is laid, a vacuum treatment is performed to compact the laid layer structure on the surface of the mold.

[0056] The prepreg cloth 902 may correspond to the web ply or the flange ply, or correspond to both the web ply and the flange ply at the same time. When the prepreg cloth 902 corresponds to the flange ply, it is laid on the bottom of the inner surface of the mold. When the prepreg cloth 902 corresponds to the web ply, it is laid on the side of the inner surface of the mold. When the prepreg cloth 902 corresponds to both the web ply and the flange ply at the same time, it is laid on the entire inner surface of the mold.

[0057] In an alternative embodiment, as Figure 7 and Figure 8 shown, the end of the corner module 96 adapted to be docked with the top module is provided with a rounded corner, so as to prevent the end of the corner section from scratching the prepreg cloth 902.

[0058] Figure 9 It is a schematic diagram of the second state of the main beam manufacturing process according to an embodiment of the present disclosure. Figure 10 It is Figure 9 a partial enlarged view of.

[0059] As Figure 9 and Figure 10 shown, on the basis of the first state, a layer of prepreg cloth 902 and a release layer 903 are continuously laid. Among them, the previously laid release layer 903 can separate the first reserved sections of the two layers of prepreg cloth 902 to prevent them from connecting, so as to uncover the first reserved sections in subsequent steps. After the above-mentioned layer structure is laid, a vacuum treatment is carried out to compact the laid layer structure on the surface of the mold.

[0060] If more layers of prepreg cloth need to be laid, the steps described in the previous paragraph can be repeated.

[0061] As can be understood by those skilled in the art, the prepreg cloth laid in step 200 is used to form the web floating layer and the flange ply outside the core material.

[0062] Step 300, lay the remaining sections of the plurality of core material sections except the top section along the inner surface of at least one layer of prepreg cloth.

[0063] Figure 11 It is a schematic diagram of the third state of the main beam manufacturing process according to an embodiment of the present disclosure. As Figure 11 shown, lay the part of the core material 1 except the top section along the inner surface of the prepreg cloth laid in step 200.

[0064] After the core material 1 is laid, a vacuum treatment is carried out to compact the core material 1 and other laid layer structures on the surface of the mold.

[0065] Step 400, continue to lay at least one layer of prepreg cloth along the inner surface of the remaining section, and the part of the at least one layer of prepreg cloth extending out of the inner surface of the remaining section forms a second reserved section.

[0066] Figure 12 It is a schematic diagram of the fourth state of the main beam manufacturing process according to an embodiment of the present disclosure. As Figure 12 shown, continue to lay a layer of prepreg cloth 902 and a release layer 903 along the inner surface of the core material 1 laid in step 300, wherein the part of the prepreg cloth 902 extending out of the inner surface of the core material 1 forms a second reserved section. The release layer 903 is arranged on the surface of the second reserved section. If multiple layers of prepreg cloth are required, the above steps are repeated.

[0067] As can be understood by those skilled in the art, the prepreg cloth laid in step 400 is used to form the web ply and flange ply on the outside of the core material.

[0068] Step 500, arrange support materials inside the mold.

[0069] Figure 13 is a schematic diagram of the fifth state of the main beam manufacturing process according to an embodiment of the present disclosure. As Figure 13 shown, a pressure bag 904 is arranged inside the laid layer structure, and support materials are arranged inside the pressure bag 904. The support materials are used to support the top section 11 and the layer structures on both sides thereof. Optionally, the support materials include an inflatable bag 905 and a support layer 906. The inflatable bag 905 can play a filling role, and the support layer 906 can provide a rigid support surface.

[0070] Step 600, lay a first reserved section on the surface of the support materials, lay a top section on the surface of the first reserved section, and lay a second reserved section on the surface of the top section.

[0071] As Figure 13 shown, the first reserved section is laid layer by layer on the surface of the support layer 906 (the isolation layer between adjacent first reserved sections is removed), the top section 11 is laid on the surface of the first reserved section, and the second reserved section is laid layer by layer on the surface of the top section 11 (the isolation layer between adjacent second reserved sections is removed).

[0072] In step 600, as Figure 13 shown, the first reserved sections on both sides of the top opening of the mold are respectively laid on the surface of the support layer 906, so that the first reserved sections on both sides of the opening overlap at an adjacent part by a first preset length to form an internal overlapping part 907. Similarly, the second reserved sections on both sides of the top opening of the mold are respectively laid on the surface of the top section 11, and the second reserved sections on both sides of the opening overlap at an adjacent part by a second preset length. The first preset length and the second preset length may be the same or different. Exemplarily, the first preset length and the second preset length may take values in the range of 10 mm to 15 mm (including the end values).

[0073] Step 700, install the top module, and connect each layer structure through bonding materials to form the main beam.

[0074] Figure 14 is a schematic diagram of the sixth state of the main beam manufacturing process according to an embodiment of the present disclosure. As Figure 14 shown, on the basis of step 600, install the top module 91, remove the support materials and utilize the inflatable bag 905 (see Figure 13)Pressurize from the inside out to compact the laid layer structure as a whole. On this basis, the entire mold can be placed in an autoclave for further pressurization and heating, and the bonding agent is cooled and cured. In an alternative embodiment, before the entire mold is placed in the autoclave, the pressure applied by the inflatable bag can be maintained for a preset duration (e.g., 24 hours).

[0075] Embodiments of the present disclosure also provide a mold for use in the above manufacturing process. As Figures 3 - 6 shown, the mold has an internal space with a rectangular cross-section. As Figure 3 shown, the mold includes a top module 91 extending transversely and the remaining modules. As Figure 4 shown, the remaining modules other than the top module 91 are further divided into a bottom module 91, side modules 93, 95, and corner modules 92, 96.

[0076] In Figure 4 , the corner modules 92, 96 can be integrated with the side modules 93, 95 respectively. In addition, the corner segments of the side modules 93, 95 can be separated to form independent modules.

[0077] In an alternative embodiment, as Figure 7 and Figure 8 shown, the end of the corner module 96 adapted to dock with the top module is provided with a rounded corner, which can prevent the end of the corner segment from scratching the prepreg cloth 902.

[0078] Embodiments of the present disclosure also provide an aircraft including the above main beam.

[0079] For the specific details and technical effects of the mold and the aircraft in the embodiments of the present disclosure, reference can be made to the description of the main beam and its manufacturing method above, which will not be elaborated here.

[0080] Based on the above, the present disclosure proposes the following technical solutions:

[0081] 1. A main beam for an aircraft, comprising:

[0082] A core material, which is a closed rectangular frame in the cross-section of the main beam;

[0083] A flange laminate, arranged on the inner side and / or outer side of the core material, extending transversely in the cross-section of the main beam;

[0084] A web laminate, arranged on the inner side and / or outer side of the core material, extending longitudinally in the cross-section of the main beam.

[0085] 2. The main beam according to 1, wherein:

[0086] The stringer ply located at the upper edge of the rectangular frame has an internal joint, and each stringer ply is divided into a plurality of ply segments based on the internal joint.

[0087] 3. The main beam according to 2, wherein:

[0088] The adjacent ply segments overlap at the internal joint.

[0089] 4. The main beam according to 1, wherein:

[0090] In the closing direction of the rectangular frame, the stringer ply and the corresponding web ply butt or overlap at the adjacent position.

[0091] 5. The main beam according to 4, wherein:

[0092] The rectangular frame includes rounded corners, and in the closing direction of the rectangular frame, the joint between the stringer ply and the corresponding web ply is spaced apart from the rounded corners by a certain distance.

[0093] 6. The main beam according to 1, wherein:

[0094] The material of the stringer ply includes unidirectional tape; and / or

[0095] The material of the web ply includes fabric.

[0096] 7. The main beam according to 1, wherein:

[0097] In the thickness direction of the rectangular frame, joining materials are provided between adjacent layer structures.

[0098] 8. The main beam according to 1, wherein:

[0099] The layer structures on both the inner and outer sides of the rectangular frame are symmetrically distributed.

[0100] 9. The main beam according to 1, wherein:

[0101] The core material includes a plurality of core segments, and in the closing direction of the rectangular frame, different core segments are joined by joining materials.

[0102] 10. The main beam according to 9, wherein:

[0103] In the closing direction of the rectangular frame, the joint of different core segments is spaced apart from the joint of the stringer ply and the corresponding web ply by a certain distance.

[0104] 11. The main beam according to 9, wherein:

[0105] The plurality of core material sections include a first section extending laterally and a second section extending longitudinally, and at least one of the first sections and / or at least one of the second sections has an inclined end face.

[0106] 12. The main beam according to claim 11, wherein:

[0107] From the inner side to the outer side of the rectangular frame, the end face of at least one of the first sections is inclined in a direction that reduces the lateral width of the first section.

[0108] 13. The main beam according to claim 11, wherein:

[0109] The second section has a corner section; and / or

[0110] The plurality of core material sections further include a third section formed by a separate corner section.

[0111] 14. The main beam according to claim 11, wherein:

[0112] At least one of the first sections and / or at least one of the second sections has a vertical end face.

[0113] 15. A manufacturing method for a main beam of an aircraft, comprising:

[0114] Providing a mold and a core material, the mold having an internal space with a rectangular cross-section, the mold including a plurality of modules, the plurality of modules including a top module extending laterally, the cross-section of the core material being a closed rectangular frame, the core material including a plurality of core material sections, the plurality of core material sections including a top section extending laterally;

[0115] Laying at least one layer of prepreg cloth along the inner surfaces of the remaining modules of the mold except the top module, and the part of the at least one layer of prepreg cloth extending out of the inner surfaces of the remaining modules forms a first reserved section, and each layer of prepreg cloth includes a ply and a bonding material;

[0116] Laying the remaining sections of the plurality of core material sections except the top section along the inner surface of the at least one layer of prepreg cloth;

[0117] Continuing to lay at least one layer of the prepreg cloth along the inner surface of the remaining sections, and the part of the at least one layer of prepreg cloth extending out of the inner surface of the remaining sections forms a second reserved section;

[0118] Setting a support material inside the mold;

[0119] Laying the first reserved section on the surface of the support material, laying the top section on the surface of the first reserved section, and laying the second reserved section on the surface of the top section;

[0120] Install the top module and connect each layer structure through the bonding material to form the main beam.

[0121] 16. The method according to 15, wherein:

[0122] The length of the top section is less than the length of the top module.

[0123] 17. The method according to 15, wherein:

[0124] The remaining module includes a laterally extending bottom module and a longitudinally extending side module.

[0125] 18. The method according to 17, wherein:

[0126] The side module or the bottom module has a corner section; and / or

[0127] The remaining module further includes a corner module formed by a separate corner section.

[0128] 19. The method according to 18, wherein:

[0129] The end of the corner section adapted to dock with the top module is provided with a rounded corner.

[0130] 20. The method according to 15, wherein:

[0131] The first reserved section is laid on the surface of the mold, the second reserved section is laid on the surface of the first reserved section, and an isolation layer is provided between the second reserved section and the first reserved section.

[0132] 21. The method according to 15, wherein:

[0133] The remaining module has an opening corresponding to the top module, and the first reserved section and the second reserved section are reserved on both sides of the opening;

[0134] The step of "laying the first reserved section on the surface of the support material" includes: laying the first reserved sections on both sides of the opening on the surface of the support material respectively, so that the first reserved sections on both sides of the opening overlap at an adjacent position by a first preset length;

[0135] The step of "laying the second reserved section on the surface of the top section" includes: laying the second reserved sections on both sides of the opening on the surface of the top section respectively, and making the second reserved sections on both sides of the opening overlap at an adjacent position by a second preset length.

[0136] 22. The method according to 15, wherein:

[0137] After the step of "laying at least one layer of prepreg cloth on the inner surfaces of the remaining modules of the mold except the top module", the method further includes:

[0138] Performing a vacuum compaction treatment on the laid prepreg cloth.

[0139] 23. The method according to 15, wherein after the step of "laying the second reserved section on the surface of the top section", the method further includes:

[0140] Performing a vacuum compaction treatment on the entire laid layer structure.

[0141] 24. The method according to 23, wherein the performing a vacuum compaction treatment on the entire laid layer structure includes:

[0142] Maintaining the pressure after vacuuming for a preset duration.

[0143] 25. The method according to 15, wherein the connecting the respective layer structures by the bonding material includes:

[0144] Heating the bonding material and cooling and curing the bonding material.

[0145] 26. A mold for the method according to any one of 15 - 25, the mold having an internal space with a rectangular cross-section, the mold including a plurality of modules, the plurality of modules including a laterally extending top module and remaining modules.

[0146] 27. The mold according to 26, wherein:

[0147] The remaining modules include a laterally extending bottom module and longitudinally extending side modules.

[0148] 28. The mold according to 27, wherein:

[0149] The side module or the bottom module has a corner section; and / or

[0150] The remaining modules further include a corner module formed by a separate corner section.

[0151] 29. The mold according to 28, wherein:

[0152] The end of the corner section adapted to be docked with the top module is provided with a rounded corner.

[0153] 30. An aircraft, including a main beam according to any one of 1 - 14.

[0154] Although embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes may be made therein without departing from the principles and spirit of the invention, and the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A main beam for an aircraft, comprising: A core material, which is a closed rectangular frame in the cross section of the main beam; A cap strip ply is arranged on the inner side and / or the outer side of the core material and extends in the transverse direction in the cross section of the main beam; A web ply is disposed on the inner side and / or the outer side of the core material and extends in the longitudinal direction in the cross section of the main beam.

2. The main beam according to claim 1, wherein: The cap plies located at the upper edge of the rectangular frame have inner joints, and each of the cap plies is divided into a plurality of ply sections based on the inner joints.

3. The main beam according to claim 2, wherein: Adjacent said ply sections overlap at said interior joints.

4. The main beam according to claim 1, wherein: In the closing direction of the rectangular frame, the edge strip plies and the corresponding web plies are butted or overlapped at adjacent locations; or In the closing direction of the rectangular frame, the edge strip ply and the corresponding web ply are butted or overlapped at adjacent locations, the rectangular frame includes a rounded corner, and in the closing direction of the rectangular frame, the joint between the edge strip ply and the corresponding web ply is spaced a certain distance from the rounded corner.

5. The main beam according to claim 1, wherein: The material of the cap ply comprises unidirectional tape, and / or the material of the web ply comprises fabric; or In the thickness direction of the rectangular frame, bonding materials are provided between adjacent layer structures; or The layer structures on both sides of the rectangular frame are symmetrically distributed.

6. The main beam according to claim 1, wherein: The core material comprises a plurality of core material segments, and in the closing direction of the rectangular frame, different core material segments are joined by a joining material; or The core material comprises a plurality of core material segments, in the closing direction of the rectangular frame, different core material segments are joined by joining materials, and the joining points of different core material segments are spaced a certain distance from the joining points of the flange plies and the corresponding web plies; or The core material comprises a plurality of core material segments, in the closing direction of the rectangular frame, different core material segments are joined by joining materials, the plurality of core material segments comprise a first segment extending transversely, and a second segment extending longitudinally, at least one of the first segments and / or at least one of the second segments has an inclined end surface; or The core material comprises a plurality of core material segments, in the closing direction of the rectangular frame, different core material segments are joined by joining materials, the plurality of core material segments comprise a first segment extending transversely, and a second segment extending longitudinally, and from the inside to the outside of the rectangular frame, an end surface of at least one of the first segments is inclined in a direction that reduces the transverse width of the first segment; or The core material comprises a plurality of core material segments, in the closing direction of the rectangular frame, different core material segments are joined by joining materials, the plurality of core material segments comprise a first segment extending transversely, and a second segment extending longitudinally, the second segment has a corner segment and / or the plurality of core material segments further comprise a third segment formed by a separate corner segment; or The core material includes multiple core material segments. In the closing direction of the rectangular frame, different core material segments are joined by joining materials. The multiple core material segments include a first segment extending laterally and a second segment extending longitudinally. At least one of the first segments and / or at least one of the second segments has a vertical end face.

7. A method for manufacturing a main beam for an aircraft, comprising: A mold and a core material are provided, wherein the mold has an inner space with a rectangular cross section, the mold includes a plurality of modules, the plurality of modules include a transversely extending top module, the cross section of the core material is a closed rectangular frame, the core material includes a plurality of core material segments, the plurality of core material segments include a transversely extending top segment; Laying at least one layer of prepreg cloth along the inner surface of the remaining modules of the mold except the top module, the portion of the at least one layer of prepreg cloth extending out of the inner surface of the remaining modules forms a first reserved section, and each layer of the prepreg cloth includes a laying layer and a bonding material; Laying the remaining sections of the plurality of core material sections except the top section along the inner surface of the at least one layer of prepreg cloth; Continue to lay at least one layer of the prepreg cloth along the inner surface of the remaining section, and the portion of the at least one layer of the prepreg cloth extending out of the inner surface of the remaining section forms a second reserved section; Disposing a support material inside the mold; Laying the first reserved section on the surface of the supporting material, laying the top section on the surface of the first reserved section, and laying the second reserved section on the surface of the top section; The top module is installed, and the various layer structures are connected by the bonding material to form the main beam.

8. The method according to claim 7, wherein: The first reserved section is laid on the surface of the mold, the second reserved section is laid on the surface of the first reserved section, and an isolation layer is arranged between the second reserved section and the first reserved section.

9. The method according to claim 7, wherein: The remaining module has an opening corresponding to the top module, and the first reserved section and the second reserved section are reserved on both sides of the opening; The step of "laying the first reserved section on the surface of the supporting material" includes: laying the first reserved sections on both sides of the opening on the surface of the supporting material respectively, so that the first reserved sections on both sides of the opening overlap by a first preset length at adjacent locations; The step of "laying the second reserved section on the surface of the top section" includes: laying the second reserved sections on both sides of the opening on the surface of the top section respectively, and overlapping the second reserved sections on both sides of the opening at adjacent positions by a second preset length.

10. The method according to claim 7, wherein: After the step of "laying at least one layer of prepreg cloth along the inner surface of the remaining modules of the mold except the top module", the method further comprises: performing a vacuum compaction treatment on the laid prepreg cloth; and / or After the step of "laying the second reserved section on the surface of the top section", the method further comprises: performing a vacuum compaction process on the entire laid layer structure.

11. The method according to claim 10, wherein: The vacuuming and compacting of the entire laid layer structure includes: maintaining the vacuum pressure for a preset time; or The connecting of the various layer structures by the bonding material comprises: heating the bonding material and cooling and solidifying the bonding material.

12. A mold for use in the method according to any one of claims 7 to 11, the mold having an inner space with a rectangular cross section, the mold comprising a plurality of modules, the plurality of modules comprising a transversely extending top module and remaining modules.

13. The mold according to claim 12, wherein: The remaining modules include a bottom module extending laterally and a side module extending longitudinally; or The remaining modules include a bottom module extending transversely, and a side module extending longitudinally; the side module or the bottom module has a corner section, and / or the remaining modules further include a corner module formed by a separate corner section; or The remaining modules include a bottom module extending laterally and a side module extending longitudinally; the side module or the bottom module has a corner section, and / or the remaining modules also include a corner module formed by a separate corner section; the end of the corner section suitable for docking with the top module is provided with a rounded corner.

14. An aircraft comprising the main beam according to any one of claims 1-6.

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