CN115503260A - Core material filling method - Google Patents
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- CN115503260A CN115503260A CN202210991153.1A CN202210991153A CN115503260A CN 115503260 A CN115503260 A CN 115503260A CN 202210991153 A CN202210991153 A CN 202210991153A CN 115503260 A CN115503260 A CN 115503260A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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- Chemical & Material Sciences (AREA)
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- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The application relates to the technical field of composite material parts, and particularly discloses a core material filling method, which comprises the following steps: determining the core material filling amount of a filling area of a composite material part according to the composite material part formed by combining a plurality of sub-parts; according to the core material filling amount, paving prepreg on a male die of a forming tool layer by layer to form a first core material layer on the male die, and paving prepreg on a female die of the forming tool layer by layer to form a second core material layer on the female die; performing the first core material layer and the second core material layer to respectively obtain an inner edge filling core material and an outer edge filling core material; and filling the variable-curvature outer edge filling area and the variable-curvature inner edge filling area of the composite material part respectively by using the outer edge filling core material and the inner edge filling core material. The application solves the technical problem that the filling quality of the variable-curvature core material is poor in the prior art.
Description
Technical Field
The application relates to the technical field of composite material parts, in particular to a core material filling method.
Background
At present, the composite material is widely applied to airplanes, the dosage ratio of the composite material is an important index for measuring the advancement of the airplanes, and the composite material is increasingly applied in the field of aviation by virtue of the excellent overall design. In order to avoid stress concentration in the corner region, the composite material member is usually designed to have an R-angle transition, and after the sub-members with the R-angle are combined into an integral structure, an inherent gap is formed in the R-region. In engineering, the gap region needs to be filled with a core material with a corresponding size. In the prior art, the fiber continuity of core material filling is often ensured only when the axial direction (X direction) of the core material has no curvature change, and the core material is easy to bend or cut aiming at the filling of the core material with variable curvature in the axial direction, so that the core material has fiber accumulation wrinkles or fiber fracture discontinuity, the original structure of the core material is damaged, and the mechanical property of a product is reduced, and the internal layering defect or the surface quality defect is caused.
The above is only for the purpose of assisting understanding of the technical solutions of the present application, and does not represent an admission that the above is prior art.
Disclosure of Invention
The application mainly aims to provide a core material filling method, and aims to solve the technical problem that in the prior art, the filling quality of a variable-curvature core material is poor.
The invention relates to a core material filling method with variable curvature in the axial direction, which improves the filling quality of an R-angle core material at a large-curvature corner.
In order to achieve the above object, the present application provides a core material filling method, including the steps of:
determining the core material filling amount of a filling area of a composite material part according to the composite material part formed by combining a plurality of sub-parts; the filling area is an area to be filled formed by combining R angles of a plurality of sub-pieces, and the area to be filled comprises a variable-curvature outer edge filling area and a variable-curvature inner edge filling area;
according to the core material filling amount, laying prepreg on a male die of a forming tool layer by layer to form a first core material layer on the male die; wherein the shape of the male die is matched with that of the variable-curvature outer edge filling area;
according to the filling amount of the core material, laying prepreg on a female die of a forming tool layer by layer to form a second core material layer on the female die; wherein the shape of the female die is matched with that of the variable-curvature inner edge filling area;
performing the first core material layer and the second core material layer to respectively obtain an inner edge filling core material and an outer edge filling core material;
and filling the variable-curvature outer edge filling area and the variable-curvature inner edge filling area of the composite material part respectively by using the outer edge filling core material and the inner edge filling core material.
Further, according to the core material filling amount, the core material is paved on a male mold layer by layer to form a first core material layer on the male mold, and the method comprises the following steps: obtaining the number n of layers and the total width W of the first core material layer according to the filling amount of the core materials; designing the layer-by-layer width W according to the layer number n and the total width W of the pavement 1 、w 2 、w 3 ……w n Said w is 1 、w 2 、w 3 ……w n The width of the 1 st layer of ply, the width of the 2 nd layer of ply and the width of the 3 rd layer of ply … … of the nth layer of ply are respectively; according to the layer-by-layer width w 1 、w 2 、w 3 ……w n And laying up layer by layer on a male mold to form a first core layer on the male mold.
Further, the sectional area J of the filling area is calculated by the formula: j =2R 2 -πR 2 the/2,R is the radius in the Y-Z plane of the core material.
Further, a calculation formula of the number n of the first core material layer and the second core material layer is as follows: n = R/σ, σ being the single prepreg thickness.
Further, the calculation formula of the total filling width W of the core material is as follows: w = KJ/σ, K is a correction coefficient.
Further, a layer-by-layer width w 1 、w 2 、w 3 ……w n And the ratio of two adjacent numerical values satisfies an equal difference relation.
Further, the region to be filled also comprises a non-curvature filling region; the method further comprises the following steps: filling the non-curvature filled region with a non-curvature core material.
Furthermore, the curvature-free core material and the curvature-variable core material are spliced in an inclined plane.
Optionally, the forming tool further comprises a pressing plate and a bottom plate, the female die and the male die are arranged above the bottom plate, and the pressing plate is used for providing uniform acting force for core material preforming.
Further, the pressing plate is a flexible metal sheet.
The beneficial effect that this application can realize is as follows: according to the technical scheme, based on the filling amount and curvature change conditions of the filling area in the composite material part, the filling core material matched with the curvature change of the filling area of the composite material part is prefabricated by a method of performing the pre-forming after the filling core material is laid on a forming tool matched with the curvature change layer by layer, and then the filling core material is filled in a triangular area at a variable curvature corner of a composite material structure. Compared with the method for bending the filling core material without curvature change in the prior art, the method has the advantages that the technical problem of poor filling quality of the core material in the prior art is solved due to the fact that deformation is caused by bending and fiber discontinuity is avoided, the problems of bending deformation and fiber discontinuity of the filling core material in the R area at the curvature-variable corner are solved, the surface quality of a product in the R area is improved, and the internal defect of the R area is eliminated.
Drawings
Fig. 1 is a flow chart of a core filling method in an embodiment of the present application;
FIG. 2 is a schematic structural view of the composite article of the present embodiment;
FIG. 3 isbase:Sub>A cross-sectional view taken at A-A of FIG. 2;
FIG. 4 is a schematic structural view of a core material having no curvature change in the axial direction (X direction) in the present embodiment;
FIG. 5 is a schematic structural view of a core material filled in the outer edge of the variable curvature in the axial direction in the embodiment;
FIG. 6 is a schematic structural view of a core material filled in the inner edge with variable curvature in the axial direction in the present embodiment;
FIG. 7 is a schematic structural view of a male mold of the axial variable curvature core material according to the present embodiment;
FIG. 8 is a cross-sectional view taken at B-B of FIG. 7;
fig. 9 is a schematic structural view of a negative mold of the core material of this embodiment with a variable curvature in the axial direction.
Reference numerals are as follows: 1-a composite part; 101-a first sub-part; 102-a second sub-part; 2-the area to be filled; 3-a region of variable curvature; 301-outer rim fill area; 302-inner edge fill area; 4-a core material without curvature; 5-filling a core material at the outer edge of the variable curvature; 6-variable curvature inner edge is filled with core material; 7-forming the core material; 8-pressing a plate; 9-bottom plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the motion situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In addition, if there is a description of "first", "second", etc. in an embodiment of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" appearing throughout includes three juxtapositions, exemplified by "A and/or B" including either A or B or both A and B. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The composite material is a new material formed by optimizing and combining material components with different properties by applying an advanced material preparation technology. The matrix materials of the composite materials are divided into two main categories of metal and nonmetal. Commonly used metal substrates are aluminum, magnesium, copper, titanium and alloys thereof. The non-metal matrix mainly comprises synthetic resin, rubber, ceramic, graphite, carbon and the like. The reinforced material mainly comprises glass fiber, carbon fiber, boron fiber, aramid fiber, silicon carbide fiber, asbestos fiber, whisker and metal.
At present, the composite material is widely applied to airplanes, the dosage ratio of the composite material is an important index for measuring the advancement of the airplanes, and the composite material is increasingly applied in the field of aviation by virtue of the excellent overall design. In order to avoid stress concentration in the corner region, the composite material member is usually designed to have an R-angle transition, and after the sub-members with the R-angle are combined into an integral structure, the R-region forms an inherent gap. In engineering, the gap region needs to be filled with a core material with a corresponding size. In the prior art, the continuity of the fibers filled in the core material is always ensured only when the curvature of the core material in the axial direction (X direction) is not changed. When filling a core material having a curvature change in the X direction, the core material is bent in the axial direction (X direction) to match the curvature change region. In the prior art, after the core material in the curvature change area is bent, the outer edge of the bent core material is stretched under tension due to the difference between the inner arc and the outer arc, and the inner edge of the bent core material is extruded and stacked, so that the surface quality of a composite material part is sunken or raised. In addition, in the prior art, when the core material is filled in the R-angle of the curvature change region, the core material at the corner is cut in the axial direction (X direction), or two core materials are directly spliced at the corner for filling, but this method may cause discontinuous fibers at the core material cut or spliced portion, and finally the mechanical properties of the composite material product at the position are reduced, and the seam is recessed. The two prior art methods have great technical difficulty in filling the core material at the R angle at the variable-curvature corner, and the inner part of the product has a layering defect caused by the bending or splicing of the core material in the X direction.
The following problems exist in the prior art: 1) The prepreg which is curled into a rod shape is used for molding, is limited to manufacturing a core material without curvature change in the X direction, and is not suitable for the filling condition with large curvature change in the X direction; 2) When the manufactured core material is filled in an R angle with large curvature change in the axis direction (X direction), the core material needs to be bent or cut, so that fiber accumulation wrinkles or fiber fracture discontinuity occur in the core material, the original structure of the core material is damaged, and the mechanical property of a product is reduced, and the internal delamination defect or the surface quality defect is caused.
The R-angle is the radius of the transition arc where two straight lines intersect, typically producing a casting fillet when casting a part.
The prepreg is a material for manufacturing a filling core material, and is in a layered form.
Therefore, a core material filling method capable of effectively improving the problems of bending deformation and discontinuous fiber of the core material filled in the R region at the variable curvature corner so as to improve the surface quality of the R region of the product and eliminate the internal defects of the R region is needed.
Based on this, the embodiment of the application provides a core material filling method.
Example 1
Referring to fig. 1 to 9, the present embodiment provides a core material filling method, including the following steps:
determining the core material filling amount of a filling area of a composite material product 1 according to the composite material product 1 formed by combining a plurality of sub-products; the filling area is an area to be filled 2 formed by combining R angles of a plurality of sub-pieces, and the area to be filled 2 comprises a variable-curvature outer edge filling area 301 and a variable-curvature inner edge filling area 302;
according to the filling amount of the core materials, laying prepreg on a male die of a forming tool layer by layer to form a first core material layer on the male die; wherein the shape of the male mold matches the shape of the variable curvature outer edge filling region 301;
according to the filling amount of the core material, laying prepreg on a female die of a forming tool layer by layer to form a second core material layer on the female die; wherein the negative mold matches the shape of the variable curvature inner edge fill region 302;
performing the first core material layer and the second core material layer to respectively obtain an inner edge filling core material 6 and an outer edge filling core material 5;
the outer edge filling core material 5 and the inner edge filling core material 6 are used for respectively filling the variable curvature outer edge filling area 301 and the variable curvature inner edge filling area 302 of the composite material product 1.
It should be noted that the composite material product 1 is formed by stacking and combining a plurality of sub-components, and the combined composite material product 1 has an R region, please refer to fig. 2, fig. 2 is a cross-sectional view of fig. 1 at a, as can be seen from the figure, the composite material product 1 is formed by combining a first sub-component 101 and a second sub-component 102, and in the figure, the first sub-component 101 and the second sub-component 102 have an R region filling gap after being combined, it is worth noting that, according to the requirement of the actual composite material product 1, the composite material product 1 may be formed by combining sub-components with different numbers and different shapes, and details are not described herein. Specifically, the R area filling gap is calculated, and the structure of the core material layer is analyzed and designed according to the calculation result, so that accurate filling is realized; according to the designed core material structure and the data calculation result, laying a prepreg for manufacturing the composite material in a forming area, and enabling the prepreg to become a core material capable of filling the R area of the composite material part 1 after the prepreg is subjected to the pressure action of a pressing plate 8; a pressing plate 8 is placed on the laid core material, and the bottom plate 9, the core material forming mold 7 and the pressing plate 8 are hermetically packaged by using a vacuum bag, so that the core material can be preformed in a packaging environment, and the preformed product is that the core material 5 is filled at the variable-curvature outer edge on the X-Z plane or the core material 6 is filled at the variable-curvature inner edge, please refer to fig. 5 and 6, wherein fig. 5 is a structural schematic diagram of the core material 5 filled at the variable-curvature outer edge in the axial direction, and fig. 6 is a structural schematic diagram of the core material 6 filled at the variable-curvature inner edge in the axial direction. Filling the filling core material obtained by preforming at the designated position of the composite material part 1, placing the auxiliary material on the composite material part 1, packaging the composite material part 1 filled with the core material by using a vacuum bag, and finally realizing curing molding between the core material and the composite material part 1 through a curing process, thereby completing filling of the core material with variable curvature in the axial direction.
It should be noted that the core material forming mold 7 includes a male mold on which the outer edge filling core material 5 for filling the outer edge 301 of the variable curvature region 3 is stacked to form the first core material layer, and a female mold on which the inner edge filling core material 6 for filling the inner edge of the variable curvature region 3 is stacked to form the second core material layer. Filling a preformed outer edge filling core material 5 in an outer edge R area of a variable curvature area 3 of the composite material product 1, filling a preformed inner edge filling core material 6 in an inner edge R area of the variable curvature area 3 of the composite material product 1, and filling a non-curvature core material 4 in an R filling area without curvature change of the composite material product 1. Specifically, the outer edge filling core material 5 is filled in the outer edge 301R region of the variable curvature region 3 of the composite material part 1, and the inner edge filling core material 6 is filled in the inner edge R region of the variable curvature region 3 of the composite material part 1, and since the composite material part 1 needs to fill not only the variable curvature region in the axial direction but also the region without curvature change in the axial direction, the core material 4 without curvature is filled in the R filling region without curvature change of the composite material part 1 according to the prepared core material without curvature 4. Referring to fig. 2-3, according to the characteristics of the structure and shape of the composite material product 1, when the core material is stacked and filled in the molding area, the core material 5 for filling the outer edge 301 of the variable curvature area 3 is stacked on the male mold, and the core material 6 for filling the inner edge of the variable curvature area 3 is stacked on the female mold, i.e. the curvature of the male mold is the same as the curvature of the outer edge 301 of the variable curvature area 3 of the composite material product 1, and the curvature of the female mold is the same as the curvature of the inner edge of the variable curvature area 3 of the composite material product 1. When the core material is preformed, the specific setting temperature, vacuum, pressure and pressure holding time of the core material are required, wherein the temperature depends on a resin system of the prepreg used for manufacturing the core material, and generally does not exceed the temperature at which the resin starts to flow; wherein the vacuum is generally required to be not less than-0.85 bar; pressures therein typically require 6 to 7 atmospheres; the pressure therein was maintained for a period of more than 30 minutes.
According to the method, the core material with the specific curvature in the axis direction is manufactured by calculating and designing the core material laying layer and the method for performing after the core material laying layer by layer on the specific core material forming tool, and the core material is used for accurately filling the triangular area at the variable-curvature corner of the composite material structure so as to realize the quality improvement of the part. In detail, according to the curvature of the composite material part 1, the core material forming die 7 with the same curvature is used for performing laying and preforming on the core material, and the core material adopts a layer-by-layer laying method, so that the problem of wrinkles caused by interlayer slippage when the core material is bent at the variable-curvature part in the axial direction due to the fact that the core material adopts an integral curling or pultrusion method in the prior art is solved; meanwhile, the problems of mechanical property reduction and internal defects caused by discontinuous fibers after the core material is filled at the variable-curvature position in the axial direction and is cut are solved; the invention can adopt male die or female die for forming, and meets the requirements of filling the outer edge 301 and the inner edge in the curvature change area. The embodiment solves the technical problems of bending deformation and fiber discontinuity of the R area filling core material at the variable curvature corner in the prior art, namely the problem of poor filling quality of the variable curvature core material in the prior art is solved, the problems of bending deformation and fiber discontinuity of the R area filling core material at the variable curvature corner are solved, the surface quality of a product in the R area is improved, and the internal defect of the R area is eliminated.
Example 2
This embodiment is a preferred embodiment of the present invention, and discloses a core material filling method based on embodiment 1, specifically: according to the core material filling amount, the core material filling amount is overlapped on a male die layer by layer to form a first core material layer on the male die, and the core material filling amount comprises the following steps: obtaining the number n of layers and the total width W of the first core material layer according to the filling amount of the core materials; designing the layer-by-layer width W according to the layer number n and the total width W of the pavement 1 、w 2 、w 3 ……w n W of 1 、w 2 、w 3 ……w n The width of the 1 st layer of ply, the width of the 2 nd layer of ply and the width of the 3 rd layer of ply … … n layer of ply are respectively; according to the layer-by-layer width w 1 、w 2 、w 3 ……w n And laying up layer by layer on a male mold to form a first core layer on the male mold. In the present embodiment, the layer-by-layer width w 1 、w 2 、w 3 ……w n And the ratio of two adjacent numerical values satisfies an equal difference relation. In this embodiment, the calculation formula of the total filling width W of the core material is: w = KJ/σ, K is a correction coefficient. The calculation formula for analyzing the total filling width of the prepreg can further improve the accuracy of the core structure, and can reduce the error of the core structure by correcting the coefficient. Because the R filling area is formed by enclosing two arcs and a straight line, the widths of two adjacent sides in the laying layer are set to be in an equal difference relation, so that the arc edges of the core materials can be attached to the space to be filled to the greatest extent, specifically, the width of the first layer is the largest at the bottommost layer, and the width of the nth layer is the smallest at the topmost layer. In this embodiment, the sectional area J of the filling region is calculated by the following formula: j =2R 2 -πR 2 the/2,R is the radius in the Y-Z plane of the core material. It should be noted that the effect of filling the composite material product 1 with the core material can be further improved by accurately controlling the cross-sectional area of the core material. In this embodiment, the calculation formula of the number n of the first core layer and the second core layer is: n = R/σ, σ being a single layerThe thickness of the prepreg. The core material is formed by stacking a plurality of layers, so that the internal stress in the whole core material structure can be better controlled, the mechanical property of the core material is improved, the seam sinking is avoided, and the molding quality of the core material is ensured; meanwhile, the core material formed by lamination can ensure that the core material can not have internal layering defects of products when being bent or spliced in the X direction. In this embodiment, the curvature-free core material 4 and the curvature-variable core material are spliced in an inclined plane; for the mode of 90 degrees terminal surfaces concatenations among the prior art, in this embodiment, the core adopts the inclined plane concatenation, can increase concatenation face area of contact, helps the improvement of mechanical properties, and on the other hand forms when pressurizeing in the part curing process and caves in, and sunken can cause the sunken defect in part surface, and the mode of setting up of this embodiment can effectively avoid concatenation department sudden change. The pressing plate 8 is a flexible metal sheet. It should be noted that, in the prior art, a rigid pressing plate 8 is used during core material molding, and deformation of the rigid pressing plate 8 may cause a problem of pressure transmission failure in a long-term use condition, and the pressing plate 8 provided in this embodiment is made of a sheet metal material with certain flexibility, so that the flexible pressing plate 8 can adapt to a curvature in a preforming process, and the above problem is effectively avoided.
The above is only a preferred embodiment of the present application, and the present invention is not limited to the scope of the present application, and the present invention only refers to the variable curvature condition of the core material in the X-Z plane, and does not indicate or imply that the present invention only protects the variable curvature core material in the X-Z plane, but also can be a variable curvature core material filling method in the X-Y plane, and when the variable curvature core material in the X-Y plane is manufactured, the core material forming tool does not have the division of the male mold and the female mold. The technical solutions formed by equivalent transformation or equivalent replacement, or directly or indirectly applied to other related technical fields, are all within the scope of the present invention.
Claims (10)
1. A method of filling a core material, comprising the steps of:
determining the core material filling amount of a filling area of a composite material part according to the composite material part formed by combining a plurality of sub-parts; the filling area is an area to be filled formed by combining R angles of a plurality of sub-pieces, and the area to be filled comprises a variable-curvature outer edge filling area and a variable-curvature inner edge filling area;
according to the core material filling amount, laying prepreg on a male die of a forming tool layer by layer to form a first core material layer on the male die; wherein the shape of the male die is matched with that of the variable-curvature outer edge filling area;
according to the filling amount of the core material, laying prepreg on a female die of a forming tool layer by layer to form a second core material layer on the female die; wherein the female mold matches the shape of the variable curvature inner edge fill area;
performing the first core material layer and the second core material layer to respectively obtain an inner edge filling core material and an outer edge filling core material;
and filling the variable-curvature outer edge filling area and the variable-curvature inner edge filling area of the composite material part respectively by using the outer edge filling core material and the inner edge filling core material.
2. The core material filling method of claim 1, wherein the step of laying up a first core material layer on a male mold layer by layer to form a first core material layer on the male mold according to the core material filling amount comprises:
obtaining the number n of layers and the total width W of the first core material layer according to the filling amount of the core materials;
designing the layer-by-layer width W according to the layer number n and the total width W of the pavement 1 、w 2 、w 3 ……w n Said w is 1 、w 2 、w 3 ……w n The width of the 1 st layer of ply, the width of the 2 nd layer of ply and the width of the 3 rd layer of ply … … of the nth layer of ply are respectively;
according to the layer-by-layer width w 1 、w 2 、w 3 ……w n And laying up layer by layer on a male mold to form a first core layer on the male mold.
3. A method of core filling according to claim 2, wherein said method comprisesThe sectional area J of the filling area is calculated by the formula: j =2R 2 -πR 2 the/2,R is the radius in the Y-Z plane of the core material.
4. A core material filling method according to claim 3, wherein the calculation formula of the number n of layers of the first core material layer and the second core material layer is: n = R/σ, σ being the single prepreg thickness.
5. The core filling method of claim 4, wherein the total filling width W of the core material is calculated by the formula: w = KJ/σ, K is a correction coefficient.
6. The core filling method of claim 5, wherein the layer-by-layer width w 1 、w 2 、w 3 ……w n And the ratio of two adjacent numerical values satisfies an equal difference relation.
7. The core filling method as claimed in claim 6, wherein the region to be filled further comprises a curvature-free filling region;
the method further comprises the following steps:
filling the non-curvature filled region with a non-curvature core material.
8. The method of claim 7, wherein the non-curvature core material and the variable-curvature core material are bevel-spliced.
9. The core filling method of claim 1, wherein the forming tool further comprises a pressing plate and a base plate, the female mold and the male mold being disposed above the base plate, the pressing plate being configured to provide a uniform force for core pre-forming.
10. A method of core filling according to claim 9, wherein said press plate is a flexible metal sheet.
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| CN117067639A (en) * | 2023-09-22 | 2023-11-17 | 哈尔滨远驰航空装备有限公司 | Forming method and product of small-fillet composite material outer lining |
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