Circumferential quasi-isotropic composite material membrane disc and preparation method thereof

Abstract

The invention relates to a circumferential quasi-isotropic composite material membrane disc and a preparation method thereof.The composite material membrane disc comprises a center through hole and an annular area concentric with the center through hole, and an inner connecting hole reinforcing area concentric with the center through hole is arranged on the inner side of the annular area; an outer connecting hole reinforcing area concentric with the central through hole is arranged on the outer side of the annular area; the composite material membrane disc is obtained through hot press molding of composite material layers, the layer laying mode is # imgabs0 #, the layer laying number of the annular area is N0, the deflection angle of the next layer in every two adjacent layers of composite materials in the same direction is alpha compared with the deflection angle of the previous layer in the same direction, the laying frequency of each layer of composite materials is beta, only half of the # imgabs1 # symmetrical layer is written, and only half of the # imgabs1 # symmetrical layer is written. And the parentheses and subscripts s represent symmetry. Compared with the prior art, the method has the advantages that compared with a traditional orthogonal laying scheme, the method can better fit the loaded working condition of a product, the stress level of a membrane disc can be reduced, and the utilization rate of a fiber material is increased.

Description

Technical Field

[0001] The present invention relates to the technical field of composite material membrane disks, and in particular to a circumferentially quasi-isotropic composite material membrane disk and a preparation method thereof. Background Art

[0002] The diaphragm coupling is a kind of elastic coupling. It is widely used in machinery, shipbuilding, aviation and other fields due to its simple structure, smooth movement, self-lubrication and low noise. The diaphragm, as a key component, has to withstand complex loads such as torsion, bending, shearing and centrifugal force during operation, while also absorbing vibrations and axial displacement compensation and angle compensation. With the continuous development of science and technology, fiber-reinforced resin-based composite materials have begun to be widely used in various industries. They have the advantages of high specific strength, high specific modulus, corrosion resistance, and strong designability. Compared with metal materials, composite materials can significantly reduce weight and have higher material strength.

[0003] As an anisotropic material, composite materials have obvious fiber orientation in their material properties, that is, the material strength is higher along the fiber direction, while the material strength will decrease to a certain extent when it deviates from the fiber direction. The movement of the membrane disc is rotation, and it is uniformly stressed in the circumferential direction during operation. However, the traditional orthogonal ply scheme cannot achieve uniform reinforcement of the fibers in the circumferential direction, and there is a certain strength deviation area. Patent Publication No. CN110821979A discloses a composite corrugated membrane disc, a hot pressing forming mold and a hot pressing forming method. The process of laying the membrane disc is to heat the prepreg ply obtained by cutting. When the prepreg ply is softened for easy laying, the loose prepreg ply is laid according to the designed ply form, and finally laid into a regular-shaped membrane disc ply compact. A plurality of prepreg plies are arranged in the membrane disc body, and the two radial directions perpendicular to each other of the membrane disc body are 0° and 90° respectively. Then, all the prepreg plies include at least 0° plies with a fiber direction of 0°, 90° plies with a fiber direction of 90°, 45° plies with a fiber direction of 45° and -45° plies with a fiber direction of -45°. Summary of the invention

[0004] The purpose of the present invention is to overcome the defects of the above-mentioned prior art and provide a circumferentially quasi-isotropic composite material diaphragm disk and a preparation method so that the material strength of the composite material is consistent with the load form of the diaphragm disk.

[0005] The purpose of the present invention can be achieved by the following technical solutions:

[0006] In one aspect, the present invention provides a circumferential quasi-isotropic composite material membrane disk, the composite material membrane disk comprising a central through hole and an annular area arranged concentrically therewith, an inner connecting hole reinforcement area arranged concentrically with the central through hole is arranged on the inner side of the annular area, and an outer connecting hole reinforcement area arranged concentrically with the central through hole is arranged on the outer side of the annular area;

[0007] The composite membrane disc is obtained by hot pressing composite material plies, and the plies are in the form of The number of plies in the annular area is N0, the deflection angle of the next ply in the adjacent two layers of composite material compared to the previous ply in the same direction is α, and the number of times each layer of composite material is laid is β. Symmetrical plies are written with only half of their plies, and the subscript “s” outside the brackets indicates symmetry.

[0008] Furthermore, a plurality of internal connection holes are distributed on the internal connection hole reinforcement area;

[0009] A plurality of external connection holes are distributed on the external connection hole reinforcement area.

[0010] Furthermore, metal inserts are installed in the inner connection hole and the outer connection hole respectively.

[0011] Furthermore, the number of plies in the annular area is the number of full plies, and the full ply is a complete ply relative to the local reinforcement layer. The starting point of material cutting is the inner diameter circle of the composite material membrane disk, and the end point of material cutting is the outer diameter circle of the composite material membrane disk. The inner diameter circle of the composite material membrane disk, that is, the intersection edge position of the circle of the central through hole and the inner connecting hole reinforcement area, is the position of the composite material membrane disk closest to the center of the central through hole; the outer diameter circle of the composite material membrane disk, that is, the outermost edge position of the outer connecting hole reinforcement area, is the position of the composite material membrane disk farthest from the center of the central through hole. All the following inner diameter circles indicate the position of the area closest to the center of the central through hole, and all the following outer diameter circles indicate the position of the area farthest from the center of the central through hole. For example, the outer diameter circle of the inner connecting hole reinforcement area described below is the position of the inner connecting hole reinforcement area farthest from the center of the central through hole.

[0012] Furthermore, the thickness of the inner connection hole reinforcement area and the outer connection hole reinforcement area is greater than the thickness of the annular area;

[0013] The number of plies in the inner connection hole reinforcement area is N1=N0+N1', where N1' represents the number of plies of the local reinforcement layer in the inner connection hole reinforcement area;

[0014] The number of plies in the outer connection hole reinforcement area is N2=N0+N2', where N2' represents the number of plies of the local reinforcement layer in the outer connection hole reinforcement area.

[0015] Furthermore, the local reinforcement layer of the inner connection hole reinforcement area and the local reinforcement layer of the outer connection hole reinforcement area are evenly distributed between the two layers of the annular area plies, and the ply angle is consistent with the previous full ply angle;

[0016] The starting point of cutting the local reinforcement layer of the inner connection hole reinforcement area is the inner diameter circle of the composite material membrane disk, and the end point of cutting is the outer diameter circle of the inner connection hole reinforcement area;

[0017] The starting point of cutting the local reinforcement layer of the outer connection hole reinforcement area is the outer diameter circle of the composite material membrane disk, and the ending point of cutting is the inner diameter circle of the outer connection hole reinforcement area.

[0018] Furthermore, the plying form of the local reinforcement layer in the inner connection hole reinforcement area is

[0019] The plying form of the local reinforcement layer in the outer connection hole reinforcement area is:

[0020] s indicates symmetry. The top mark “-” on the ply of the symmetric middle surface indicates that the laying times of each layer of composite material in the local reinforcement layer of the inner connection hole reinforcement area is β1, and the laying times of each layer of composite material in the local reinforcement layer of the outer connection hole reinforcement area is β2.

[0021] Furthermore, the annular area is connected to the inner connection hole reinforcement area through an inner transition area;

[0022] The annular area is connected to the outer connection hole reinforcement area through an outer transition area.

[0023] More preferably, the thickness of one end of the inner transition zone connected to the annular zone is consistent with the thickness of the annular zone, and the thickness of one end connected to the inner connection hole reinforcement zone is consistent with the thickness of the inner connection hole reinforcement zone. The thickness of the inner transition zone increases from the end connected to the annular zone to the end connected to the inner connection hole reinforcement zone, preferably increases uniformly.

[0024] The thickness of one end of the outer transition zone connected to the annular zone is consistent with the thickness of the annular zone, and the thickness of one end connected to the outer connecting hole reinforcement zone is consistent with the thickness of the outer connecting hole reinforcement zone. The thickness of the inner transition zone increases from the end connected to the annular zone to the end connected to the outer connecting hole reinforcement zone, preferably increases evenly.

[0025] More preferably, the starting point of the blanking of the local reinforcement layer in the inner connection hole reinforcement zone is the inner diameter circle of the composite material membrane disk, and the end point of the blanking gradually changes from the inner diameter circle of the inner transition zone to the outer diameter circle of the inner transition zone, and then gradually changes to the inner diameter circle of the inner transition zone, and when the end point of the blanking is the outer diameter circle of the inner transition zone, the deflection angle of the layer of composite material is 180°;

[0026] The starting point of the blanking of the local reinforcement layer in the outer connection hole reinforcement zone is the outer diameter circle of the composite material membrane disk, and the blanking end point gradually changes from the outer diameter circle of the outer transition zone to the inner diameter circle of the outer transition zone, and then gradually changes to the outer diameter circle of the outer transition zone. When the blanking end point is the inner diameter circle of the outer transition zone, the deflection angle of the composite material layer is 180°;

[0027] The composite material membrane disks are symmetrically distributed along a horizontal neutral plane.

[0028] Furthermore, the composite material is a fiber-reinforced resin-based composite material.

[0029] Furthermore, the composite material includes glass fiber unidirectional cloth, aramid fiber unidirectional cloth or carbon fiber cloth of other specifications.

[0030] On the other hand, the present invention also provides a method for preparing a circumferentially quasi-isotropic composite membrane disk, wherein the composite material is The composite material membrane disc is obtained by laying layers in a mold in the form of a plurality of layers, closing the upper mold and the lower mold for heating and curing, and curing and demoulding.

[0031] Furthermore, the method for preparing the composite material membrane disk comprises the following steps:

[0032] S1. Determine the size of the composite material membrane disc, including the inner diameter and outer diameter of the composite material membrane disc, the thickness, inner diameter and outer diameter of the inner connection hole reinforcement area, the annular area and the outer connection hole reinforcement area;

[0033] S2, determining the single layer thickness of the composite material used to form the composite film disc;

[0034] S3, determine the number of plies of the inner connection hole reinforcement area and its local reinforcement layer, the annular area, the outer connection hole reinforcement area and its local reinforcement layer, which are N1, N1', N0, N2, N2', respectively, N1 = N0 + N1', N2 = N0 + N2';

[0035] S4. Lay the layers in the mold and mark an origin on the mold. When the fiber direction passes through the center of the circle and points to this point, the layup angle is 0°. The number of layups of each layer of composite material is β. The deflection angle of the next layer of the adjacent two layers of composite material in the same direction is α compared with the previous layer. Taking the origin as the reference, The annular area is fully paved in the form of a paving layer, wherein the starting point of the material cutting is the inner diameter circle of the composite material membrane disk, and the end point of the material cutting is the outer diameter circle of the composite material membrane disk;

[0036] by A local reinforcement layer is laid on the inner connection hole reinforcement area in the form of a laying layer, the starting point of the material cutting is the inner diameter circle of the composite material membrane disk, and the end point of the material cutting is the outer diameter circle of the inner connection hole reinforcement area;

[0037] by A local reinforcement layer is laid on the outer connection hole reinforcement area in the laying form, the starting point of cutting is the outer diameter circle of the composite material membrane disk, and the end point of cutting is the inner diameter circle of the outer connection hole reinforcement area.

[0038] The local reinforcement layer of the inner connection hole reinforcement area and the local reinforcement layer of the outer connection hole reinforcement area of ​​each layer are located between two layers of full plies, and the ply angle is consistent with the angle of the previous full ply;

[0039] S5, the upper mold and the lower mold are combined, heated and cured, and then the composite material film disc is obtained by curing and demoulding.

[0040] Furthermore, the number of plies of the inner connecting hole reinforcement area, the annular area, and the outer connecting hole reinforcement area is equal to the thickness of the inner connecting hole reinforcement area, the annular area, and the outer connecting hole reinforcement area divided by the single layer thickness of the composite material, and the result is obtained by the step-up method.

[0041] Furthermore, a layer of carbon fiber orthogonal fabric is laid on the upper and lower surface layers of the composite film disc as an outer protective layer, and the extra thickness is used as a filler margin of the film disc, which helps to compact the part during the mold closing process.

[0042] Furthermore, the heating and curing conditions adopt the conventional heating and curing temperature in the art.

[0043] Furthermore, the method for preparing the composite film disk comprises the following steps:

[0044] S1. Determine the size of the composite membrane disc, including the inner diameter and outer diameter of the composite membrane disc, the thickness, inner diameter and outer diameter of the inner connection hole reinforcement zone, the annular zone and the outer connection hole reinforcement zone, and the inner diameter and outer diameter of the inner transition zone and the outer transition zone;

[0045] S2, determining the single layer thickness of the composite material used to form the composite film disc;

[0046] S3, determine the number of plies of the inner connection hole reinforcement area and its local reinforcement layer, the annular area, the outer connection hole reinforcement area and its local reinforcement layer, which are N1, N1', N0, N2, N2', respectively, N1 = N0 + N1', N2 = N0 + N2';

[0047] S4. Lay the layers in the mold and mark an origin on the mold. When the fiber direction passes through the center of the circle and points to this point, the layup angle is 0°. The number of layups of each layer of composite material is β. The deflection angle of the next layer of the adjacent two layers of composite material in the same direction is α compared with the previous layer. Taking the origin as the reference, The annular area is fully paved in the form of a paving layer, wherein the starting point of the material cutting is the inner diameter circle of the composite material membrane disk, and the end point of the material cutting is the outer diameter circle of the composite material membrane disk;

[0048] by A local reinforcement layer is laid on the inner connection hole reinforcement area in the form of a laying layer, the starting point of the material cutting is the inner diameter circle of the composite material membrane disc, and the end point of the material cutting gradually changes from the inner diameter circle of the inner transition zone to the outer diameter circle of the inner transition zone, and then gradually changes to the inner diameter circle of the inner transition zone, and when the end point of the material cutting is the outer diameter circle of the inner transition zone, the deflection angle of the layer of composite material is 180°;

[0049] by A local reinforcement layer is laid on the outer connection hole reinforcement area in the form of a laying layer, the starting point of the material cutting is the outer diameter circle of the composite material membrane disk, and the end point of the material cutting gradually changes from the outer diameter circle of the outer transition zone to the inner diameter circle of the outer transition zone, and then gradually changes to the outer diameter circle of the outer transition zone, and when the end point of the material cutting is the inner diameter circle of the outer transition zone, the deflection angle of the layer of composite material is 180°;

[0050] According to the symmetry principle of composite material layer design, the composite material diaphragm disc is symmetrically distributed along the horizontal neutral plane;

[0051] The local reinforcement layer of the inner connection hole reinforcement area and the local reinforcement layer of the outer connection hole reinforcement area of ​​each layer are located between two layers of full plies, and the ply angle is consistent with the angle of the previous full ply;

[0052] S5, the upper mold and the lower mold are combined, heated and cured, and then the composite material film disc is obtained by curing and demoulding.

[0053] Compared with the prior art, the present invention has the following advantages:

[0054] (1) The present invention provides a circumferentially quasi-isotropic composite material membrane disk and a preparation method thereof, wherein the layering method is as follows: Since the movement of the diaphragm disc is rotation, it is uniformly stressed in the circumferential direction during operation, which can achieve uniform reinforcement of the fibers in the circumferential direction, and there is no strength deviation zone. Compared with the traditional orthogonal laying scheme, it can better fit the load conditions of the product, reduce the stress level of the diaphragm disc, and improve the utilization rate of fiber materials. The laying angles of orthogonal laying are 0°, 90°, and ±45°, that is, there is no direct fiber reinforcement in other angles. For diaphragm disc components, their working load is mainly affected by centrifugal force, which is a radial load. The use of orthogonal laying will cause the diaphragm disc to have direct fiber reinforcement only in the directions of 0°, 90°, and ±45°, and no direct fiber reinforcement at other angles. There is a certain angle between the centrifugal force and the fiber direction, which limits the strength of the material. Continuous positive and negative laying is indicated by "±" or Indicates that the symbol above represents the previous layer.

[0055] (2) The present invention provides a circumferential quasi-isotropic composite material diaphragm disk and a preparation method thereof. When laying the layers, the annular area is fully laid. In addition to being fully laid, the inner connection hole reinforcement area and the outer connection hole reinforcement area are also provided with local reinforcement layers, and each local reinforcement layer is arranged between two layers of full laying. This can more effectively achieve uniform reinforcement of the fiber in the circumferential direction, better fit the product's load conditions, reduce the stress level of the diaphragm disk, and improve the utilization rate of the fiber material. The combination of local laying and overall laying makes the overall structure of the diaphragm disk more uniform, avoiding problems such as stress concentration and local slippage caused by excessive thickness of the local reinforcement layer.

[0056] (3) The present invention provides an axial quasi-isotropic composite membrane disk and a preparation method thereof, wherein an inner transition zone is designed between the annular zone and the inner connection hole reinforcement zone, and an outer transition zone is designed between the annular zone and the outer connection hole reinforcement zone, taking into account the gradual thickness change of the product in the inner transition zone and the outer transition zone, and the composite membrane disk with variable thickness is symmetrical about the neutral plane, which can make the layer more in line with the load condition of the product, reduce the stress level of the membrane disk, and improve the utilization rate of the fiber material. This is the basic principle of paving. The layer angle of the component needs to be symmetrical about the neutral plane, otherwise there will be large residual stress during the curing process, and even warping will occur.

[0057] (4) The invention combines the product forming process, and the orthogonal fabric added to the upper and lower surfaces not only serves as a filler margin to help product forming, but also serves as an outer protective layer for the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] Figure 1 It is a schematic diagram of the structure of the composite material membrane disk shown in Example 1;

[0059] Figure 2 is a full cross-sectional view of the composite material membrane disc shown in Example 1;

[0060] Figure 3 It is a stress cloud diagram of the composite material membrane disk shown in Example 1 at a rotation speed of 15000 rpm;

[0061] Figure 4 It is a stress cloud diagram of the composite material membrane disc shown in Comparative Example 1 at a rotation speed of 15000 rpm;

[0062] Figure 5 It is a displacement cloud diagram of the composite material diaphragm shown in Example 1 under a torque of 5000 N·m;

[0063] Figure 6 It is a displacement cloud diagram of the composite material diaphragm shown in Comparative Example 1 under a torque of 5000 N·m;

[0064] Figure 7 It is a displacement cloud diagram of the composite material membrane disk shown in Example 1 under a bending moment of 500 N·m;

[0065] Figure 8 This is the displacement cloud diagram of the composite material diaphragm shown in Comparative Example 1 under a bending moment of 500 N·m.

[0066] Description of the markings in the figure:

[0067] 1-Composite material membrane disc;

[0068] 2-internal connection hole reinforcement area, 21-internal connection hole;

[0069] 3-Inner transition zone;

[0070] 4- Ring area;

[0071] 5-outer transition zone;

[0072] 6-external connection hole reinforcement area, 61-external connection hole. DETAILED DESCRIPTION

[0073] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments are implemented based on the technical solution of the present invention, and detailed implementation methods and specific operation processes are given, but the protection scope of the present invention is not limited to the following embodiments. In the following embodiments or embodiments, if there is no special description of the functional components or structures, it means that they are all conventional components or conventional structures used in the art to achieve the corresponding functions.

[0074] It should be noted that in the description of the present invention, the terms "upper", "lower", "inner", "outer", "front end", "rear end", "two ends", "one end", "the other end" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0075] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0076] In the following embodiments, T700 carbon fiber unidirectional prepreg, brand UA2435-125; orthogonal fabric uses T300-3K carbon fiber plain prepreg, brand WSN-3K-P-T300, both of which are purchased from Shanghai Jinhao Fiber Composite Materials Co., Ltd.

[0077] A circumferential quasi-isotropic composite material diaphragm, the composite material diaphragm comprising a central through hole 1 and an annular area 4 arranged concentrically therewith, an inner connecting hole reinforcement area 2 arranged concentrically with the central through hole 1 is arranged on the inner side of the annular area 4, and an outer connecting hole reinforcement area 6 arranged concentrically with the central through hole 1 is arranged on the outer side of the annular area 4;

[0078] The composite membrane disc is obtained by hot pressing composite material plies, and the plies are in the form of The number of plies in the annular area 4 is N0, the deflection angle of the next ply in the adjacent two layers of composite material compared to the previous ply in the same direction is α, and the number of times each layer of composite material is laid is β. Symmetrical plies are written with only half of their plies, and the subscript “s” outside the brackets indicates symmetry.

[0079] As one of the preferred embodiments, a plurality of internal connection holes 21 are distributed on the internal connection hole reinforcement area 2;

[0080] A plurality of external connection holes 61 are distributed on the external connection hole reinforcement area 6 .

[0081] As one of the preferred implementations, metal inserts are installed in the inner connection hole 21 and the outer connection hole 61 respectively.

[0082] As one of the preferred embodiments, the number of plies in the annular area 4 is the full number of plies, and the starting point for cutting is the inner diameter circle of the composite material membrane disk, and the end point for cutting is the outer diameter circle of the composite material membrane disk. The inner diameter circle of the composite material membrane disk, i.e., the intersection edge position of the circle of the central through hole 1 and the inner connecting hole reinforcement area 2, is the position of the composite material membrane disk closest to the center of the central through hole 1; the outer diameter circle of the composite material membrane disk, i.e., the outermost edge position of the outer connecting hole reinforcement area 6, is the position of the composite material membrane disk farthest from the center of the central through hole 1. All the following inner diameter circles indicate the position of the area closest to the center of the central through hole 1, and all the following outer diameter circles indicate the position of the area farthest from the center of the central through hole 1. For example, the outer diameter circle of the inner connecting hole reinforcement area 2 described below is the position of the inner connecting hole reinforcement area 2 farthest from the center of the central through hole 1.

[0083] As one of the preferred embodiments, the thickness of the inner connection hole reinforcement area 2 and the outer connection hole reinforcement area 6 is greater than the thickness of the annular area 4;

[0084] The number of plies of the inner connection hole reinforcement area 2 is N1=N0+N1', where N1' represents the number of plies of the local reinforcement layer of the inner connection hole reinforcement area 2;

[0085] The number of plies N2 of the outer connection hole reinforcement area 6 is N0+N2′, where N2′ represents the number of plies of the local reinforcement layer of the outer connection hole reinforcement area 6 .

[0086] As one of the preferred embodiments, the local reinforcement layer of the inner connection hole reinforcement area 2 and the local reinforcement layer of the outer connection hole reinforcement area 6 are evenly distributed between the two layers of the plies of the annular area 4, and the ply angle is consistent with the previous full ply angle;

[0087] The starting point of cutting the local reinforcement layer of the inner connection hole reinforcement area 2 is the inner diameter circle of the composite material membrane disk, and the end point of cutting is the outer diameter circle of the inner connection hole reinforcement area 2;

[0088] The starting point of cutting the local reinforcement layer of the outer connection hole reinforcement area 6 is the outer diameter circle of the composite material membrane disk, and the end point of cutting is the inner diameter circle of the outer connection hole reinforcement area 6.

[0089] As one of the preferred embodiments, the plying form of the local reinforcement layer in the inner connection hole reinforcement area 2 is

[0090] The plying form of the local reinforcement layer in the outer connection hole reinforcement area 6 is:

[0091] s indicates symmetry. The top mark “-” on the ply of the symmetric middle surface indicates that the laying times of each layer of composite material in the local reinforcement layer of the inner connection hole reinforcement area 2 is β1, and the laying times of each layer of composite material in the local reinforcement layer of the outer connection hole reinforcement area 6 is β2.

[0092] As one of the preferred embodiments, the annular area 4 is connected to the inner connection hole reinforcement area 2 via an inner transition area 3;

[0093] The annular region 4 is connected to the outer connection hole reinforcement region 6 via an outer transition region 5 .

[0094] As one of the preferred embodiments, the thickness of one end of the inner transition zone 3 connected to the annular zone 4 is consistent with the thickness of the annular zone 4, and the thickness of one end connected to the inner connection hole reinforcement zone 2 is consistent with the thickness of the inner connection hole reinforcement zone 2. The thickness of the inner transition zone 3 increases from the end connected to the annular zone 4 to the end connected to the inner connection hole reinforcement zone 2, preferably increases uniformly.

[0095] The thickness of the end of the outer transition zone 5 connected to the annular zone 4 is consistent with the thickness of the annular zone 4, and the thickness of the end connected to the external connection hole reinforcement zone 6 is consistent with the thickness of the external connection hole reinforcement zone 6. The thickness of the inner transition zone 3 increases from the end connected to the annular zone 4 to the end connected to the external connection hole reinforcement zone 6, and preferably increases evenly.

[0096] As one of the preferred embodiments, the starting point of the blanking of the local reinforcement layer of the inner connection hole reinforcement zone 2 is the inner diameter circle of the composite material membrane disk, and the blanking end point gradually changes from the inner diameter circle of the inner transition zone 3 to the outer diameter circle of the inner transition zone 3, and then gradually changes to the inner diameter circle of the inner transition zone 3, and when the blanking end point is the outer diameter circle of the inner transition zone 3, the deflection angle of the layer of composite material is 180°;

[0097] The starting point of the cutting of the local reinforcement layer of the outer connection hole reinforcement area 6 is the outer diameter circle of the composite material membrane disk, and the end point of the cutting gradually changes from the outer diameter circle of the outer transition zone 5 to the inner diameter circle of the outer transition zone 5, and then gradually changes to the outer diameter circle of the outer transition zone 5. When the end point of the cutting is the inner diameter circle of the outer transition zone 5, the deflection angle of the composite material layer is 180°;

[0098] The composite material membrane disks are symmetrically distributed along a horizontal neutral plane.

[0099] As one of the preferred implementations, the composite material is a fiber-reinforced resin-based composite material.

[0100] As one of the preferred implementations, the composite material includes glass fiber unidirectional cloth, aramid fiber unidirectional cloth or carbon fiber cloth of other specifications.

[0101] A method for preparing a circumferentially quasi-isotropic composite membrane disk, comprising: The composite material membrane disc is obtained by laying layers in a mold in the form of a plurality of layers, closing the upper mold and the lower mold for heating and curing, and curing and demoulding.

[0102] As one of the preferred embodiments, the method for preparing the composite membrane disk comprises the following steps:

[0103] S1. Determine the size of the composite membrane disc, including the inner diameter and outer diameter of the composite membrane disc, the thickness, inner diameter and outer diameter of the inner connection hole reinforcement area 2, the annular area 4 and the outer connection hole reinforcement area 6;

[0104] S2, determining the single layer thickness of the composite material used to form the composite film disc;

[0105] S3, determine the number of plies of the inner connection hole reinforcement area 2 and its local reinforcement layer, the annular area 4, the outer connection hole reinforcement area 6 and its local reinforcement layer, which are N1, N1', N0, N2, N2', respectively, N1 = N0 + N1', N2 = N0 + N2';

[0106] S4. Lay the layers in the mold and mark an origin on the mold. When the fiber direction passes through the center of the circle and points to this point, the layup angle is 0°. The number of layups of each layer of composite material is β. The deflection angle of the next layer of the adjacent two layers of composite material in the same direction is α compared with the previous layer. Taking the origin as the reference, The annular area 4 is fully paved in the form of a ply, wherein the starting point of the material cutting is the inner diameter circle of the composite material membrane disk, and the end point of the material cutting is the outer diameter circle of the composite material membrane disk;

[0107] by A local reinforcement layer is laid on the inner connection hole reinforcement area 2 in the form of a laying layer, the starting point of the material cutting is the inner diameter circle of the composite material membrane disk, and the end point of the material cutting is the outer diameter circle of the inner connection hole reinforcement area 2;

[0108] by A local reinforcement layer is laid on the outer connection hole reinforcement area 6 in the laying form, the starting point of cutting is the outer diameter circle of the composite material membrane disk, and the end point of cutting is the inner diameter circle of the outer connection hole reinforcement area 6.

[0109] The local reinforcement layer of the inner connection hole reinforcement area 2 and the local reinforcement layer of the outer connection hole reinforcement area 6 of each layer are located between two layers of full plies, and the ply angle is consistent with the angle of the previous full ply;

[0110] S5, the upper mold and the lower mold are combined, heated and cured, and then the composite material film disc is obtained by curing and demoulding.

[0111] As one of the preferred embodiments, the number of plies of the inner connecting hole reinforcement area 2, the annular area 4, and the outer connecting hole reinforcement area 6 is equal to the thickness of the inner connecting hole reinforcement area 2, the annular area 4, and the outer connecting hole reinforcement area 6 divided by the single layer thickness of the composite material, and the result is obtained by the further method.

[0112] As one of the preferred embodiments, a layer of carbon fiber orthogonal fabric is laid on the upper and lower surface layers of the composite film disc as an outer protective layer, and the extra thickness is used as a filling margin of the film disc to help compact the part during the mold closing process.

[0113] As one of the preferred embodiments, the heating and curing conditions adopt the conventional heating and curing temperature in the art.

[0114] As one of the preferred embodiments, the method for preparing the composite membrane disk comprises the following steps:

[0115] S1. Determine the size of the composite membrane disc, including the inner diameter and outer diameter of the composite membrane disc, the thickness, inner diameter and outer diameter of the inner connection hole reinforcement area 2, the annular area 4 and the outer connection hole reinforcement area 6, and the inner diameter and outer diameter of the inner transition area 3 and the outer transition area 5;

[0116] S2, determining the single layer thickness of the composite material used to form the composite film disc;

[0117] S3, determine the number of plies of the inner connection hole reinforcement area 2 and its local reinforcement layer, the annular area 4, the outer connection hole reinforcement area 6 and its local reinforcement layer, which are N1, N1', N0, N2, N2', respectively, N1 = N0 + N1', N2 = N0 + N2';

[0118] S4. Lay the layers in the mold and mark an origin on the mold. When the fiber direction passes through the center of the circle and points to this point, the layup angle is 0°. The number of layups of each layer of composite material is β. The deflection angle of the next layer of the adjacent two layers of composite material in the same direction is α compared with the previous layer. Taking the origin as the reference, The annular area 4 is fully paved in the form of a ply, wherein the starting point of the material cutting is the inner diameter circle of the composite material membrane disk, and the end point of the material cutting is the outer diameter circle of the composite material membrane disk;

[0119] by A local reinforcement layer is laid on the inner connection hole reinforcement area 2 in the laying form, the starting point of the material cutting is the inner diameter circle of the composite material membrane disc, and the end point of the material cutting gradually changes from the inner diameter circle of the inner transition zone 3 to the outer diameter circle of the inner transition zone 3, and then gradually changes to the inner diameter circle of the inner transition zone 3, and when the end point of the material cutting is the outer diameter circle of the inner transition zone 3, the deflection angle of the layer of composite material is 180°;

[0120] by A local reinforcement layer is laid on the outer connection hole reinforcement area 6 in the laying form, the starting point of the material cutting is the outer diameter circle of the composite material membrane disc, and the end point of the material cutting gradually changes from the outer diameter circle of the outer transition zone 5 to the inner diameter circle of the outer transition zone 5, and then gradually changes to the outer diameter circle of the outer transition zone 5, and when the end point of the material cutting is the inner diameter circle of the outer transition zone 5, the deflection angle of the layer of composite material is 180°;

[0121] According to the symmetry principle of composite material layer design, the composite material diaphragm disc is symmetrically distributed along the horizontal neutral plane;

[0122] The local reinforcement layer of the inner connection hole reinforcement area 2 and the local reinforcement layer of the outer connection hole reinforcement area 6 of each layer are located between two layers of full plies, and the ply angle is consistent with the angle of the previous full ply;

[0123] S5, the upper mold and the lower mold are combined, heated and cured, and then the composite material film disc is obtained by curing and demoulding.

[0124] Example 1

[0125] like Figure 1 The figure is a schematic diagram of the structure of the composite material diaphragm disk of the present embodiment, in particular, a composite material diaphragm disk of variable thickness, the composite material diaphragm disk comprises a central through hole 1 and an annular area 4 arranged concentrically therewith, the inner side of the annular area 4 is provided with an inner connection hole reinforcement area 2 arranged concentrically with the central through hole 1, and the outer side of the annular area 4 is provided with an outer connection hole reinforcement area 6 arranged concentrically with the central through hole 1. A plurality of inner connection holes 21 are distributed on the inner connection hole reinforcement area 2; a plurality of outer connection holes 61 are distributed on the outer connection hole reinforcement area 6. Metal inserts are respectively installed in the inner connection holes 21 and the outer connection holes 61. The composite material diaphragm disk is obtained by hot pressing composite material plies, and the ply form is The number of plies in the annular area 4 is N0, the deflection angle of the next ply in the adjacent two layers of composite material compared to the previous ply in the same direction is α, and the number of times each layer of composite material is laid is β. Symmetrical plies are written with only half of their plies, and the subscript “s” outside the brackets indicates symmetry.

[0126] like Figure 2 , which is a full cross-sectional view of the composite material membrane disk in this embodiment, and its dimensions are shown in the following Table 1.

[0127] Table 1 Dimensions of composite membrane disc

[0128] Reference numerals name Inner diameter mm Outer diameter (mm) Thickness mm 1 Center through hole 140 140 13 2 Internal connection hole reinforcement area 140 212 13 3 Inner transition zone 212 242 1.8～13 4 Ring Area 242 386 4.8 5 Outer transition zone 386 404 4.8～9 6 External connection hole reinforcement area 404 466 9

[0129] The materials used in this layer design are T700 carbon fiber unidirectional prepreg tape and orthogonal fabric, where the unidirectional tape layer is 0.2mm thick and the orthogonal fabric layer is 0.2mm thick. The above materials are specific materials used in this implementation case, and the present invention is not limited to the above materials, including but not limited to glass fiber unidirectional cloth, aramid fiber unidirectional cloth and other specifications of carbon fiber cloth.

[0130] In this embodiment, the number of layers of the annular area 4 is the full number of layers, and the starting point and end point of the material cutting are the inner diameter and outer diameter of the composite membrane disk, respectively.

[0131] In this embodiment, the thickness of the inner connection hole reinforcement area 2 and the outer connection hole reinforcement area 6 is greater than the thickness of the annular area 4;

[0132] The number of plies of the inner connection hole reinforcement area 2 is N1=N0+N1', where N1' represents the local reinforcement layer of the inner connection hole reinforcement area 2;

[0133] The number of plies N2 of the outer connection hole reinforcement area 6 is N0+N2′, where N2′ represents the local reinforcement layer of the outer connection hole reinforcement area 6 .

[0134] In this embodiment, the thickness of one end of the inner transition zone 3 connected to the annular zone 4 is consistent with the thickness of the annular zone 4, and the thickness of the other end connected to the inner connecting hole reinforcement zone 2 is consistent with the thickness of the inner connecting hole reinforcement zone 2. The thickness of the inner transition zone 3 increases uniformly from the end connected to the annular zone 4 to the end connected to the inner connecting hole reinforcement zone 2. The cutting starting point of the local reinforcement layer of the inner connecting hole reinforcement zone 2 is the inner diameter circle of the composite material membrane disk, and the cutting end point gradually changes from the inner diameter circle of the inner transition zone 3 to the outer diameter circle of the inner transition zone 3, and then gradually changes to the inner diameter circle of the inner transition zone 3. When the cutting end point is the outer diameter circle of the inner transition zone 3, the deflection angle of this layer of composite material is 180°.

[0135] In this embodiment, the thickness of the end of the outer transition zone 5 connected to the annular zone 4 is consistent with the thickness of the annular zone 4, and the thickness of the end connected to the outer connection hole reinforcement zone 6 is consistent with the thickness of the outer connection hole reinforcement zone 6. The thickness of the inner transition zone 3 increases uniformly from the end connected to the annular zone 4 to the end connected to the outer connection hole reinforcement zone 6. The starting point of the cutting of the local reinforcement layer of the outer connection hole reinforcement zone 6 is the outer diameter circle of the composite membrane disk, and the cutting end point gradually changes from the outer diameter circle of the outer transition zone 5 to the inner diameter circle of the outer transition zone 5, and then gradually changes to the outer diameter circle of the outer transition zone 5. When the cutting end point is the inner diameter circle of the outer transition zone 5, the deflection angle of this layer of composite material is 180°. The composite membrane disk is symmetrically distributed along the horizontal neutral plane.

[0136] In this embodiment, the ply layup form of the full ply is

[0137] The plying form of the local reinforcement layer in the inner connection hole reinforcement area 2 is:

[0138] The plying form of the local reinforcement layer in the outer connection hole reinforcement area 6 is:

[0139] s indicates symmetry. The top mark “-” on the ply of the symmetric middle surface indicates that the laying times of each layer of composite material in the local reinforcement layer of the inner connection hole reinforcement area 2 is β1, and the laying times of each layer of composite material in the local reinforcement layer of the outer connection hole reinforcement area 6 is β2.

[0140] In this embodiment, according to the model size and material thickness, the total number of plies N0 of the annular area 4 is 24, the total number of plies N1 of the inner connection hole reinforcement area 2 is 65, and the total number of plies N2 of the outer connection hole reinforcement area 6 is 45. Among them, 24 layers are full plies N0, the number of local reinforcement layers N1' of the inner connection hole reinforcement area 2 is 41; the number of local reinforcement layers N2' of the outer connection hole reinforcement area 6 is 21, the deflection angle of each layer of composite material α = 15°, the number of times each layer of composite material is laid in the local reinforcement layer of the inner connection hole reinforcement area 2 is β1 = 2, and the number of times each layer of composite material is laid in the local reinforcement layer of the outer connection hole reinforcement area 6 is β2 = 1. Mark an origin on the mold, and then divide the circumference into 12 equal parts and mark them. It is worth noting that the local reinforcement layer of the inner connection hole reinforcement area 2 and the local reinforcement layer of the outer connection hole reinforcement area 6 of each layer are located between two layers of full plies.

[0141] The detailed ply information is shown in Table 2 below.

[0142] Table 2 Lamination information of Example 1

[0143]

[0144]

[0145] In this embodiment, the method for preparing the composite film disk comprises the following steps:

[0146] S1. Determine the size of the composite membrane disc, including the inner diameter and outer diameter of the composite membrane disc, the thickness, inner diameter and outer diameter of the inner connection hole reinforcement area 2, the annular area 4 and the outer connection hole reinforcement area 6, and the inner diameter and outer diameter of the inner transition area 3 and the outer transition area 5;

[0147] S2, determining the single layer thickness of the composite material used to form the composite film disc;

[0148] S3, determine the number of plies of the inner connection hole reinforcement area 2 and its local reinforcement layer, the annular area 4, the outer connection hole reinforcement area 6 and its local reinforcement layer, which are N1, N1', N0, N2, N2', respectively, N1 = N0 + N1', N2 = N0 + N2';

[0149] S4. Lay the layers in the mold and mark an origin on the mold. When the fiber direction passes through the center of the circle and points to this point, the layup angle is 0°. The number of layups of a single layer of composite material is β, and the deflection angle of each layer of composite material is Taking the origin as the reference, The annular area 4 is fully paved in the form of a paving layer, and the starting point and the end point of the material cutting are the inner diameter and the outer diameter of the composite material membrane disk respectively;

[0150] by A local reinforcement layer is laid on the inner connection hole reinforcement area 2 in the laying form, the starting point of the material cutting is the inner diameter of the composite material membrane disc, the end point of the material cutting gradually changes from the inner diameter of the inner transition zone 3 to the outer diameter of the inner transition zone 3, and then gradually changes to the inner diameter of the inner transition zone 3, and when the end point of the material cutting is the outer diameter of the inner transition zone 3, the deflection angle of the layer of composite material is 180°;

[0151] by A local reinforcement layer is laid on the outer connection hole reinforcement area 6 in the form of a laying layer, and the starting point of the material cutting is the outer diameter of the composite material membrane disc, and the end point of the material cutting gradually changes from the outer diameter of the outer transition zone 5 to the inner diameter of the outer transition zone 5, and then gradually changes to the outer diameter of the outer transition zone 5, and when the end point of the material cutting is the inner diameter of the outer transition zone 5, the deflection angle of the layer of composite material is 180°;

[0152] According to the symmetry principle of composite material layer design, the composite material diaphragm disc is symmetrically distributed along the horizontal neutral plane;

[0153] The local reinforcement layer of the inner connection hole reinforcement area 2 and the local reinforcement layer of the outer connection hole reinforcement area 6 of each layer are located between two layers of full plies, and the ply angle is consistent with the angle of the previous full ply;

[0154] S5, the upper mold and the lower mold are combined and heated for curing, the curing temperature is 130° C., the curing time is 2 hours, the curing pressure is 10 Bar, and the composite material membrane disk is obtained by curing and demoulding.

[0155] Comparative Example 1

[0156] The composite membrane disk was prepared by conventional orthogonal plying, and compared with Example 1, most of the features were the same, except that:

[0157] The ply layout of the full ply is:

[0158] [0° / 45° / -45° / 90° / 90° / -45° / 45° / 0° / 0° / 45° / -45° / 90° / 90° / -45° / 45° / 0°] S ;

[0159] The plying form of the local reinforcement layer of the inner connection hole reinforcement area 2 is:

[0160] [0° / 45° / -45° / 90° / 90° / -45° / 45° / 0° / 0° / 45° / -45° / 90° / 90° / -45° / 45° / 0°] S ;

[0161] The plying form of the local reinforcement layer of the outer connection hole reinforcement area 6 is:

[0162] [0° / 45° / -45° / 90° / 90° / -45° / 45° / 0° / 0° / 45° / -45° / 90° / 90° / -45° / 45° / 0°] S .

[0163] The plying form refers to the plying form of Example 1 in Patent Publication No. CN110821979A, and the other conditions are consistent with the conditions in Example 1 of the present invention.

[0164] The performance of the prepared composite membrane disk was tested.

[0165] Figure 3 and Figure 4 The stress cloud diagrams of the composite membrane disks prepared in Example 1 and Comparative Example 1 at a rotation speed of 15000 rpm show that at the same operating speed, the composite membrane disks prepared by the lamination method of the present invention have lower stress levels and more uniform stress distribution.

[0166] Figure 5 and Figure 6 The displacement cloud diagrams of the composite membrane disks prepared in Example 1 and Comparative Example 1 under a torque of 5000 N·m show that, under the same torque, the torsional stiffness of the composite membrane disk designed according to the lamination method of the present invention is consistent with that of the orthogonal lamination.

[0167] Figure 7 and Figure 8 The displacement cloud diagrams of the composite membrane disks prepared in Example 1 and Comparative Example 1 under a bending moment of 500 N·m show that under the same bending moment, the bending stiffness of the composite membrane disk designed according to the lamination method of the present invention is higher than that of the traditional orthogonal lamination.

[0168] In summary, the circumferential quasi-isotropic composite material diaphragm disk and its preparation method provided by the present invention are more suitable for the load conditions of the product than the traditional orthogonal lamination scheme, can reduce the stress level of the diaphragm disk and improve the utilization rate of fiber materials.

[0169] Although the present invention has been described in detail above by means of general description, specific implementation methods and tests, it is obvious to those skilled in the art that some modifications or improvements may be made to the present invention. Therefore, these modifications or improvements made without departing from the spirit of the present invention all fall within the scope of protection claimed by the present invention.

Claims

1. A circumferentially quasi-isotropic composite material diaphragm disk, characterized in that: The composite material membrane disk comprises a central through hole (1) and an annular area (4) arranged concentrically therewith, an inner connecting hole reinforcement area (2) arranged concentrically with the central through hole (1) is arranged on the inner side of the annular area (4), and an outer connecting hole reinforcement area (6) arranged concentrically with the central through hole (1) is arranged on the outer side of the annular area (4); The composite membrane disc is obtained by hot pressing composite material plies, and the plies are in the form of The number of plies in the annular area (4) is N0, the deflection angle of the next ply in the two adjacent layers of composite material relative to the previous ply in the same direction is α, the number of times each layer of composite material is laid is β, Symmetrical plies are written with only half of the ply, and the subscript "s" outside the brackets indicates symmetry.

2. A circumferentially quasi-isotropic composite material diaphragm disk according to claim 1, characterized in that: The number of layers of the annular zone (4) is the full number of layers, the starting point of material cutting is the inner diameter circle of the composite material membrane disc, and the end point of material cutting is the outer diameter circle of the composite material membrane disc.

3. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 1, characterized in that: The thickness of the inner connection hole reinforcement area (2) and the outer connection hole reinforcement area (6) is greater than the thickness of the annular area (4); The number of plies of the inner connection hole reinforcement area (2) is N1=N0+N1', where N1' represents the number of plies of the local reinforcement layer of the inner connection hole reinforcement area (2); The number of plies N2 of the outer connection hole reinforcement area (6) is N0+N2', where N2' represents the number of plies of the local reinforcement layer of the outer connection hole reinforcement area (6).

4. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 3, characterized in that: The local reinforcement layer of the inner connection hole reinforcement area (2) and the local reinforcement layer of the outer connection hole reinforcement area (6) are evenly distributed between the two layers of the annular area (4), and the layer laying angle is consistent with the previous full layer laying angle; The starting point of cutting the local reinforcement layer of the inner connection hole reinforcement area (2) is the inner diameter circle of the composite material membrane disk, and the end point of cutting is the outer diameter circle of the inner connection hole reinforcement area (2); The starting point for cutting the local reinforcement layer of the outer connection hole reinforcement area (6) is the outer diameter circle of the composite material membrane disk, and the ending point for cutting is the inner diameter circle of the outer connection hole reinforcement area (6).

5. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 3, characterized in that: The plying form of the local reinforcement layer of the inner connection hole reinforcement area (2) is: The plying form of the local reinforcement layer of the outer connection hole reinforcement area (6) is: s represents symmetry, and a top mark "-" is added to the ply of the symmetric middle surface to indicate that the number of times each layer of composite material is laid in the local reinforcement layer of the inner connection hole reinforcement area (2) is β1, and the number of times each layer of composite material is laid in the local reinforcement layer of the outer connection hole reinforcement area (6) is β2.

6. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 3, characterized in that: The annular area (4) is connected to the inner connection hole reinforcement area (2) via an inner transition area (3); The annular area (4) is connected to the outer connection hole reinforcement area (6) via an outer transition area (5).

7. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 6, characterized in that: The thickness of the end of the inner transition zone (3) connected to the annular zone (4) is consistent with the thickness of the annular zone (4), and the thickness of the end connected to the inner connection hole reinforcement zone (2) is consistent with the thickness of the inner connection hole reinforcement zone (2); the thickness of the inner transition zone (3) increases from the end connected to the annular zone (4) to the end connected to the inner connection hole reinforcement zone (2); The thickness of the end of the outer transition zone (5) connected to the annular zone (4) is consistent with the thickness of the annular zone (4), and the thickness of the end connected to the outer connection hole reinforcement zone (6) is consistent with the thickness of the outer connection hole reinforcement zone (6); the thickness of the inner transition zone (3) increases from the end connected to the annular zone (4) to the end connected to the outer connection hole reinforcement zone (6).

8. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 7, characterized in that: The starting point of the blanking of the local reinforcement layer of the inner connection hole reinforcement zone (2) is the inner diameter circle of the composite material membrane disk, and the end point of the blanking gradually changes from the inner diameter circle of the inner transition zone (3) to the outer diameter circle of the inner transition zone (3), and then gradually changes to the inner diameter circle of the inner transition zone (3), and when the end point of the blanking is the outer diameter circle of the inner transition zone (3), the deflection angle of the layer of composite material is 180°; The starting point of the blanking of the local reinforcement layer of the outer connection hole reinforcement zone (6) is the outer diameter circle of the composite material membrane disk, and the end point of the blanking gradually changes from the outer diameter circle of the outer transition zone (5) to the inner diameter circle of the outer transition zone (5), and then gradually changes to the outer diameter circle of the outer transition zone (5), and when the blanking end point is the inner diameter circle of the outer transition zone (5), the deflection angle of the layer of composite material is 180°; The composite material membrane disks are symmetrically distributed along a horizontal neutral plane.

9. The circumferentially quasi-isotropic composite material diaphragm disk according to claim 1, characterized in that: The composite material is a fiber-reinforced resin-based composite material; A layer of carbon fiber orthogonal fabric is laid on the upper and lower surface layers of the composite material membrane disk as an outer protective layer.

10. A method for preparing a circumferentially quasi-isotropic composite material membrane disk according to any one of claims 1 to 9, characterized in that: The composite material The composite material membrane disc is obtained by laying layers in a mold in the form of a plurality of layers, closing the upper mold and the lower mold for heating and curing, and curing and demoulding.

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