Method for calculating layer boundary compensation amount of composite material piece with rotary body structure

Abstract

The invention belongs to the technical field of composite material manufacturing, and relates to a rotary body structure composite material piece laying layer boundary compensation amount calculation method, which comprises the following steps: S1, measuring the ratio X of the pre-forming thickness to the theoretical thickness of a prepreg; s2, calculating a difference delta C between the length of a circle at a theoretical position and the length of a circle at an actual position of the Nth layer of prepreg; and S3, calculating the laying layer boundary compensation amount of the Nth layer of prepreg. The method solves the problem that when a large-thickness rotary body structure composite part is laid based on a reduced core mold, a boundary line in a design digital model is used for carrying out laser projection design, and the projection position is relatively small relative to the theoretical position.

Description

Technical Field

[0001] The invention belongs to the technical field of composite material manufacturing, and relates to a method for calculating the compensation amount of a laser projection boundary relative to a theoretical boundary when a composite material part of a rotating body structure with large thickness is draped based on a reduced core mold. Background Art

[0002] Composite layer laser projection positioning technology is an advanced technology widely used in industries such as aviation, aerospace, automobile and wind turbine blade manufacturing. The core of this technology is to use a laser system to project high-precision broken lines and contours on the mold or workpiece surface to guide the precise laying of composite materials. These projected laser lines are generated based on the true-to-scale CAD data image, which greatly improves the production accuracy and efficiency of composite parts.

[0003] The CAD model used to generate the laser projection data of the composite material layup is called the composite material layup process model. Using Fibersim software, according to the product digital model and following the conventional operating steps, the composite material layup process model can be easily established. This part is the prior art and the present invention will not be described in detail here. With the advancement of industrial technology and the increasing demand for high-performance composite materials, higher requirements are placed on the design of composite material layup process models. In particular, the demand for the development of heavy helicopters has put forward new requirements for the design of composite material layup process models for large-thickness rotating body structural parts.

[0004] After much research and exploration, the process scheme of core mold laying and external mold shape control is proposed for the composite parts of the rotating body structure. The layup information of the product digital model is designed based on the outer surface. The final manufacturing needs to ensure the structure of the outer surface and the product thickness requirements. The actual forming process is to lay outward layer by layer with the core mold surface as the reference surface. In order to ensure the accuracy of the laser projection position, the layup process model should select the core mold surface as the layup reference surface for design.

[0005] Theoretically, the core mold surface should be the theoretical inner shape of the product, but for thick rotating body structure composite parts, the prepreg "press thickness ratio" is large. After the layering is completed, the thickness of the preform is 30%-40% larger than the theory. In this state, it cannot be returned to the hard molding mold to complete the mold closing. At the same time, considering the influence of material accumulation at the overlap and arc of the layer under the small-sized airbag, in order to meet the mold entry requirements after layering, the core mold needs to shrink inward by a certain proportion based on the theoretical inner shape of the product.

[0006] The design of the composite layup process model is based on the reduced core mold surface. If the boundary line in the design digital model is directly used for laser projection design, the projection position will be smaller than the theoretical position. In this case, it is necessary to study a method for calculating the compensation amount of the laser projection boundary relative to the theoretical boundary when laying composite parts of large thickness rotating body structures based on reduced core molds. The margin should be increased on the basis of the theoretical boundary of the product digital model to ensure the accuracy of the laser projection position. Summary of the invention

[0007] The technical problem solved by the present invention is: to provide a method for calculating the boundary compensation amount of the ply of a composite part of a rotating body structure, so as to solve the problem that when a composite part of a rotating body structure with large thickness is clad based on a reduced core mold, laser projection design is performed using the boundary line in the designed digital model, and the projection position is smaller than the theoretical position.

[0008] Technical solution of the present invention

[0009] A method for calculating the ply boundary compensation amount of a composite material component of a rotating body structure comprises the following steps:

[0010] S1. Measure the ratio X of the prepreg preform thickness to the theoretical thickness;

[0011] S2, calculating the difference ΔC between the length of one circle of the Nth layer of prepreg at the theoretical position and the length of one circle of the actual position;

[0012] S3. Calculate the ply boundary compensation amount of the Nth layer of prepreg.

[0013] Further, step S1 specifically comprises: taking several layers of prepreg of the same size, laying them out and vacuum compacting them, measuring their molding thickness, calculating the theoretical thickness of the several layers of prepreg, and then finding the ratio X of the molding thickness to the theoretical thickness.

[0014] Further, step S2 includes the following steps:

[0015] S2.1 Calculate the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent prepreg layers for each layer;

[0016] S2.2 Based on the design digital model, use software to make the theoretical paving surface of each layer of prepreg, so as to measure the theoretical arc length C2 of each layer of prepreg;

[0017] S2.3 Calculate the theoretical arc length difference ΔC2 for each layer of prepreg;

[0018] S2.4 Calculate the actual arc length difference ΔC1 for each layer of prepreg;

[0019] S2.5 Calculate the difference ΔC between the length of one circle of the Nth layer of prepreg at the theoretical position and the length of one circle of the actual position.

[0020] Further, in step S2.1, the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent layers of prepreg includes:

[0021] The actual arc radius of the Nth layer R1=r+Nδ1

[0022] Theoretical arc radius of the Nth layer R2=R+Nδ2

[0023] The actual position of the Nth layer has a circle length of C1 = 2πR1 + 2A = 2π(r + Nδ1) + 2A

[0024] The length of a circle at the theoretical position of the Nth layer C2=2πR2+2A=2π(R+Nδ2)+2A

[0025] ΔC=C2-C1=2π(R+Nδ2)-2π(r+Nδ1)

[0026] When laying each layer in the actual position, the arc length difference ΔC1 between the upper and lower adjacent layers of prepreg cross section is:

[0027] ΔC1=[2π(r+Nδ1)+2A]-{2π[r+(N-1)δ1]+2A}=2πδ1

[0028] The difference in arc length between the upper and lower adjacent layers of prepreg in the cross section is ΔC2:

[0029] ΔC2=[2π(R+Nδ2)+2A]-{2π[R+(N-1)δ2]+2A}=2πδ2

[0030] Substituting the compression thickness ratio X for calculation, we get δ1=Xδ2, then we can get the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent layers of prepreg:

[0031] ΔC1=XΔC 2；

[0032] Wherein, r is the radius of the arc segment of the core mold, R is the radius of the arc segment of the inner profile of the composite part of the body of revolution structure, A is the length of the straight section of the composite part of the body of revolution structure, δ1 is the actual thickness of the prepreg, δ2 is the theoretical thickness of the prepreg, and N is the number of prepreg layers.

[0033] Furthermore, in step 2.4, the actual arc length difference ΔC1 of each layer of prepreg is calculated by the formula ΔC1=XΔC2.

[0034] Further, step S2.5 calculates the difference ΔC between the length of one circle of the Nth layer of prepreg at the theoretical position and the length of one circle of the actual position by the following formula:

[0035] ΔC = C2-C1 (1)

[0036] Wherein, C1 is the length of one circle of the actual position of the Nth layer of prepreg, and C2 is the length of one circle of the theoretical position of the Nth layer of prepreg.

[0037] Further, step S3 calculates the ply boundary compensation of the Nth layer, that is, calculates the difference ΔL between the arc length of the actual arc line of the Nth layer of prepreg projected onto the core mold surface and the arc length of the theoretical arc line projected onto the core mold surface 投 .

[0038] Further, step S3 specifically includes the following steps:

[0039] Step S3.1 intercepts a section of the actual arc line of the Nth layer, and calculates the arc length L of the actual arc line of the Nth layer projected onto the core mold surface when the corresponding central angle of the arc section is β. 投 The actual arc length L 实 ratio;

[0040] Step S3.2 Calculate the actual arc length ΔL of the Nth layer of prepreg when the central angle of the intercepted arc segment is Δα 实 :

[0041] S3.3 Calculate the ply boundary compensation ΔL of the Nth layer of prepreg 投 , that is, ΔL 投 =rΔC / (r+NXδ2).

[0042] Furthermore, in step S1, the number of prepreg layers taken is 50.

[0043] Furthermore, in step S1, the size of the prepreg obtained is 100 mm×100 mm.

[0044] Beneficial Effects

[0045] 1. The method of the present invention obtains the compensation amount of the laser positioning boundary relative to the theoretical boundary when laying the composite parts of the rotating structure through scientific calculation, which is used for the design of the composite laying process model, directly generates accurate laser projection data, and uses the laser system to project high-precision broken lines and contours on the surface of the mold or workpiece to guide the precise laying of the composite materials, thereby significantly improving the manufacturing accuracy and production efficiency of the composite parts of the rotating structure.

[0046] 2. The method of the present invention provides an accurate manufacturing basis for the laying of the composite parts of the rotating structure, avoids the risk of scrapping the composite parts of the rotating structure during manufacturing, and saves manufacturing costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 It is a schematic diagram of the cross-sectional structure of a composite material component of a rotating body structure;

[0048] Figure 2 This is a schematic diagram of compensation calculation. DETAILED DESCRIPTION

[0049] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0050] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0051] One embodiment of the present invention is that the method for calculating the ply boundary compensation amount of a composite material component of a rotating body structure provided by the present invention adopts the following calculation steps:

[0052] S1. Measure the ratio X of the prepreg preform thickness to the theoretical thickness, referred to as the pressed thickness ratio.

[0053] Take several layers of prepreg of the same size, lay them out and vacuum compact them, measure their thickness, calculate the theoretical total thickness of the several layers of prepreg, and then find the ratio X of the two thicknesses;

[0054] S2. Calculate the difference ΔC between the length of one circle at the theoretical position of the Nth layer and the length of one circle at the actual position.

[0055] See also Figure 1 , simplify the calculation by taking the cross section of the rotating body and the core mold as an oblong.

[0056] The radius of the arc (i.e. actual position) of the core mold is r, the radius of the arc (i.e. theoretical position) of the inner mold surface of the rotating body is R, the length of the straight section is set to A, the actual thickness of the material is δ1, and the theoretical thickness of the material is δ2.

[0057] S2.1 Calculate the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent prepreg layers for each layer;

[0058] The actual arc radius of the Nth layer R1=r+Nδ1

[0059] Theoretical arc radius of the Nth layer R2=R+Nδ2

[0060] The actual position of the Nth layer has a circle length of C1 = 2πR1 + 2A = 2π(r + Nδ1) + 2A

[0061] The length of a circle at the theoretical position of the Nth layer C2=2πR2+2A=2π(R+Nδ2)+2A

[0062] ΔC=C2-C1=2π(R+Nδ2)-2π(r+Nδ1)

[0063] When laying each layer in the actual position, the arc length difference ΔC1 between the upper and lower adjacent layers of prepreg cross section is:

[0064] ΔC1=[2π(r+Nδ1)+2A]-{2π[r+(N-1)δ1]+2A}=2πδ1

[0065] The difference in arc length between the upper and lower adjacent layers of prepreg in the cross section is ΔC2:

[0066] ΔC2=[2π(R+Nδ2)+2A]-{2π[R+(N-1)δ2]+2A}=2πδ2

[0067] Substitute the pressure-thickness ratio X for calculation, δ1=Xδ2, then ΔC1=XΔC 2。

[0068] S2.2 Based on the design model, the software can be used to make the theoretical paving surface of each layer, so that the theoretical arc length C2 of each layer can be measured;

[0069] S2.3 Calculate the theoretical arc length difference ΔC2 for each layer;

[0070] S2.4 Calculate the actual arc length difference ΔC1 of each layer, ΔC1 = XΔC2;

[0071] The arc length of the S2.5 core mold can be measured, that is, the actual arc length of the first layer can be measured, and then the arc length C1 of each layer at the actual position can be obtained; then the difference ΔC between the length of a circle at the theoretical position of the Nth layer and the length of a circle at the actual position can be calculated.

[0072] S3. Calculate the ply boundary compensation of the Nth layer, that is, the difference ΔL between the arc length of the actual arc of the Nth layer projected onto the core mold surface and the arc length of the theoretical arc projected onto the core mold surface 投 .

[0073] See also Figure 2 , intercept a section of the actual arc of the Nth layer for calculation. Assume that the center angle of the Nth layer is α, the radius is R2, and the length of the theoretical position arc is L 理 , which is exactly equal to the length L of the arc at the actual paving position of the Nth layer with a central angle of β and a radius of R1 实 ,So:

[0074] L 理 =αR2=L 实 =βR1

[0075] S3.1 Calculate the corresponding central angle β, and the arc length L of the actual arc line of the Nth layer projected onto the core mold surface 投 The actual arc length L 实 The ratio:

[0076] L 投 / L 实 =βr / βR1=r / R1

[0077] ΔL 投 / ΔL 实 =Δαr / ΔαR 1=r / R1

[0078] ΔL 投 / ΔL 实 =L 投 / L 实

[0079] S3.2 Calculate the corresponding center angle Δα, the actual arc length ΔL of the Nth layer 实 :

[0080] ΔL 实 =L 实 -αR1=L 理 -αR1=αR2-αR1=α(R2-R1)

[0081] S3.3 Calculate the ply boundary compensation ΔL for the Nth layer 投

[0082] ΔL 投 = rΔL 实 / R1

[0083] =rα(R2-R1) / R1

[0084] =rα[(R+Nδ2)-(r+Nδ1)] / (r+Nδ1)

[0085] =r[α(R+Nδ2)-α(r+Nδ1)] / (r+Nδ1)

[0086] =r[α(R+Nδ2)-α(r+Nδ1)] / (r+NXδ2)

[0087] When α=360°, α=2π, which means the Nth layer is actually laid in one circle.

[0088] ΔL 投 =r[2π(R+Nδ2)-2π(r+Nδ1)] / (r+NXδ2)

[0089] =r(C2-C1) / (r+NXδ2)

[0090] =rΔC / (r+NXδ2)

[0091] Given r, ΔC, N, X, and δ2, the ply boundary compensation amount of the Nth layer can be approximately calculated according to the above formula.

[0092] A second embodiment of the present invention provides a method for calculating the ply boundary compensation amount of a composite part of a rotating body structure, comprising the following steps:

[0093] S1. A certain rotating structure composite part is laid with prepreg, and the prepreg thickness ratio is 1.62.

[0094] S2. Calculate the difference ΔC between the length of one circle at the theoretical position of the Nth layer and the length of one circle at the actual position.

[0095] See also Figure 1 , simplify the calculation by taking the cross section of the rotating body and the core mold as an oblong.

[0096] The radius of the arc (i.e. actual position) of the core mold is r, the radius of the arc (i.e. theoretical position) of the inner mold surface of the rotating body is R, the length of the straight section is set to A, the actual thickness of the material is δ1, and the theoretical thickness of the material is δ2.

[0097] The actual arc radius of the Nth layer R1=r+Nδ1

[0098] Theoretical arc radius of the Nth layer R2=R+Nδ2

[0099] The actual position of the Nth layer has a circle length of C1 = 2πR1 + 2A = 2π(r + Nδ1) + 2A

[0100] The length of a circle at the theoretical position of the Nth layer C2=2πR2+2A=2π(R+Nδ2)+2A

[0101] ΔC=C2-C1=2π(R+Nδ2)-2π(r+Nδ1)

[0102] When laying each layer in the actual position, the arc length difference ΔC1 between the upper and lower adjacent layers of prepreg cross section is:

[0103] ΔC1=[2π(r+Nδ1)+2A]-{2π[r+(N-1)δ1]+2A}=2πδ1

[0104] The difference in arc length between the upper and lower adjacent layers of prepreg in the cross section is ΔC2:

[0105] ΔC2=[2π(R+Nδ2)+2A]-{2π[R+(N-1)δ2]+2A}=2πδ2

[0106] Substituting the pressure-thickness ratio X for calculation, δ1=1.62δ2, then ΔC1=1.62ΔC2

[0107] According to the design digital model, the software can be used to make the theoretical paving surface of each layer, so that the arc length C2 of each layer can be measured, and the theoretical arc length difference ΔC2 of each layer can be calculated, and the actual arc length difference ΔC1 of each layer can be obtained; the arc length of the core model can be measured, and then the arc length C1 of each layer at the actual position can be obtained; then the difference ΔC between the length of a circle at the theoretical position of the Nth layer and the length of a circle at the actual position can be calculated.

[0108] S3. Calculate the ply boundary compensation of the Nth layer, that is, the difference ΔL between the arc length of the actual arc of the Nth layer projected onto the core mold surface and the arc length of the theoretical arc projected onto the core mold surface 投 .

[0109] See also Figure 2 , intercept a section of the arc for calculation. Assume that the center angle of the Nth layer is α and the radius is R2. The length of the arc at the theoretical position is L 理 , which is exactly equal to the length L of the arc at the actual paving position of the Nth layer with a central angle of β and a radius of R1 实 ,So:

[0110] L 理 =αR2=L 实 =βR1

[0111] The corresponding central angle is β, and the arc length L of the actual arc line of the Nth layer projected onto the core mold surface 投 The actual arc length L 实 Ratio: L 投 / L 实 =βr / βR1=r / R1

[0112] ΔL 投 / ΔL 实 =Δαr / ΔαR 1=r / R1

[0113] ΔL 投 / ΔL 实 =L 投 / L 实

[0114] ΔL 实 =L 实 -αR1=L 理 -αR1=αR2-αR1=α(R2-R1)

[0115] ΔL 投 = rΔL 实 / R1

[0116] =rα(R2-R1) / R1

[0117] =rα[(R+Nδ2)-(r+Nδ1)] / (r+Nδ1)

[0118] =r[α(R+Nδ2)-α(r+Nδ1)] / (r+Nδ1)

[0119] =r[α(R+Nδ2)-α(r+Nδ1)] / (r+NXδ2)

[0120] When α=360°, α=2π, then

[0121] ΔL 投 =r[2π(R+Nδ2)-2π(r+Nδ1)] / (r+NXδ2)

[0122] =r(C2-C1) / (r+NXδ2)

[0123] =rΔC / (r+NXδ2)

[0124] Given X=1.62, r=46.5, δ2=0.319, N=1, 2, 3…, and the length of one circle of the core mold is 1035.15 mm, C2 is measured layer by layer, and ΔC2, ΔC1, C1, and ΔC are calculated in sequence. The ply boundary compensation ΔL of the Nth layer can be approximately calculated according to the above formula. 投 , as shown in Table 1.

[0125] Table 1 Data table of the Nth layer's ply boundary compensation

[0126] N <![CDATA[C2]]> <![CDATA[ΔC2]]> <![CDATA[ΔC1]]> <![CDATA[C1]]> ΔC <![CDATA[ΔL 投 ]]> Core mold / inner surface 1140.557 1035.15 105.41 1 1142.544 1.987 3.21894 1038.37 104.17 25.75701 2 1144.531 1.987 3.21894 1041.59 102.94 25.1757 3 1146.518 1.987 3.21894 1044.81 101.71 24.60689 4 1148.262 1.744 2.82528 1047.63 100.63 24.08624 5 1150.007 1.745 2.8269 1050.46 99.55 23.57641 …… …… …… …… …… …… ……

[0127] According to the Nth layer boundary compensation ΔL calculated above 投 , project the theoretical boundary of the product digital model onto the core mold surface, and obtain the actual laser projection boundary after adding the corresponding margin to each layer. Use Fibersim software to output the laser projection data. The actual production verification shows that this calculation method is accurate and effective, which significantly improves the manufacturing accuracy and production efficiency of the composite parts of the rotating structure and saves manufacturing costs.

[0128] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or substitutions within the technical scope disclosed by the present invention, and these modifications or substitutions should all be covered within the protection scope of the present invention.

Claims

1. A method for calculating the ply boundary compensation of a composite part of a rotating structure, characterized in that: The following steps are involved: S1. Measure the ratio X of the prepreg preform thickness to the theoretical thickness; S2, calculating the difference ΔC between the length of one circle of the Nth layer of prepreg at the theoretical position and the length of one circle of the actual position; S3. Calculate the ply boundary compensation amount of the Nth layer of prepreg.

2. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 1, characterized in that: Step S1 specifically comprises: taking several layers of prepreg of the same size, laying them out and vacuum compacting them, measuring their molding thickness, calculating the theoretical thickness of the several layers of prepreg, and then finding the ratio X of the molding thickness to the theoretical thickness.

3. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 2, characterized in that: Step S2 includes the following steps: S2.1 Calculate the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent prepreg layers for each layer; S2.2 Based on the design digital model, use software to make the theoretical paving surface of each layer of prepreg, so as to measure the theoretical arc length C2 of each layer of prepreg; S2.3 Calculate the theoretical arc length difference ΔC2 for each layer of prepreg; S2.4 Calculate the actual arc length difference ΔC1 for each layer of prepreg; S2.5 Calculate the difference ΔC between the length of one circle of the Nth layer of prepreg at the theoretical position and the length of one circle of the actual position.

4. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 3, characterized in that: In step S2.1, the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent prepreg layers includes: The actual arc radius of the Nth layer R1=r+Nδ1 Theoretical arc radius of the Nth layer R2=R+Nδ2 The actual position of the Nth layer has a circle length of C1 = 2πR1 + 2A = 2π(r + Nδ1) + 2A The length of a circle at the theoretical position of the Nth layer C2=2πR2+2A=2π(R+Nδ2)+2A ΔC=C2-C1=2π(R+Nδ2)-2π(r+Nδ1) When laying each layer in the actual position, the arc length difference ΔC1 between the upper and lower adjacent layers of prepreg cross section is: ΔC1=[2π(r+Nδ1)+2A]-{2π[r+(N-1)δ1]+2A}=2πδ1 The difference in arc length between the upper and lower adjacent layers of prepreg in the cross section is ΔC2: ΔC2=[2π(R+Nδ2)+2A]-{2π[R+(N-1)δ2]+2A}=2πδ2 Substituting the compression thickness ratio X for calculation, we get δ1=Xδ2, then we can get the relationship between the theoretical value and the actual value of the arc length difference on the cross section of the upper and lower adjacent layers of prepreg: ΔC1=XΔC 2； Wherein, r is the radius of the arc segment of the core mold, R is the radius of the arc segment of the inner profile of the composite part of the body of revolution structure, A is the length of the straight section of the composite part of the body of revolution structure, δ1 is the actual thickness of the prepreg, δ2 is the theoretical thickness of the prepreg, and N is the number of prepreg layers.

5. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 4, characterized in that: In step 2.4, the actual arc length difference ΔC1 of each layer of prepreg is calculated by the formula ΔC1=XΔC2.

6. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 5, characterized in that: Step S2.5 calculates the difference ΔC between the length of one circle of the Nth layer of prepreg at the theoretical position and the length of one circle of the actual position by the following formula: ΔC = C2-C1 (1) Wherein, C1 is the length of one circle of the actual position of the Nth layer of prepreg, and C2 is the length of one circle of the theoretical position of the Nth layer of prepreg.

7. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 6, characterized in that: Step S3 calculates the ply boundary compensation of the Nth layer, that is, calculates the difference ΔL between the arc length of the actual arc line of the Nth layer of prepreg projected onto the core mold surface and the arc length of the theoretical arc line projected onto the core mold surface 投 .

8. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 7, characterized in that: Step S3 specifically includes the following steps: Step S3.1 intercepts a section of the actual arc line of the Nth layer, and calculates the arc length L of the actual arc line of the Nth layer projected onto the core mold surface when the corresponding central angle of the arc section is β. 投 The actual arc length L 实 ratio; Step S3.2 Calculate the actual arc length ΔL of the Nth layer of prepreg when the central angle of the intercepted arc segment is Δα 实 : S3.3 Calculate the ply boundary compensation ΔL of the Nth layer of prepreg 投 , that is, ΔL 投 =rΔC / (r+NXδ2).

9. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 2, characterized in that: In step S1, the number of prepreg layers taken is 50.

10. The method for calculating the ply boundary compensation of a composite part of a rotating structure according to claim 2, characterized in that: In step S1, the size of the prepreg obtained is 100 mm×100 mm.

Images