# Structural Design and Mechanical Performance Analysis of Carbon Fiber Closed Fixtures for UHV Transmission Lines

Authors: Yujiao Zhang; Cheng Yan; Xiongfeng Huang; Yanran Chen
Journal: Mathematical Problems in Engineering
 (2021)

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## Abstract

The closed clamp is a standard tool for the insulator replacement in ultrahigh voltage (UHV) transmission lines, which is mainly made of titanium alloy material and weighs more than 27 kg that greatly reduces the working efficiency for operators. Due to the lightweight demand, carbon fiber composite materials are applied to design a new type of clamp, in which mechanical properties of new fixtures need to be fulfilled while considering poor impact resistance and low interlaminar shear strength of carbon fiber composite materials. To excavate a high-strength ply structure, finite element progressive damage strength analysis is employed to evaluate the mechanical properties of three different ply angles of the carbon fiber closed fixture, in which Tsai–Wu strength theory is thought as the strength judgment basis for carbon fiber composite materials. After comparison with the displacement-load curves, the three different ply angles fail to meet the strength requirements. So, a carbon fiber laminate structure with an outer cladding for carbon fiber closed fixtures is raised and verified. The analysis results show that the laminate structure meets the strength requirements. Destructive test of the new closed clamp is conducted to verify the correctness of the proposed method, and the weight is reduced by 36.46%.


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## Body

## 1. Introduction

The closed fixture is the most commonly used tool for replacing the porcelain or glass insulators in ultrahigh voltage transmission lines, which consists of a front fixture, a rear fixture, and a screw, as shown in Figure1. Currently, closed clamps are mainly made of titanium alloy materials [1, 2]. Because of large size and large load of the insulators, the weight of titanium alloy closed clamps has increased to about 27 kg with the strength requirements. For the workers, it is extremely inconvenient to operate, which reduces the efficiency of insulator replacement. Therefore, lightweight demand is aroused for the design of the closed fixture.Figure 1
Titanium alloy closed fixture.Carbon fiber composite materials are light materials, which are fit for reducing the weight of closed clamp, because the density of carbon fiber materials is 0.38 times that of titanium alloy materials, and the strength is more than 5 times that of titanium alloy materials [3]. But considering poor impact resistance and low interlaminar shear strength [4, 5], carbon fiber material is difficult to achieve the required mechanical properties for large load-bearing components like UHV closed clamps.As carbon fiber composites are the same as polymer matrix composites, different thickness and mechanical properties (Young’s modulus and strain energy release rate) have great influence on the mechanical properties of the composites [6, 7]. Therefore, in order to meet the mechanical performance requirements, carbon fiber laminate structures need to be elaborated. A quasi-isotropic pavement structure with 0°, ±45°, and 90° cross-arrangement is proposed to meet the mechanical performance requirements of some bent and sheared parts [8–11]. And to reduce the weight and improve the flexural rigidity and the stability, a carbon fiber foam sandwich structure is discussed in the aerospace [12–15]. For this sandwich structure, the upper and lower panels mainly bear in-plane tensile and compression, and in-plane shear loads, while the core bears compression and shear loads. Although these pavement structures meet the mechanical performance requirements, they are only used on small load-bearing components. For the big load-bearing closed fixtures which require a weight of less than 20 kg and a strength of more than 200 kN, this type of application is scarce, so a new layer structure needs to be exploited for the carbon fiber closed fixture. To assess the strength of carbon fiber members quickly and accurately, the progressive damage strength analysis method is employed [16–18] as the finite element strength analysis method of carbon fiber members, and Tsai–Wu strength theory is preferred as the strength judgment. At present, the most commonly used strength theories are Hoffman strength theory, Tsai–Hill strength theory, and Tsai–Wu strength theory [19–21]. Usually, Tsai–Wu strength theory is thought as a higher accuracy and more comprehensive description of materials than other theories.In this paper, a novel carbon fiber laminate structure with an outer cladding for carbon fiber closed fixtures is proposed for the design of new 1000 kV ultrahigh voltage closed fixture. Compared with the structure of the traditional titanium alloy closed fixture, the structure of the carbon fiber closed fixture is raised considering the enhancement of the shear and bending resistance at the ends of the two wings of the fixture. To protect the carbon fiber from being damaged and improve the bending resistance and shear strength of the new fixture, this paper firstly designs a new shape for the carbon fiber closed fixture and proposes three traditional bending and shear strength ply structures. To compare and analyze the mechanical properties of the three types, the finite element progressive damage strength analysis method is employed, in which Tsai–Wu tensor theory is thought as the strength judgment basis for carbon fiber composite materials. Then, on the basis of the three traditional layup structures, a novel layup structure with an outer cladding is designed for the fixture to further increase the strength. At last, the mechanical test is to be conducted by the tensile machine for the verification of the feasibility of the structural design and the effectiveness of the finite element calculation.


## 2. Structural Design of the Carbon Fiber Closed Fixture

### 2.1. Shape Structure of the Traditional Titanium Alloy Closed Fixture

To design the new structure of the 1000 kV closed fixture based on carbon fiber materials, the XWP-420 closed fixture made of titanium alloy material is selected as a reference, in which the rated load is 80 kN, the safety factor is 2.5 with 200 kN maximum load, and the total weight is 27.48 kg. The outline structure of XWP-420 is shown in Figure2. The difference between the front fixture and the rear fixture is only the structure of the inner cavity, and the rest are the same.Figure 2
Schematic diagram of XWP-420 closed fixture: (a) front fixture; (b) rear fixture.
(a)(b)When replacing the insulator, the front clamp and the rear clamp are, respectively, clamped on the front and rear insulator steel caps. And then the screw rod is tightened to transfer the load on the insulator to the clamp. Finally, the operator removes the insulator and replaces it with a new one, as shown in Figure3(a).Figure 3
Analysis of the stress characteristics of the closed fixture: (a) closed fixture work diagram; (b) closed fixture force diagram.
(a)(b)While tightening the screw rod of the closed fixture, the contact part between the closed fixture and the steel cap is regarded as fixed constraint and the end of the left and right wings is regarded as the loading end [1]. And during the analysis of the mechanical properties, the front fixture and the rear fixture are regarded as a simple beam balanced by three points of force shown in Figure 3(b), considering that the forces and dimensions of the front and rear fixtures are exactly the same.According to the loading characteristics and boundary conditions of the fixture, the structure mainly bears the bending moment and shear force. The overall structure is simplified as a simply supported cantilever beam.


### 2.2. Concept of Exterior Design

According to the working condition of the closed fixture, since the inner cavity wall of the closed fixture directly contacts the insulator steel cap, the inner cavity wall will be rubbed by the steel cap when the screw is tightened. Therefore, considering that carbon fiber is a non-wear-resistant material, a layer of metal foil is glued to the inner cavity wall of the carbon fiber closed fixture. According to Figure3, the closed fixture needs to make bolt holes at the ends of both wings for connecting the screw rods. If bolt holes are drilled at the ends of the two wings of the carbon fiber closed fixture, the fiber continuity of the carbon fiber will be destroyed and the strength of the fixture will be reduced. Therefore, this article designed a metal sleeve with bolt holes, glued to the ends of the two wings of the carbon fiber closed clamp. The new carbon fiber closed clamp is shown in Figure 4; the sheet metal and the metal sleeve are made of aluminum alloy.Figure 4
Structural chart of the carbon fiber closed fixture: (a) carbon fiber closed fixture front fixture; (b) carbon fiber closed fixture rear fixture.
(a)(b)Considering the higher brittleness of new materials and the safety factor set in XWP-420 closed fixture, the safety factor of carbon fiber closed fixture is set to 3; that is, the maximum load is allowed as 240 kN. To improve the bending resistance and shear resistance of the fixture, the thickness of the fixture and the height of the ends of the two wings are increased. And according to the external dimensions of the 420 kN ceramic insulator steel cap and the size of the umbrella skirt, the external dimensions of the ultrahigh voltage carbon fiber closed clamp are designed. Dimensions of various components of the carbon fiber closed clamp are shown in Figure5.Figure 5
Dimensions of various components of the carbon fiber closed clamp (unit: mm): (a) carbon fiber front fixture overall structure, (b) A part bottom view, (c) B part top view, (d) structural dimension of the inner cavity of the carbon fiber rear fixture, and (e) dimensions of the metal sleeve outline.
(a)(b)(c)(d)(e)


### 2.3. Structural Design of Pavement

T700/T009 type carbon fiber composite material is used to fabricate the clamp. The mechanical parameters of the material are shown in Table1. Fiber directions of the carbon fiber laminate are shown in Figure 6. Direction 1 indicates the fiber direction, direction 2 indicates the direction perpendicular to the fiber direction in the paving layer, and direction 3 indicates the paving layer direction.Table 1
Mechanical parameters of T700/T009 material.
DirectionElastic modulusTensile strengthCompressive strengthDirection 1 (MPa)1400002616965Direction 2 (MPa)900047168Direction 3 (MPa)900047124DirectionShear modulusShear strengthPoisson’s ratio1-2 face (MPa)4700720.322-3 face (MPa)3100510.451-3 face (MPa)4700710.32Density (g/cm3)1.61Single-layer thickness/mm0.2Figure 6
Fiber direction of the carbon fiber laminate.According to the classic laminate theory [22], the relationship between the internal force and strain of the laminate and the internal torque and strain of the laminate is expressed as follows:(1)TxTyTxy=B11B12B16B12B22B26B16B26B66εx0εy0γxy0+D11D12D16D12D22D26D16D26D66kxkykxy,TxTyTxy=B11B12B16B12B22B26B16B26B66εx0εy0γxy0+D11D12D16D12D22D26D16D26D66kxkykxy,where Fx, Fy, and Fxy denote the internal forces per unit width (or length) on the cross section of the laminated plate; Tx, Ty, and Txy denote the internal moments per unit width (or length) on the cross section of the laminated plate; and εxo, εyo, and γxyo are the midplane strain. kx, ky, and kxy are the curvature and twist rate of the middle plane. Aij denotes the tensile stiffness, Bij denotes the coupling stiffness, and Dij denotes the bending stiffness; i and j belong to the collection of positive integer.According to the calculation formula of coupling stiffness,(2)Bij=∑k=1nQ¯ijkZk2−Zk−122=Q¯ij1Z12−Z022+Q¯ij2Z22−Z122+⋯+Q¯ijn/20−Zn/22−12+Q¯ijn/2+1Zn/2+122+⋯+Q¯ijn−1Zn−12−Zn−222+Q¯ijnZn2−Zn−122,where Q¯ij represents the reduction stiffness coefficient and Z represents the distance from one layer of the laminate to the middle of the laminate.For carbon fiber laminates with general layup methods,Q¯ij1≠Q¯ijn and Z12−Z02≠−Zn2−Zn−12. The coupling stiffness is not equal to zero, which produces the coupling of tensile force and shear force, tensile force, and bending moment, that affects the rigidity and strength of the entire laminate. However, for carbon fiber laminates with symmetrical layup, Q¯ij1=Q¯ijn and Z12−Z02=−Zn2−Zn−12. The coupling stiffness is equal to zero, so there is no coupling between tensile force and shear force, tensile force and bending moment, that is conducive to enhancing the rigidity and strength of the laminate. Therefore, a symmetrical layup method is adopted for the design of the carbon fiber closed fixtures.At present, for the selection of the ply angle, 0°, 90°, and ±45° are generally preferred. The special angle process ofπ/4 is easy to operate and is more accurate to be grasped and controlled, which improves the in-plane shear stiffness and strength of carbon fiber laminates [23].According to the thickness of the new closed fixture, three kinds of layup angles are investigated as shown in Table2.Table 2
Five carbon fiber closed fixture layer angles.
NumberLaying angle1[0°]3702[0°/90°/0°/90°/0°]37S3[-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/45°/0°/45°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°]5SNote: taking the second ply angle as an example, number ‘37’ indicates that there are 37 ply groups, and ‘s’ indicates that all plies are symmetrical.


## 2.1. Shape Structure of the Traditional Titanium Alloy Closed Fixture

To design the new structure of the 1000 kV closed fixture based on carbon fiber materials, the XWP-420 closed fixture made of titanium alloy material is selected as a reference, in which the rated load is 80 kN, the safety factor is 2.5 with 200 kN maximum load, and the total weight is 27.48 kg. The outline structure of XWP-420 is shown in Figure2. The difference between the front fixture and the rear fixture is only the structure of the inner cavity, and the rest are the same.Figure 2
Schematic diagram of XWP-420 closed fixture: (a) front fixture; (b) rear fixture.
(a)(b)When replacing the insulator, the front clamp and the rear clamp are, respectively, clamped on the front and rear insulator steel caps. And then the screw rod is tightened to transfer the load on the insulator to the clamp. Finally, the operator removes the insulator and replaces it with a new one, as shown in Figure3(a).Figure 3
Analysis of the stress characteristics of the closed fixture: (a) closed fixture work diagram; (b) closed fixture force diagram.
(a)(b)While tightening the screw rod of the closed fixture, the contact part between the closed fixture and the steel cap is regarded as fixed constraint and the end of the left and right wings is regarded as the loading end [1]. And during the analysis of the mechanical properties, the front fixture and the rear fixture are regarded as a simple beam balanced by three points of force shown in Figure 3(b), considering that the forces and dimensions of the front and rear fixtures are exactly the same.According to the loading characteristics and boundary conditions of the fixture, the structure mainly bears the bending moment and shear force. The overall structure is simplified as a simply supported cantilever beam.


## 2.2. Concept of Exterior Design

According to the working condition of the closed fixture, since the inner cavity wall of the closed fixture directly contacts the insulator steel cap, the inner cavity wall will be rubbed by the steel cap when the screw is tightened. Therefore, considering that carbon fiber is a non-wear-resistant material, a layer of metal foil is glued to the inner cavity wall of the carbon fiber closed fixture. According to Figure3, the closed fixture needs to make bolt holes at the ends of both wings for connecting the screw rods. If bolt holes are drilled at the ends of the two wings of the carbon fiber closed fixture, the fiber continuity of the carbon fiber will be destroyed and the strength of the fixture will be reduced. Therefore, this article designed a metal sleeve with bolt holes, glued to the ends of the two wings of the carbon fiber closed clamp. The new carbon fiber closed clamp is shown in Figure 4; the sheet metal and the metal sleeve are made of aluminum alloy.Figure 4
Structural chart of the carbon fiber closed fixture: (a) carbon fiber closed fixture front fixture; (b) carbon fiber closed fixture rear fixture.
(a)(b)Considering the higher brittleness of new materials and the safety factor set in XWP-420 closed fixture, the safety factor of carbon fiber closed fixture is set to 3; that is, the maximum load is allowed as 240 kN. To improve the bending resistance and shear resistance of the fixture, the thickness of the fixture and the height of the ends of the two wings are increased. And according to the external dimensions of the 420 kN ceramic insulator steel cap and the size of the umbrella skirt, the external dimensions of the ultrahigh voltage carbon fiber closed clamp are designed. Dimensions of various components of the carbon fiber closed clamp are shown in Figure5.Figure 5
Dimensions of various components of the carbon fiber closed clamp (unit: mm): (a) carbon fiber front fixture overall structure, (b) A part bottom view, (c) B part top view, (d) structural dimension of the inner cavity of the carbon fiber rear fixture, and (e) dimensions of the metal sleeve outline.
(a)(b)(c)(d)(e)


## 2.3. Structural Design of Pavement

T700/T009 type carbon fiber composite material is used to fabricate the clamp. The mechanical parameters of the material are shown in Table1. Fiber directions of the carbon fiber laminate are shown in Figure 6. Direction 1 indicates the fiber direction, direction 2 indicates the direction perpendicular to the fiber direction in the paving layer, and direction 3 indicates the paving layer direction.Table 1
Mechanical parameters of T700/T009 material.
DirectionElastic modulusTensile strengthCompressive strengthDirection 1 (MPa)1400002616965Direction 2 (MPa)900047168Direction 3 (MPa)900047124DirectionShear modulusShear strengthPoisson’s ratio1-2 face (MPa)4700720.322-3 face (MPa)3100510.451-3 face (MPa)4700710.32Density (g/cm3)1.61Single-layer thickness/mm0.2Figure 6
Fiber direction of the carbon fiber laminate.According to the classic laminate theory [22], the relationship between the internal force and strain of the laminate and the internal torque and strain of the laminate is expressed as follows:(1)TxTyTxy=B11B12B16B12B22B26B16B26B66εx0εy0γxy0+D11D12D16D12D22D26D16D26D66kxkykxy,TxTyTxy=B11B12B16B12B22B26B16B26B66εx0εy0γxy0+D11D12D16D12D22D26D16D26D66kxkykxy,where Fx, Fy, and Fxy denote the internal forces per unit width (or length) on the cross section of the laminated plate; Tx, Ty, and Txy denote the internal moments per unit width (or length) on the cross section of the laminated plate; and εxo, εyo, and γxyo are the midplane strain. kx, ky, and kxy are the curvature and twist rate of the middle plane. Aij denotes the tensile stiffness, Bij denotes the coupling stiffness, and Dij denotes the bending stiffness; i and j belong to the collection of positive integer.According to the calculation formula of coupling stiffness,(2)Bij=∑k=1nQ¯ijkZk2−Zk−122=Q¯ij1Z12−Z022+Q¯ij2Z22−Z122+⋯+Q¯ijn/20−Zn/22−12+Q¯ijn/2+1Zn/2+122+⋯+Q¯ijn−1Zn−12−Zn−222+Q¯ijnZn2−Zn−122,where Q¯ij represents the reduction stiffness coefficient and Z represents the distance from one layer of the laminate to the middle of the laminate.For carbon fiber laminates with general layup methods,Q¯ij1≠Q¯ijn and Z12−Z02≠−Zn2−Zn−12. The coupling stiffness is not equal to zero, which produces the coupling of tensile force and shear force, tensile force, and bending moment, that affects the rigidity and strength of the entire laminate. However, for carbon fiber laminates with symmetrical layup, Q¯ij1=Q¯ijn and Z12−Z02=−Zn2−Zn−12. The coupling stiffness is equal to zero, so there is no coupling between tensile force and shear force, tensile force and bending moment, that is conducive to enhancing the rigidity and strength of the laminate. Therefore, a symmetrical layup method is adopted for the design of the carbon fiber closed fixtures.At present, for the selection of the ply angle, 0°, 90°, and ±45° are generally preferred. The special angle process ofπ/4 is easy to operate and is more accurate to be grasped and controlled, which improves the in-plane shear stiffness and strength of carbon fiber laminates [23].According to the thickness of the new closed fixture, three kinds of layup angles are investigated as shown in Table2.Table 2
Five carbon fiber closed fixture layer angles.
NumberLaying angle1[0°]3702[0°/90°/0°/90°/0°]37S3[-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/45°/0°/45°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°]5SNote: taking the second ply angle as an example, number ‘37’ indicates that there are 37 ply groups, and ‘s’ indicates that all plies are symmetrical.


## 3. Method for Analyzing Mechanical Properties of the Carbon Fiber Closed Fixture

The progressive damage strength analysis method is used to analyze the mechanical properties of the fixture, which mainly completes the calculation through three parts such as stress analysis, failure analysis, and rigidity reduction.


### 3.1. Progressive Damage Strength Analysis Method

The progressive damage strength analysis method is a calculation method based on the assumption that a certain bearing capacity is retained after material damage [16], where approximate processes are shown as Figure 7.Figure 7
Progressive damage analysis flowchart.Based on the Finite Element Modeling (FEM) models for the component, stress analysis is conducted first, and then the termination calculation is determined. The termination calculation conditions are as follows. (1) Calculate the applied displacement load to reach the set expected displacement load. (2) The entire layer of fibers in a certain layer of carbon fiber laminate is damaged and damaged, resulting in the failure of the entire carbon fiber laminate.If the termination calculation condition is fulfilled, the calculation is exited, the progressive damage strength analysis is completed, and otherwise, the damage analysis is performed. During the failure analysis, the stress of the element obtained by the stress analysis is brought into the appropriate strength criterion to determine whether the element is damaged.If the element is not damaged, the load is applied. And then a new round of calculation is started. If the element is broken, the stiffness is reduced first, then the load is applied, and then a new round of calculation is started. During this cycle, until the termination calculation condition is satisfied, the progressive damage strength analysis is completed.


### 3.2. Strength Criterion of the Carbon Fiber Composite

In failure analysis, strength criterion is required. For the judgment of the destruction of the components made by carbon fiber materials, Tsai–Wu strength theory is involved considering that a comprehensive description of material failure is specified compared to other strength theories and is closer to the experimental value [19].The expression of Tsai–Wu strength theory is as follows [20]:(3)W=F1σ1+F2σ2+F3σ3+F11σ12+F22σ22+F33σ32+2F12σ1σ2+2F23σ2σ3+2F31σ3σ1+F44σ42+F55σ52+F66σ62where σi and σj denote stress components, and σ4 = τ23, σ5 = τ31, σ6 = τ12, tij denotes shear stress, and Fi and Fij indicate intensity coefficient tensors, calculated by equation (4), and i and j belong to the collection of positive integer.(4)F1=1At−1Ac,F11=1AtAc,F2=1Bt−1Bc,F22=1BtBc,F3=1Ct−1Cc,F22=1CtCc,F44=1S232,F55=1S132,F66=1S122,F12=−12F11F22,F23=−12F22F33,F13=−12F11F33,where At and Ac denote the tensile strength and the compressive strength of the carbon fiber composite material in the 1 direction, Bt and Bc denote the tensile strength and the compressive strength in the 2 direction, and Ct and Cc denote the tensile strength and the compressive strength in the 3 direction. S23, S13, and S12 denote the shear strength on the in-plane and out-of-plane, respectively.In Tsai–Wu tensor theory, the failure judgment is to substitute the calculated element stress into formula (3). If W≥1, the element is judged to be damaged; otherwise, the destruction does not occur.


### 3.3. Stiffness Reduction

If the destruction occurs, the stiffness of the element needs to be reduced. Changing material properties of the damaged element is an efficient way to reduce the stiffness. Therefore, the material performance degradation method is adopted as shown in Table3. Eii represents the elastic modulus, Gij and υij represent the shear modulus and Poisson's ratio, and Eii′, Gij′, and υij′ represent the modulus of elasticity, front modulus, and Poisson's ratio of the carbon fiber composite material after failure, respectively. Here, i and j belong to the collection of positive integer.Table 3
Composite material stiffness reduction.
Failure modesMaterial stiffness reduction method1-directional tensile or compressive failureE11=E22=E33=0G12=G13=G23=0υ12=υ13=υ23=02-directional tensile or compressive failureE22′=0.01E22,G12′=0.2G12G13′=0.2G13,υ12′=0.01υ12υ23′=0.01υ233-directional tensile or compressive failureE33′=0.01E33,G12′=0.2G12G13′=0.2G13,υ13′=0.01υ13υ23′=0.01υ231-2 in-plane shear failureE22′=0.01E22,G12′=0.01G12υ12′=0.01υ12,υ23′=0.01υ231-3 in-plane shear failureE33′=0.01E33,G13′=0.01G13υ13′=0.01υ13,υ23′=0.01υ232-3 in-plane shear failureE22′=0.01E22,E33′=0.01E33G12′=0.01G12,G13′=0.01G13G23′=0.01G23,υ12′=0.01υ12υ13′=0.01υ13,υ23′=0.01υ23During calculation, because the material property of the element is not set to 0, the elastic modulus and shear modulus of the element degenerate to 0.0001 and Poisson ratio degenerates to 0.01 when tensile or compressive failure occurs in the direction of 1.


### 3.4. Finite Element Modeling of the Carbon Fiber Closed Fixture

The mechanical properties of carbon fiber closed fixture were analyzed by using the finite element progressive damage strength analysis method. Based on ABAQUS finite element software and USDFLD user subroutine, the strength criterion and stiffness reduction method were compiled, and the mechanical properties of three kinds of carbon fiber closed fixtures with different ply angles were analyzed.Because the front clamps and the rear clamps have the same force and dimensions, only the analysis of the front or rear is conducted. The analysis of the mechanical properties of the front carbon fiber clamps is to be carried out.According to the progressive damage strength analysis method, the stiffness of T700/T009 carbon fiber composite can be reduced according to the material performance degradation method. Figure8 shows the stiffness changes (part) of mechanical parameters of T700/T009 carbon fiber composite under various failure modes written by ABAQUS program input window. In Figure 8, there are nine mechanical parameters and six field variables. In the first nine lines, mechanical parameters of T700/T009 carbon fiber composite are shown, and in the last six lines field variable parameters are listed. The first line expresses that the material has not been damaged, and the field variables are all zero. The second line indicates that the material is damaged in direction 1. The material mechanical parameters are the parameters after stiffness reduction, and the first field variable is 1. By analogy, the corresponding field variable will change from 0 to 1 when there is tension compression failure or shear failure in a certain direction. Carbon fiber materials have three directions and three shear planes. There are 64 kinds of failure combinations, so there are 64 kinds of field variables.Figure 8
Stiffness and field variation of mechanical parameters of T700/T009 carbon fiber composites.In the process of progressive damage strength analysis, every element of the finite element model needs to be re-assigned with material properties, which are to select the material mechanical parameters according to the combination form of six field variable parameters. The six field variables of the failure mode of the marking unit are controlled in real time by the USDFLD user subroutine.The user subroutine USDFLD of ABAQUS is written in Fortran language. In the progressive damage strength analysis, the USDFLD user subroutine of ABAQUS is to calculate the 12 coefficients of Tsai–Wu strength criterion according to the failure strength parameters of T700/T009 carbon fiber composite, then to substitute the calculated element stress and 12 coefficient values into Tsai–Wu strength criterion formula to judge the material failure, and finally to update the element according to whether the failure occurs or not and the failure mode field variables of material properties and state variables of USDFLD user subroutine.According to the stress characteristics, the inner cavity of the finite element model of carbon fiber closed fixture is set as fixed; that is, the degree of freedom in six directions is set as zero. The ends of the two wings of the finite element model are coupled to RP-1 and RP-2, respectively, and a displacement load in the thickness direction is applied to these two points to simulate the loading of the screw rod.The loading and the constraints of finite element model of the carbon fiber closed fixture are shown in Figure9. Finally, according to the progressive damage strength analysis method, the finite element calculation of carbon fiber closed fixture is carried out.Figure 9
Coupling diagram of the carbon fiber closed fixture with finite element model constraints.


## 3.1. Progressive Damage Strength Analysis Method

The progressive damage strength analysis method is a calculation method based on the assumption that a certain bearing capacity is retained after material damage [16], where approximate processes are shown as Figure 7.Figure 7
Progressive damage analysis flowchart.Based on the Finite Element Modeling (FEM) models for the component, stress analysis is conducted first, and then the termination calculation is determined. The termination calculation conditions are as follows. (1) Calculate the applied displacement load to reach the set expected displacement load. (2) The entire layer of fibers in a certain layer of carbon fiber laminate is damaged and damaged, resulting in the failure of the entire carbon fiber laminate.If the termination calculation condition is fulfilled, the calculation is exited, the progressive damage strength analysis is completed, and otherwise, the damage analysis is performed. During the failure analysis, the stress of the element obtained by the stress analysis is brought into the appropriate strength criterion to determine whether the element is damaged.If the element is not damaged, the load is applied. And then a new round of calculation is started. If the element is broken, the stiffness is reduced first, then the load is applied, and then a new round of calculation is started. During this cycle, until the termination calculation condition is satisfied, the progressive damage strength analysis is completed.


## 3.2. Strength Criterion of the Carbon Fiber Composite

In failure analysis, strength criterion is required. For the judgment of the destruction of the components made by carbon fiber materials, Tsai–Wu strength theory is involved considering that a comprehensive description of material failure is specified compared to other strength theories and is closer to the experimental value [19].The expression of Tsai–Wu strength theory is as follows [20]:(3)W=F1σ1+F2σ2+F3σ3+F11σ12+F22σ22+F33σ32+2F12σ1σ2+2F23σ2σ3+2F31σ3σ1+F44σ42+F55σ52+F66σ62where σi and σj denote stress components, and σ4 = τ23, σ5 = τ31, σ6 = τ12, tij denotes shear stress, and Fi and Fij indicate intensity coefficient tensors, calculated by equation (4), and i and j belong to the collection of positive integer.(4)F1=1At−1Ac,F11=1AtAc,F2=1Bt−1Bc,F22=1BtBc,F3=1Ct−1Cc,F22=1CtCc,F44=1S232,F55=1S132,F66=1S122,F12=−12F11F22,F23=−12F22F33,F13=−12F11F33,where At and Ac denote the tensile strength and the compressive strength of the carbon fiber composite material in the 1 direction, Bt and Bc denote the tensile strength and the compressive strength in the 2 direction, and Ct and Cc denote the tensile strength and the compressive strength in the 3 direction. S23, S13, and S12 denote the shear strength on the in-plane and out-of-plane, respectively.In Tsai–Wu tensor theory, the failure judgment is to substitute the calculated element stress into formula (3). If W≥1, the element is judged to be damaged; otherwise, the destruction does not occur.


## 3.3. Stiffness Reduction

If the destruction occurs, the stiffness of the element needs to be reduced. Changing material properties of the damaged element is an efficient way to reduce the stiffness. Therefore, the material performance degradation method is adopted as shown in Table3. Eii represents the elastic modulus, Gij and υij represent the shear modulus and Poisson's ratio, and Eii′, Gij′, and υij′ represent the modulus of elasticity, front modulus, and Poisson's ratio of the carbon fiber composite material after failure, respectively. Here, i and j belong to the collection of positive integer.Table 3
Composite material stiffness reduction.
Failure modesMaterial stiffness reduction method1-directional tensile or compressive failureE11=E22=E33=0G12=G13=G23=0υ12=υ13=υ23=02-directional tensile or compressive failureE22′=0.01E22,G12′=0.2G12G13′=0.2G13,υ12′=0.01υ12υ23′=0.01υ233-directional tensile or compressive failureE33′=0.01E33,G12′=0.2G12G13′=0.2G13,υ13′=0.01υ13υ23′=0.01υ231-2 in-plane shear failureE22′=0.01E22,G12′=0.01G12υ12′=0.01υ12,υ23′=0.01υ231-3 in-plane shear failureE33′=0.01E33,G13′=0.01G13υ13′=0.01υ13,υ23′=0.01υ232-3 in-plane shear failureE22′=0.01E22,E33′=0.01E33G12′=0.01G12,G13′=0.01G13G23′=0.01G23,υ12′=0.01υ12υ13′=0.01υ13,υ23′=0.01υ23During calculation, because the material property of the element is not set to 0, the elastic modulus and shear modulus of the element degenerate to 0.0001 and Poisson ratio degenerates to 0.01 when tensile or compressive failure occurs in the direction of 1.


## 3.4. Finite Element Modeling of the Carbon Fiber Closed Fixture

The mechanical properties of carbon fiber closed fixture were analyzed by using the finite element progressive damage strength analysis method. Based on ABAQUS finite element software and USDFLD user subroutine, the strength criterion and stiffness reduction method were compiled, and the mechanical properties of three kinds of carbon fiber closed fixtures with different ply angles were analyzed.Because the front clamps and the rear clamps have the same force and dimensions, only the analysis of the front or rear is conducted. The analysis of the mechanical properties of the front carbon fiber clamps is to be carried out.According to the progressive damage strength analysis method, the stiffness of T700/T009 carbon fiber composite can be reduced according to the material performance degradation method. Figure8 shows the stiffness changes (part) of mechanical parameters of T700/T009 carbon fiber composite under various failure modes written by ABAQUS program input window. In Figure 8, there are nine mechanical parameters and six field variables. In the first nine lines, mechanical parameters of T700/T009 carbon fiber composite are shown, and in the last six lines field variable parameters are listed. The first line expresses that the material has not been damaged, and the field variables are all zero. The second line indicates that the material is damaged in direction 1. The material mechanical parameters are the parameters after stiffness reduction, and the first field variable is 1. By analogy, the corresponding field variable will change from 0 to 1 when there is tension compression failure or shear failure in a certain direction. Carbon fiber materials have three directions and three shear planes. There are 64 kinds of failure combinations, so there are 64 kinds of field variables.Figure 8
Stiffness and field variation of mechanical parameters of T700/T009 carbon fiber composites.In the process of progressive damage strength analysis, every element of the finite element model needs to be re-assigned with material properties, which are to select the material mechanical parameters according to the combination form of six field variable parameters. The six field variables of the failure mode of the marking unit are controlled in real time by the USDFLD user subroutine.The user subroutine USDFLD of ABAQUS is written in Fortran language. In the progressive damage strength analysis, the USDFLD user subroutine of ABAQUS is to calculate the 12 coefficients of Tsai–Wu strength criterion according to the failure strength parameters of T700/T009 carbon fiber composite, then to substitute the calculated element stress and 12 coefficient values into Tsai–Wu strength criterion formula to judge the material failure, and finally to update the element according to whether the failure occurs or not and the failure mode field variables of material properties and state variables of USDFLD user subroutine.According to the stress characteristics, the inner cavity of the finite element model of carbon fiber closed fixture is set as fixed; that is, the degree of freedom in six directions is set as zero. The ends of the two wings of the finite element model are coupled to RP-1 and RP-2, respectively, and a displacement load in the thickness direction is applied to these two points to simulate the loading of the screw rod.The loading and the constraints of finite element model of the carbon fiber closed fixture are shown in Figure9. Finally, according to the progressive damage strength analysis method, the finite element calculation of carbon fiber closed fixture is carried out.Figure 9
Coupling diagram of the carbon fiber closed fixture with finite element model constraints.


## 4. Analysis of Simulation Results of the Carbon Fiber Closed Fixture

Using the progressive damage strength analysis method, the failure stress cloud diagrams of the carbon fiber closed clamps with three traditional type lay angles are obtained as shown, respectively, in Figure10. The failure positions of the three types are at the ends of the two wings, and shear failures occur.Figure 10
Failure stress cloud diagram of three carbon fiber closed clamps with different lay angles: (a) the first layer angle, (b) the second layer angle, and (c) the third layer angle.
(a)(b)(c)The displacement-load curves of three type fixtures are shown in Figure11. After undergoing elastic deformation, the three types of carbon fiber closed clamps start to enter plastic deformation from the inflection points such as A1, A2, and A3, and the carbon fiber closed clamps have been destroyed. While at the inflection points such as B1, B2, and B3, the three types of carbon fiber closed fixtures, respectively, reach the maximum bearing load, and then the fixtures are completely destroyed, and the curve decreases linearly. The values of Ai and Bi in the curve are shown in Table 4, where the stiffness in the elastic stage is calculated by equation (5). Here, i belongs to the collection of positive integer.(5)k=Pδ,where k denotes stiffness, P denotes the constant force acting on the structure, and δ denotes the displacement caused by the force.Figure 11
Displacement-load curve of carbon fiber closed fixtures with 3 different ply angles.Table 4
Carbon fiber closed fixture data sheet with 3 different ply angles.
Layer angleAi (kN)Bi (kN)Elastic stage stiffness (kN/mm)1st layer182.52203.2174.792nd layer164.75188.7457.783rd layer175.71191.0749.48Stiffness calculation formula is as follows:In Table4, the rigidity of the 0° ply (the first layer angle) is the largest, and the maximum bearing load (Bi) is also the largest, indicating that the 0° ply is more able to bear bending moment and shear than other ply angle carbon fiber closed fixtures. However, the maximum bearing load is only 203.21 kN, which is less than the maximum bearing load requirement, namely, 240 kN, resulting in that the strength requirements is not met. Therefore, the new layer structure with befitting ply angle arises. In the next section, a carbon fiber layup structure with an outer cladding layer is provided.


## 5. Improvement of the Layer Structure of the Carbon Fiber Closed Fixture

In Section4, the shear capacity of the ends of the two wings of the carbon fiber closed fixture is proved to be insufficient for the design. Two types of cladding structure of outer cladding angle are analyzed to select a strengthened structure.


### 5.1. Outer Cladding Layer Structure

To improve the failure strength of the carbon fiber closed fixture, the way is to strengthen the shear resistance of the ends of both wings. Carbon fiber outer cladding structure is shown in Figure12, where θi indicates the lay angle. The function of this type structure is similar to that of I-beam [8]. The upper and lower horizontal layers are similar to the webs of I-beams, which is to increase the bending strength and shear strength of the whole structure. Here, i belongs to the collection of positive integer.Figure 12
Carbon fiber outer cladding structure.


### 5.2. Analysis of Simulation Results

The thickness of the outer layer is 14 mm, known from the total thickness of the carbon fiber closed clamp which is 74 mm, and the thickness of the inner layer is 46 mm. As mentioned above, the carbon fiber closed fixture with 0° ply has a better bending resistance; therefore, the inner ply angle is set as 0° ply, and the outer ply angle is shown in Table5.Table 5
Two outer cladding layer angles.
NumberOuter layer angle1[0°/90°/0°/90°/0°]23S2[-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/45°/0°/45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°]SAfter conducting the finite element calculations on two carbon fiber closed fixtures with different outer cladding angles, the broken-ring stress cloud image is obtained as shown in Figure13.Figure 13
Failure stress cloud diagram of two carbon fiber closed clamps with different outer cladding angles: (a) the first angle of outer cladding; (b) the second angle of outer cladding.
(a)(b)The failure position of the first type of carbon fiber closed clamp with the outer cladding angle is the same as that without the outer cladding structure, and both of them appear at the ends of the two wings and are shear failures. The second type of carbon fiber closed clamp with outer cladding angle breaks around the inner cavity, with compression failure on the front and tensile failure on the back. The overall structure is a bending failure.Figure14 shows the displacement-load curves of two kinds of carbon fiber closed clamps with different cladding angles. The first type of carbon fiber closed clamp with outer cladding angle enters plastic deformation from the inflection point A1. When the B1 inflection point is reached, the fixture has the maximum load. After that, the clamp is completely destroyed and the curve drops straight. And the inflection point of the second type of carbon fiber closed clamp with outer cladding angle entering plastic deformation is A2. At the B2 inflection point, there is the maximum load. After that, the clamp is not completely destroyed, and the curve does not drop straight. The values of Ai and Bi and the stiffness of the elastic stage are shown in Table 6. Here, i belongs to the collection of positive integer.Figure 14
Displacement-load curves of closed carbon fiber fixtures with two outer layer angles.Table 6
Data sheet of carbon fiber closed fixtures with two outer laying angles.
Layer angleAi (kN)Bi (kN)Elastic stage stiffness (kN/mm)1st layer214.7422361.52nd layer397.1472.665.53From the third column of Table6, the strength of carbon fiber closed fixture with cladding structure is higher than the one without cladding structure. The rigidity and the maximum load (Bi) of the first kind of closed fixture are lower than those of the second kind; thus, the second kind of angle has better shear resistance. That is to say, the ±45° layer has a better shear resistance than the 0° and 90° layer. According to the failure stress cloud diagram of the fixture shown in Figure 13(b), the second overlay angle enhances the shear strength of the ends of the two wings, which makes the failure position transfer to the surrounding of the fixed area and the failure mode turns to bending failure.The maximum bearing load of the second kind of carbon fiber closed clamp with the angle of outer cladding is 472.6 kN, which is higher than the maximum bearing load required by the carbon fiber closed clamp. Therefore, the second type of cladding structure of the outer cladding angle is used to manufacture the new clamp.


## 5.1. Outer Cladding Layer Structure

To improve the failure strength of the carbon fiber closed fixture, the way is to strengthen the shear resistance of the ends of both wings. Carbon fiber outer cladding structure is shown in Figure12, where θi indicates the lay angle. The function of this type structure is similar to that of I-beam [8]. The upper and lower horizontal layers are similar to the webs of I-beams, which is to increase the bending strength and shear strength of the whole structure. Here, i belongs to the collection of positive integer.Figure 12
Carbon fiber outer cladding structure.


## 5.2. Analysis of Simulation Results

The thickness of the outer layer is 14 mm, known from the total thickness of the carbon fiber closed clamp which is 74 mm, and the thickness of the inner layer is 46 mm. As mentioned above, the carbon fiber closed fixture with 0° ply has a better bending resistance; therefore, the inner ply angle is set as 0° ply, and the outer ply angle is shown in Table5.Table 5
Two outer cladding layer angles.
NumberOuter layer angle1[0°/90°/0°/90°/0°]23S2[-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/-45°/0°/45°/90°/45°/0°/45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°/90°/45°/0°/-45°]SAfter conducting the finite element calculations on two carbon fiber closed fixtures with different outer cladding angles, the broken-ring stress cloud image is obtained as shown in Figure13.Figure 13
Failure stress cloud diagram of two carbon fiber closed clamps with different outer cladding angles: (a) the first angle of outer cladding; (b) the second angle of outer cladding.
(a)(b)The failure position of the first type of carbon fiber closed clamp with the outer cladding angle is the same as that without the outer cladding structure, and both of them appear at the ends of the two wings and are shear failures. The second type of carbon fiber closed clamp with outer cladding angle breaks around the inner cavity, with compression failure on the front and tensile failure on the back. The overall structure is a bending failure.Figure14 shows the displacement-load curves of two kinds of carbon fiber closed clamps with different cladding angles. The first type of carbon fiber closed clamp with outer cladding angle enters plastic deformation from the inflection point A1. When the B1 inflection point is reached, the fixture has the maximum load. After that, the clamp is completely destroyed and the curve drops straight. And the inflection point of the second type of carbon fiber closed clamp with outer cladding angle entering plastic deformation is A2. At the B2 inflection point, there is the maximum load. After that, the clamp is not completely destroyed, and the curve does not drop straight. The values of Ai and Bi and the stiffness of the elastic stage are shown in Table 6. Here, i belongs to the collection of positive integer.Figure 14
Displacement-load curves of closed carbon fiber fixtures with two outer layer angles.Table 6
Data sheet of carbon fiber closed fixtures with two outer laying angles.
Layer angleAi (kN)Bi (kN)Elastic stage stiffness (kN/mm)1st layer214.7422361.52nd layer397.1472.665.53From the third column of Table6, the strength of carbon fiber closed fixture with cladding structure is higher than the one without cladding structure. The rigidity and the maximum load (Bi) of the first kind of closed fixture are lower than those of the second kind; thus, the second kind of angle has better shear resistance. That is to say, the ±45° layer has a better shear resistance than the 0° and 90° layer. According to the failure stress cloud diagram of the fixture shown in Figure 13(b), the second overlay angle enhances the shear strength of the ends of the two wings, which makes the failure position transfer to the surrounding of the fixed area and the failure mode turns to bending failure.The maximum bearing load of the second kind of carbon fiber closed clamp with the angle of outer cladding is 472.6 kN, which is higher than the maximum bearing load required by the carbon fiber closed clamp. Therefore, the second type of cladding structure of the outer cladding angle is used to manufacture the new clamp.


## 6. Experimental Results and Analysis

### 6.1. Fabrication and Test of Carbon Fiber Closed Fixtures

The carbon fiber closed clamp manufactured is shown in Figure15, and total weight is 17.46 kg, which is 36.46% lighter than the XWP-420 titanium alloy closed fixture.Figure 15
Carbon fiber closed fixture.Mechanical test is conducted on YWL-100 hydraulic horizontal tensile testing machine which contains hydraulic tensile machine and control platform, shown in Figure16. The hydraulic tensile machine includes the front and rear chuck seats: the front chuck seat is controlled by the control platform and the rear chuck seat is manually pushed to adjust the test space in stages. The overall frame adopts steel plate welded frame structure, and the control platform adjusts the load applied by the front chuck seat and displays the test force and test curve, and automatically processes the test data according to the requirements of the test method. Due to fast response and high sensitivity, the load, displacement, and deformation of the test piece are collected in real time.Figure 16
YWL-100 hydraulic horizontal tensile testing machine: (a) hydraulic tensile machine; (b) control platform.
(a)(b)According to China power industry standard “DL/T 875–2016,” the carbon fiber closed clamp and two insulators are assembled and installed on the front chuck seat and the rear chuck seat of the hydraulic tension machine, as shown in Figure17. Then, a tensile force as 80 kN is applied to the carbon fiber closed fixture through the control platform and kept for 5 minutes. The loading rate of the entire test is 0.221 kN/s.Figure 17
Test assembly of the closed carbon fiber fixture.If no permanent deformation or damage, flexible and reliable operation, and no jamming occurs, the carbon fiber closed fixture is considered qualified.


### 6.2. Result Analysis

After the test, the displacement-load curve in the elastic deformation range is obtained, and the curve is compared with the displacement-load curve of the finite element calculation in the elastic deformation range with the thickness of 14-millimeter cladding layer, as shown in Figure18. The test rigidity of carbon fiber closed fixture in elastic deformation is 60.71 kn/mm, which is 4.82 kn/mm less than the rigidity calculated by finite element method, and the error between them is within 10%, which meets the engineering accuracy requirements.Figure 18
Comparison of the displacement and load curve between elastic deformation test and finite element calculation.The result shows that the carbon fiber closed clamps in the elastic deformation range are consistent with the results of the finite element calculation. And the validity of the finite element mechanical performance analysis method and the feasibility of the structural design of the carbon fiber closed clamp in the elastic deformation range are verified.The clamp after the test is shown in Figure19. The carbon fiber closed clamp has no signs of deformation and damage, and the bolt connection is rotated flexibly, and the connection between the metal part and carbon fiber has no falling off phenomenon; the metal part has no signs of damage, so that the new one meets the shear strength requirements of “DL/T 875–2016.”Figure 19
Carbon fiber closed clamp after test: (a) carbon fiber front fixture, (b) carbon fiber rear fixture, (c) overall top view of the carbon fiber fixture, and (d) overall side view of the carbon fiber fixture.
(a)(b)(c)(d)


## 6.1. Fabrication and Test of Carbon Fiber Closed Fixtures

The carbon fiber closed clamp manufactured is shown in Figure15, and total weight is 17.46 kg, which is 36.46% lighter than the XWP-420 titanium alloy closed fixture.Figure 15
Carbon fiber closed fixture.Mechanical test is conducted on YWL-100 hydraulic horizontal tensile testing machine which contains hydraulic tensile machine and control platform, shown in Figure16. The hydraulic tensile machine includes the front and rear chuck seats: the front chuck seat is controlled by the control platform and the rear chuck seat is manually pushed to adjust the test space in stages. The overall frame adopts steel plate welded frame structure, and the control platform adjusts the load applied by the front chuck seat and displays the test force and test curve, and automatically processes the test data according to the requirements of the test method. Due to fast response and high sensitivity, the load, displacement, and deformation of the test piece are collected in real time.Figure 16
YWL-100 hydraulic horizontal tensile testing machine: (a) hydraulic tensile machine; (b) control platform.
(a)(b)According to China power industry standard “DL/T 875–2016,” the carbon fiber closed clamp and two insulators are assembled and installed on the front chuck seat and the rear chuck seat of the hydraulic tension machine, as shown in Figure17. Then, a tensile force as 80 kN is applied to the carbon fiber closed fixture through the control platform and kept for 5 minutes. The loading rate of the entire test is 0.221 kN/s.Figure 17
Test assembly of the closed carbon fiber fixture.If no permanent deformation or damage, flexible and reliable operation, and no jamming occurs, the carbon fiber closed fixture is considered qualified.


## 6.2. Result Analysis

After the test, the displacement-load curve in the elastic deformation range is obtained, and the curve is compared with the displacement-load curve of the finite element calculation in the elastic deformation range with the thickness of 14-millimeter cladding layer, as shown in Figure18. The test rigidity of carbon fiber closed fixture in elastic deformation is 60.71 kn/mm, which is 4.82 kn/mm less than the rigidity calculated by finite element method, and the error between them is within 10%, which meets the engineering accuracy requirements.Figure 18
Comparison of the displacement and load curve between elastic deformation test and finite element calculation.The result shows that the carbon fiber closed clamps in the elastic deformation range are consistent with the results of the finite element calculation. And the validity of the finite element mechanical performance analysis method and the feasibility of the structural design of the carbon fiber closed clamp in the elastic deformation range are verified.The clamp after the test is shown in Figure19. The carbon fiber closed clamp has no signs of deformation and damage, and the bolt connection is rotated flexibly, and the connection between the metal part and carbon fiber has no falling off phenomenon; the metal part has no signs of damage, so that the new one meets the shear strength requirements of “DL/T 875–2016.”Figure 19
Carbon fiber closed clamp after test: (a) carbon fiber front fixture, (b) carbon fiber rear fixture, (c) overall top view of the carbon fiber fixture, and (d) overall side view of the carbon fiber fixture.
(a)(b)(c)(d)


## 7. Conclusion

In this paper, the application of carbon fiber material is proposed for the manufacture of the closed clamp used in ultrahigh voltage transmission lines. The new carbon fiber outer cladding structure is used to solve the problem of insufficient shear resistance of the ends of the two wings of the carbon fiber closed clamp. The manufactured equipment has passed the mechanical property test and achieved the purpose of lightweight; the weight of clamp is 36.46% lower than that of traditional titanium alloy clamp. On this basis, the destructive test and field operation test of this equipment need to be further studied.



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*Source: 6105360-2021-02-02.xml*