Method and apparatus for stripping optical fibers embedded in carbon fiber composite mandrels

Abstract

The application provides a stripping method and stripping equipment for an optical fiber inlaid in a carbon fiber composite mandrel, and belongs to the technical field of wire stripping. The equipment comprises a heating device, a peeling device and a pressing device; the heating device is used for surface heating treatment, the peeling device is used for stripping an outer protective layer, and the pressing device is used for applying radial pressure to a stripping treatment area. The stripping method and stripping equipment for the optical fiber inlaid in the carbon fiber composite mandrel can adopt different removal methods according to the properties of different layers of the carbon fiber composite mandrel, avoid the problem that the cutting depth is difficult to control when a single cutting method is adopted, and will not cause the problems of damaging the optical fiber or insufficient stripping. The optical fiber can be fully and completely separated out, the stripping success rate is high, effective connection with an external monitoring device can be realized, and the reliability of monitoring is ensured.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of wire stripping, and particularly relates to a method and equipment for stripping an optical fiber inlaid in a carbon fiber composite core rod. BACKGROUND

[0002] With the development of society, the overall power consumption increases sharply, and new transmission lines need to build new transmission corridors. In addition, the transmission capacity of some early transmission lines cannot meet the increasing demand for electricity, and needs to be upgraded. However, due to the influence of path, land, compensation and other factors, it is more and more difficult to establish a new line transmission corridor, and it is difficult to handle, takes a long time to build and has high cost. Therefore, it is an inevitable choice to use new technology, materials and process to realize capacity expansion and reconstruction by replacing the conductor on the basis of the original power facility.

[0003] The transmission conductor mainly consists of two parts. One part is the aluminum conductor outside the conductor, which mainly plays the role of transmitting load; the other part is the core inside the conductor, which mainly plays the role of mechanical support. The transmission capacity of the transmission conductor is determined by many factors such as the area of the aluminum conductor itself, the electrical conductivity (IACS), the heat resistance of the line (sag), the line loss (including resistance, reactance), etc. Among them, the carbon fiber composite core conductor has the characteristics of light weight, high mechanical strength, small sag, large carrying capacity, small thermal expansion coefficient, energy saving and consumption reduction, etc. It has incomparable advantages in increasing the transmission capacity of the line, reducing the sag, reducing the line loss and improving the wind resistance of the line, and is called "superconducting conductor" in the industry. The use of carbon fiber conductors for capacity expansion and reconstruction can make full use of the original line tower resources and greatly improve the transmission capacity of the transmission line, which is one of the effective means to deal with the situation of rapid load growth and tight transmission corridor resources.

[0004] However, the core of the carbon fiber composite core conductor is made of carbon fiber impregnated resin, which has low elongation and limited bending radius, and cannot be bent at sharp angles. It is easy to be damaged during construction, causing damage such as strand separation, lantern raising and core extraction of the carbon fiber composite core conductor, and even causing core rod breakage. Core breakage is a hidden defect that cannot be detected in time, and the carbon fiber composite core conductor operates with defects, eventually causing transmission line breakage accidents, which poses a major threat to the safe operation of the power grid and the safety of life and property. Therefore, the non-destructive testing technology for hidden defects of carbon fiber composite core conductors, especially the online non-destructive defect detection technology for carbon fiber composite cores during construction, has always been one of the research hotspots in this field.

[0005] The existing nondestructive testing methods for carbon fiber composite materials mainly include infrared, eddy current, ultrasonic, acoustic emission, X-ray, etc. For conventional steel core aluminum stranded conductor, eddy current detection principle and magnetic flux leakage detection principle can be used simultaneously to detect the damage of aluminum stranded conductor and steel core, respectively, but carbon fiber composite material is not magnetically conductive, so magnetic flux leakage detection and metal magnetic memory detection methods cannot be used. Using X-ray real-time imaging technology, the direction of the ray is perpendicular to the tangent direction of the mandrel. When the conductor rotates, most of the interface defects can be detected, and the product can be detected in real time and online at any position and any rotation angle. The detected image has high clarity and sensitivity, but the detection sensitivity of X-ray detection method for surface or internal cracks of carbon fiber conductor is low, the photographed image is blurred, the contrast of the defect part in the formed image is seriously insufficient, and because the transmission line is very long, the online detection of the conductor requires identification of a large number of pictures, which is prone to missed detection due to personnel fatigue, and the feasibility of field application is not high. Laser ultrasonic is a method of using high-energy laser pulses to produce thermal characteristics on the surface of solids, forming thermal stress, and generating ultrasonic waves in the object, but the length of the transmission conductor is several hundred to thousands of meters, the defect signal is attenuated, and the surface of the transmission conductor is not smooth, so the ultrasonic detection method is only suitable for short-distance damage detection of carbon fiber composite mandrel. According to the structure of the carbon fiber composite conductor, the glass fiber of the mandrel separates the carbon fiber bundle and the aluminum stranded conductor, so the carbon fiber can be heated by electricity alone, and then detected by an infrared thermal imager. The object's radiation detects the defects on the surface of the object or material. Due to impact or in the manufacturing process, hollows, cracks, uneven thickness and other defects may be formed, which makes heat transfer uneven, resulting in different temperatures at different places. After processing, it is displayed on the oscilloscope or computer display screen. The temperature at the defect is higher, but the infrared technology can only sample the carbon fiber mandrel for detection, so it cannot realize practical nondestructive testing of carbon fiber composite conductor.

[0006] It can be seen that the commonly used nondestructive testing methods have obvious detection limitations, resulting in low practicability. In order to solve the problem of practicability, the carbon fiber composite wire with built-in optical fiber emerges as the times require. The wire can inject a detection light pulse into the sensing optical fiber by using the principle of optical time domain reflectometer (OTDR), and the backscattered light is generated when the pulse light propagates in the optical fiber. The external monitoring equipment of the optical fiber is connected, and the size of the backscattered light attenuation loss value can be used to judge whether the hidden defects of the mandrel occur. The time of the backscattered light can be used to determine the position of the light scattering (i.e. the position of the abnormal strain point), so as to achieve the purpose of finding and positioning defects. The nondestructive testing method based on the wire structure is not limited by the length of the wire, and the detection accuracy is also high, which effectively breaks through the use limitation of the traditional detection method. In order to effectively connect the optical fiber with the external monitoring equipment, the optical fiber needs to be stripped out from the mandrel. The existing stripping method is generally to gradually thin the layers around the optical fiber by cutting until the optical fiber is exposed. The success rate of this optical fiber stripping method is not high, and it is difficult to control the cutting depth, which may cause the optical fiber to be damaged by cutting or the cutting to be not in place, and the optical fiber is adhered to the surrounding composite fiber and resin, which is not fully exposed. These phenomena will ultimately affect the information analysis of the optical fiber and the accuracy of the monitoring result. SUMMARY

[0007] The embodiment of the present application provides a method and equipment for stripping an optical fiber built in a carbon fiber composite mandrel, aiming to solve the problem of the existing technology that the stripping method of the optical fiber is difficult to control the cutting depth.

[0008] To achieve the above-mentioned purpose, the technical scheme adopted by the present application is:

[0009] In a first aspect, a method for stripping an optical fiber built in a carbon fiber composite mandrel is provided, which is used for stripping the optical fiber in the carbon fiber composite mandrel. The carbon fiber composite mandrel comprises an optical fiber, an inner protective layer, a carbon fiber layer and an outer protective layer arranged in sequence from inside to outside. The method for stripping the optical fiber built in the carbon fiber composite mandrel comprises the following steps:

[0010] S100, defining a stripping treatment area on the carbon fiber composite mandrel to be processed;

[0011] S200, performing surface heating treatment on the stripping treatment area;

[0012] S300, stripping the outer protective layer subjected to the surface heating treatment;

[0013] S400, applying a radial pressure to the stripping treatment area until the carbon fiber layer is fragmented;

[0014] S500, stripping the fragmented carbon fiber layer;

[0015] S600, tearing and peeling the inner protective layer.

[0016] With reference to the first aspect, in a possible implementation manner, the heating temperature of the surface heating treatment in the step S200 is 320-400 ℃, and the heating duration is 40-90 s.

[0017] With reference to the first aspect, in a possible implementation manner, the step S300 specifically includes:

[0018] The outer protective layer located at the first side surface and the second side surface of the carbon fiber layer is removed by cutting, the first side surface and the second side surface are parallel to each other, or the first side surface and the second side surface are arranged at an included angle.

[0019] With reference to the first aspect, in a possible implementation manner, the step S100 specifically includes:

[0020] S110, defining a reserved area of the peeling end surface of the carbon fiber composite mandrel to be processed to a reserved position, the distance from the reserved position to the peeling end surface being H1;

[0021] S120, marking a to-be-peeled mark in the reserved area, the distance from the to-be-peeled mark to the peeling end surface being H2, and the H1 being greater than the H2.

[0022] In some embodiments, the step S110 further includes:

[0023] The peeling end surface to be processed is subjected to a flattening treatment, so that the peeling end surface is a plane.

[0024] In some embodiments, the step S500 specifically includes:

[0025] S510, applying a tearing force to the fragmented carbon fiber layer at the peeling end surface until the tearing crack of the carbon fiber layer extends to a preset tearing position, the preset tearing position being within the range of the peeling treatment area;

[0026] S520, inserting a support at the bottom of the tearing crack to expand the tearing crack.

[0027] With reference to the first aspect, in a possible implementation manner, the step S600 specifically includes:

[0028] The inner protective layer is torn at a preset separation angle, and the preset separation angle is less than 30°.

[0029] The solution described in this application, compared with the prior art, softens the outer protective layer through surface heating treatment, facilitating its removal. It then uses pressure to break up the carbon fiber layers, facilitating their separation. Finally, the inner protective layer is peeled off from the core by tearing. The fiber stripping method for the carbon fiber composite core rod of this application employs different removal methods based on the properties of different layers. This avoids the problems of uncontrollable cutting depth and low stripping success rate caused by using a single cutting method. It prevents damage to the fiber or incomplete stripping, ensuring the fiber is fully and completely separated, thereby achieving effective connection with external monitoring equipment and guaranteeing monitoring reliability.

[0030] Secondly, embodiments of the present invention also provide an optical fiber stripping device embedded in a carbon fiber composite core rod, used to realize the above-mentioned method for stripping optical fibers embedded in a carbon fiber composite core rod, including a heating device, a stripping device and a pressurizing device.

[0031] The heating device is used for surface heating treatment, the peeling device is used for peeling off the outer protective layer, and the pressurizing device is used for applying radial pressure to the peeling treatment area.

[0032] In conjunction with the second aspect, in one possible implementation, a heating cavity is formed inside the heating device, and an insertion hole communicating with the heating cavity is formed on the side wall of the heating device. The difference between the inner diameter of the insertion hole and the outer diameter of the carbon fiber composite mandrel is 1 to 3 mm.

[0033] In conjunction with the second aspect, in one possible implementation, the peeling device includes:

[0034] The fixed base has a receiving groove for accommodating the carbon fiber composite mandrel, and also has a lifting adjustment channel, which is connected to the receiving groove;

[0035] A lifting adjustment component is movably disposed in the lifting adjustment channel, and its top end can extend into the receiving groove; and

[0036] The planing device is located above the fixed base and can move along a preset direction, which is set at an angle to the vertical direction.

[0037] The solution described in this application, compared with the prior art, softens the outer protective layer using a heating device, facilitating its removal by a peeling device. Then, a pressure device breaks the carbon fiber layer, facilitating its separation. Finally, the inner protective layer is peeled off from the core by tearing. The fiber stripping device embedded in the carbon fiber composite core rod of this application employs different removal methods based on the properties of different layers. This avoids the problems of uncontrollable cutting depth and low stripping success rate caused by using a single cutting method, preventing damage to the fiber or incomplete stripping. The fiber can be fully and completely separated, thereby achieving effective connection with external monitoring equipment and ensuring monitoring reliability. Attached Figure Description

[0038] Figure 1 This is a schematic cross-sectional view of a carbon fiber composite core rod used for fiber stripping via the fiber stripping method embedded in the carbon fiber composite core rod of the present invention. Figure 1 ;

[0039] Figure 2 This is a schematic cross-sectional view of a carbon fiber composite core rod used for fiber stripping via the fiber stripping method embedded in the carbon fiber composite core rod of the present invention. Figure 2 ;

[0040] Figure 3 This is a side view of a carbon fiber composite core rod used for fiber stripping using the fiber stripping method embedded in the carbon fiber composite core rod of the present invention.

[0041] Figure 4 This is a schematic diagram of the heating device used in this invention, where the arrows indicate the insertion direction of the carbon fiber composite core rod.

[0042] Figure 5 This is a partial view of the mating structure of the heating device and the carbon fiber composite mandrel used in this invention, where the arrows indicate the insertion direction of the carbon fiber composite mandrel.

[0043] Figure 6 This is a schematic diagram of the fitting process between the fixed base and the lifting adjustment component used in this invention and the carbon fiber composite mandrel, wherein the arrows indicate the insertion direction of the carbon fiber composite mandrel.

[0044] Figure 7 This is a partial view of the adaptation structure of the fixed base and lifting adjustment component with the carbon fiber composite mandrel used in this invention.

[0045] Explanation of reference numerals in the attached figures:

[0046] 100. Carbon fiber composite mandrel;

[0047] 110. Optical fiber; 120. Inner protective layer; 130. Carbon fiber layer; 131. First side surface; 132. Second side surface; 140. Outer protective layer;

[0048] 101. Peeling treatment area; 102. Peeling end face; 103. First position line; 104. Second position line; 105. Actual peeling position line;

[0049] 200. Heating device; 210. Heating chamber; 220. Insertion hole;

[0050] 300. Peeling device; 310. Fixing base; 311. Receiving groove; 320. Lifting adjustment component; 321. Lifting plate; 322. Lifting adjustment rod. Detailed Implementation

[0051] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0052] Unless otherwise expressly defined, the use of terms such as "first," "second," or "third" in the claims, description, and accompanying drawings of this invention is for distinguishing different objects and not for describing a specific order.

[0053] Unless otherwise expressly defined, in the claims, description, and accompanying drawings of this invention, the use of directional terms such as "center," "lateral," "longitudinal," "horizontal," "vertical," "top," "bottom," "inner," "outer," "upper," "lower," "front," "rear," "left," "right," "clockwise," "counterclockwise," "high," and "low" to indicate orientation or positional relationships is based on the orientation and positional relationships shown in the accompanying drawings and is only for the convenience of describing the invention and simplifying the description, and is not intended to indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the specific scope of protection of this invention.

[0054] Unless otherwise expressly defined, the terms "fixed connection" or "fixed connection" used in the claims, description and drawings of this invention should be interpreted broadly to refer to any connection in which there is no displacement or relative rotation relationship between the two parties, including non-removable fixed connection, detachable fixed connection, integral connection and fixed connection by other means or components.

[0055] In the claims, description and accompanying drawings of this invention, the terms "comprising," "having," and variations thereof are used to mean "including but not limited to."

[0056] The present invention will now describe a method for stripping optical fibers embedded in a carbon fiber composite core rod. This method is used to strip optical fibers 110 from a carbon fiber composite core rod 100. The carbon fiber composite core rod 100 includes, from the inside out, an optical fiber 110, an inner protective layer 120, a carbon fiber layer 130, and an outer protective layer 140, wherein the inner protective layer 120 is an organic fiber layer, and the outer protective layer 140 is a glass fiber braided layer, such as... Figure 1 and Figure 2 As shown, the inner protective layer 120 and the optical fiber 110, the inner protective layer 120 and the carbon fiber layer 130, and the carbon fiber layer 130 and the outer protective layer 140 are all bonded and fixed by resin adhesive curing. Based on this, the method for stripping the optical fiber embedded in the carbon fiber composite core rod includes the following steps:

[0057] S100, Delineate the peeling treatment area 101 on the carbon fiber composite mandrel 100 to be treated;

[0058] S200, Perform surface heating treatment on the stripping treatment area 101;

[0059] S300, peel off the outer protective layer 140 that has undergone surface heating treatment in the peeling treatment area 101;

[0060] S400, Apply radial pressure to the stripping treatment area 101 until the carbon fiber layer 130 breaks;

[0061] S500, peeling off the fragmented carbon fiber layer 130;

[0062] S600, tear-off inner protective layer 120.

[0063] In this embodiment, the length of the stripping treatment area 101 is related to the operational requirements of connecting the optical fiber 1 and the monitoring equipment. Generally, it is necessary to expose about 30cm of the optical fiber 1. Its specific length is not limited here.

[0064] The fiber stripping method for embedded optical fibers in the carbon fiber composite core rod provided in this embodiment, compared with the prior art, softens the outer protective layer 140 through surface heating treatment, facilitating its removal. It also breaks the carbon fiber layer 130 through pressure softening, facilitating its separation. Finally, the inner protective layer 120 is peeled off from the core body by tearing. This fiber stripping method for embedded optical fibers in the carbon fiber composite core rod 100 employs different removal methods based on the properties of different layers, avoiding the problems of uncontrollable cutting depth and low stripping success rate caused by using a single cutting method. It also avoids damage to the optical fiber 110 or incomplete stripping, ensuring that the optical fiber 110 can be fully and completely separated, thereby achieving effective connection with external monitoring equipment and ensuring monitoring reliability.

[0065] In some embodiments, in step S200, the heating temperature for surface heat treatment is 320–400°C (e.g., 340°C, 360°C), and the heating time is 40–90 seconds (e.g., 50 seconds, 60 seconds, 70 seconds). This embodiment, by reasonably setting the heating temperature and keeping the heating time within a short range, softens the outer protective layer 140 while avoiding the impact of high temperatures on the carbon fiber layer 130 and the optical fiber 110. The carbon fiber layer 130 retains a certain degree of hardness, facilitating subsequent cutting and removal of the outer protective layer 140, while also ensuring that the performance of the optical fiber 110 itself is not affected.

[0066] In some embodiments, step S300 specifically includes: cutting and removing the outer protective layer 140 located on the first side 131 and the second side 132 of the carbon fiber layer 130, wherein the first side 131 and the second side 132 are parallel to each other, or the first side 131 and the second side 132 are set at an angle. Figure 2 The dashed boxes in the figure indicate the positions corresponding to the first side 131 and the second side 132. It can be understood that the outer protective layer 140 within the dashed boxes is the outer protective layer 140 that needs to be removed. This embodiment uses a partial removal method for the outer protective layer 140, which does not require complete removal of the outer protective layer 140 while still meeting the tearing requirements of the carbon fiber layer 130. The removal area of ​​the outer protective layer 140 can extend to the actual peeling position line 105.

[0067] In practice, to facilitate the application of pressure and ensure effective fragmentation of the carbon fiber layer 130, the first side 131 and the second side 132 are perpendicular to each other, as shown below. Figure 2 As shown. Based on this, pressure can be applied in a direction perpendicular to the first side 131, such as pressure F21 and pressure F22 shown in the figure, where F21 and F22 are reaction forces; pressure can also be applied in a direction perpendicular to the second side 132, such as pressure F11 and pressure F12 shown in the figure, where F11 and F12 are reaction forces.

[0068] In other embodiments, the first side 131 and the second side 132 are parallel to each other and arranged opposite to each other, not shown in the figure. In this structure, pressure can also be applied in a direction perpendicular to the first side 131. Similar to the aforementioned vertically arranged embodiments, the outer protective layer 140 is generally removed at the location where the tear in the carbon fiber layer 130 is formed.

[0069] In some embodiments, step S100 specifically includes:

[0070] S110, Move the stripping end face 102 of the carbon fiber composite mandrel 100 to the reserved position (e.g., Figure 3The area shown in the first position line 103 is defined as the reserved area, and the distance from the reserved position to the stripping end face is H1;

[0071] S120, Mark the area to be peeled off within the reserved area (e.g., Figure 3 The distance from the mark to be peeled to the peeling end face 102 is H2, and H1 is greater than H2. (As shown in the second position line 104)

[0072] This embodiment sets up a larger area than the stripping treatment area 101 to provide a buffer zone for the extension of various deformations of the carbon fiber layer 130, outer protective layer 140 and inner protective layer 120 during operation, so as to avoid affecting the structure and performance of the mandrel body.

[0073] In some embodiments, to facilitate easier positioning when setting various position lines and to improve the controllability of carbon fiber layer 130 fragmentation, step S110 further includes: flattening the peeling end face 102 to be processed, making the peeling end face 102 a plane. More specifically, the flattening process can be achieved by sawing, grinding, etc., and is not limited to this method.

[0074] In some embodiments, step S500 specifically includes:

[0075] S510. At the peeling end face 102, a tearing force is applied to the fragmented carbon fiber layer 130 until the tear in the carbon fiber layer 130 extends to a preset tear position (e.g., Figure 3 (As shown in the actual peeling location line 105), the preset tearing location is within the peeling treatment area.

[0076] S520. Insert a support at the bottom of the tear to open the tear.

[0077] This embodiment separates the carbon fiber layer 130 from the inner protective layer 120 by tearing. The operation is simple, the separation effect is reliable, and it helps to improve work efficiency.

[0078] In practice, the support member can be a support rod with an outer diameter of 2.5 to 3.5 mm (e.g., 3 mm). The support rod can be directly inserted laterally into the tear seam and supported between the carbon fiber layer 130 and the inner protective layer 120.

[0079] In some embodiments, to ensure that the inner protective layer 120 can fully detach from the carbon fiber layer 130 while avoiding damage to the optical fiber 110, step S600 specifically includes: tearing the inner protective layer 120 at a preset separation angle, where the preset separation angle is less than 30°. The preset separation angle is the tilt angle of the inner protective layer 120 relative to the optical fiber 110. By reasonably controlling the preset separation angle, the optical fiber 110 can be subjected to a smaller radial force during the tearing process, preventing irreversible bending of the optical fiber 110 due to excessive bending, and ensuring that the optical fiber 110 is completely and successfully peeled out.

[0080] In some embodiments, step S400 specifically includes:

[0081] S410. A pressure position line is set at a distance H3 from the peeling end face 102 on the outer periphery of the carbon fiber composite mandrel 100, and the area between the peeling end face 102 and the pressure position line is defined as the fracturing area, wherein the pressure position line is located between the peeling end face 102 and the actual peeling position line 105.

[0082] S420. Place the fracturing zone within the pressurization range and align the pressurization position line with the edge of the pressurization zone.

[0083] In this embodiment, the stripping treatment area 101 is further divided, so that the carbon fiber composite core rod 100 has a longer buffer zone to accommodate the deformation and extension of the carbon fiber layer 130, the outer protective layer 140 and the inner protective layer 120, thereby maximizing the guarantee that the fiber separation operation and the core rod body have a complete structure and stable performance.

[0084] In some embodiments, the outer protective layer 140 can be removed by planing. During the planing process, the carbon fiber layer 130 can be planed without damaging the inner protective layer 120, and without affecting the fracturing effect.

[0085] Based on the same inventive concept, this application also provides an optical fiber stripping device embedded in a carbon fiber composite core rod, used to realize the above-mentioned method for stripping optical fibers embedded in a carbon fiber composite core rod, including a heating device 200, a peeling device 300 and a pressurizing device; the heating device 200 is used for surface heating treatment, the peeling device 300 is used to peel off the outer protective layer 140, and the pressurizing device is used to apply radial pressure to the peeling treatment area.

[0086] The fiber stripping device embedded in the carbon fiber composite core rod provided in this embodiment, compared with the prior art, softens the outer protective layer 140 through the heating device 200, facilitating the removal of the outer protective layer 140 by the peeling device 300. Then, the carbon fiber layer 130 is broken by the pressure device, facilitating its separation. Finally, the inner protective layer 120 is peeled off from the core by tearing. The fiber stripping device embedded in the carbon fiber composite core rod of this embodiment employs different removal methods according to the properties of different layers in the carbon fiber composite core rod 100, avoiding the problems of difficult-to-control cutting depth and low stripping success rate caused by using a single cutting method. It also avoids damage to the fiber 110 or insufficient stripping, ensuring that the fiber 110 is fully and completely separated, thereby achieving effective connection with external monitoring equipment and ensuring monitoring reliability.

[0087] See Figure 4 and Figure 5 In some embodiments, a heating cavity 210 is formed inside the heating device 200, and an insertion hole 220 communicating with the heating cavity 210 is formed on the side wall of the heating device 200. The difference between the inner diameter of the insertion hole 220 and the outer diameter of the carbon fiber composite mandrel 100 is 1-3 mm (e.g., 2 mm). The heating cavity 210 is heated to a preset temperature at a certain rate and stabilized for 5-15 minutes (e.g., 10 minutes) to create a stable heating environment in the heating cavity 210. In this embodiment, the method of inserting the carbon fiber composite mandrel 100 into the heating cavity 210 is specifically designed according to the structure of the carbon fiber composite mandrel 100. By using an insertion method, the carbon fiber composite mandrel 100 can be quickly inserted and quickly pulled out, which facilitates the control of heating time. At the same time, the reasonable setting of the diameter of the insertion hole 220 ensures that the carbon fiber composite mandrel 100 can be smoothly inserted and pulled out, and also avoids excessive heat loss from the heating cavity 210, which helps to reduce energy consumption.

[0088] In some embodiments, the heating device 200 may be a heating furnace, the inner cavity of which (i.e., heating chamber 210) has a length of not less than 50 cm, a width of not less than 40 cm, a height of not less than 40 cm, an upper limit of operating temperature of 800℃, and a temperature rise error of less than ±3℃. An insertion hole 220 is provided on the furnace door, the depth of which is not greater than the distance between the second position line 104 and the actual glass position line 105, ensuring that the outer protective layer 140 that actually needs to be peeled off can fully enter the heating chamber 210 for sufficient heating.

[0089] In some embodiments, the peeling device 300 described above may employ, for example... Figure 6 and Figure 7 The structure shown. See also Figure 6 and Figure 7The peeling device 300 includes a fixed base 310, a lifting adjustment component 320, and a planing device. The fixed base 310 has a receiving groove 311 for accommodating the carbon fiber composite mandrel 100, and also has a lifting adjustment channel communicating with the receiving groove 311. The lifting adjustment component 320 is movably disposed in the lifting adjustment channel, and its top end can extend into the receiving groove 311. The planing device is located above the fixed base 310 and can move along a preset direction, which is set at an angle to the vertical direction. To ensure positioning accuracy, the difference between the width of the receiving groove 311 and the diameter of the carbon fiber composite mandrel 100 is no more than 1 mm. The planing device can be a planer blade capable of fixing the planing depth (e.g., a double-wire bird planer). In this embodiment, the upward convex height of carbon fiber composite mandrels 100 of different sizes can be adjusted by adjusting the lifting adjustment component 320, making it more flexible to use.

[0090] In practice, one end of the receiving groove 311 is closed and the other end is open. The closed end can contact the peeling end face 102 of the carbon fiber composite mandrel 100 to restrict the displacement of the carbon fiber composite mandrel 100 in the axial direction.

[0091] In some embodiments, the lifting adjustment member 320 may be adopted as follows: Figure 6 and Figure 7 The structure shown. See also Figure 6 and Figure 7 The lifting adjustment component 320 includes a lifting plate 321 and multiple lifting adjustment rods 322. The upper ends of the lifting adjustment rods 322 are rotatably engaged with the lifting plate 321. The lifting plate 321 can move up and down within the receiving groove 311. The lifting adjustment rods 322 are screws, and the lifting adjustment channel is provided with internal threads that engage with the lifting adjustment rods 322.

[0092] Based on the above embodiment (not shown in the figure), a position sensor is provided on the upper surface of the fixed base 310. A positioning component that can move closer to or further away from the fixed base in the vertical direction is provided above the fixed base 310. A pressure sensor is provided on the positioning plate. Both the position sensor and the pressure sensor are communicatively connected to a control terminal (e.g., an industrial computer). The height h that the carbon fiber composite mandrel 100 needs to protrude from the upper surface of the fixed base is defined as the position of the positioning plate. First, the position of the positioning plate is adjusted. The distance D between the positioning plate and the upper surface of the fixed base 310 is sensed in real time by the position sensor until the value of the distance D is equal to h. With the lifting plate 321 at its lowest position, the carbon fiber composite mandrel 100 is placed into the receiving groove 311. The lifting adjustment rod 322 is adjusted to raise the carbon fiber composite mandrel 100 using the lifting plate 321. When the carbon fiber composite mandrel 100 contacts the lower surface of the positioning plate, the pressure sensor feeds back the pressure value. The pressure value is used to determine whether the carbon fiber composite mandrel 100 is properly adjusted. If properly adjusted, the rotation of the lifting adjustment rod 322 is stopped, and then the positioning plate is removed. This embodiment can more accurately locate the protrusion height of the carbon fiber composite mandrel 100, avoiding the problem of errors caused by operators using measuring tools such as rulers, and can more accurately limit the planing depth.

[0093] Determine whether the carbon fiber composite mandrel 100 is properly adjusted based on the pressure value, specifically including the following:

[0094] a) If the pressure value is within the preset range, it means that the carbon fiber composite mandrel 100 is in effective contact with the positioning plate. At this time, it is determined that the height of the carbon fiber composite mandrel 100 is adjusted in place.

[0095] b) If the pressure value is higher than the maximum value of the preset range, it means that the height of the lifting adjustment rod 322 is too high. It needs to be turned in the opposite direction to reduce the pressure value appropriately. This is to prevent the carbon fiber composite mandrel 100 from releasing the stress of extrusion deformation after the positioning plate is removed, which would cause the protrusion height to exceed the preset protrusion height value.

[0096] c) If the pressure value is 0, it is determined that the carbon fiber composite mandrel 100 is too low and does not make effective contact with the positioning plate. At this time, it is necessary to continue to rotate the lifting adjustment rod 322 in the forward direction until the pressure value is within the preset range.

[0097] In this embodiment, the minimum value of the preset range is greater than 0. Specifically, the minimum value of the preset range is 0.5N and the maximum value is 2N.

[0098] In some embodiments, the pressurizing device can be a manual press or an automatic press. Taking a manual press as an example, it can be a manual spring press with a maximum pressure of 5KN, such as the J03-0.5A (spring type) spring press. Generally speaking, the pressurizing device can be obtained by purchasing existing equipment, and its specific structure will not be described in detail here.

[0099] Based on the aforementioned fiber stripping device embedded in the carbon fiber composite core rod, a specific implementation of the fiber stripping method embedded in the carbon fiber composite core rod of this application is illustrated below:

[0100] 1) Cut the stripped end face 102 of the carbon fiber composite mandrel 100 into a flat surface using a hacksaw;

[0101] 2) Set the distance between the first position line 103 and the stripping end face 102 to 40cm, that is, the value of H1 is 40cm;

[0102] 3) Set the distance between the second position line 104 and the peeling end face 102 to 35cm, that is, the value of H2 is 35cm;

[0103] 4) Heat the heating chamber 210 to 360℃ and stabilize it for 10 minutes;

[0104] 5) Insert the carbon fiber composite mandrel 100 into the insertion hole 220, making the second position line 104 flush with the outer end face of the insertion hole 220, such as... Figure 5 As shown, the heating time is 60 seconds. After heating is completed, the carbon fiber composite mandrel 100 is quickly pulled out, at which point the outer protective layer 140 softens.

[0105] 6) Place the carbon fiber composite mandrel 100 into the receiving groove 311, and turn the lifting adjustment rod 322 so that the carbon fiber composite mandrel 100 is 0.5 to 1 mm higher than the top surface of the fixed base 310.

[0106] 7) Adjust the blade of the planer to extend 0.5mm beyond the bottom surface of the planer body, and plane 2 to 3 times until the outer protective layer 140 corresponding to the first side 131 of the carbon fiber layer 130 is removed.

[0107] 8) Rotate the carbon fiber composite mandrel 100 by 90° and scrape the outer protective layer 140 located on the second side 132 of the carbon fiber layer 130 until the outer protective layer 140 corresponding to the second side 132 of the carbon fiber layer 130 is removed.

[0108] 9) Adjust the stroke of the manual spring press to match the diameter of the carbon fiber composite mandrel 100. Place a steel plate on the worktable and insert a 5-10 mm area (i.e., H3 value is 5-10 mm) of the end of the carbon fiber composite mandrel 100 between the press punch and the steel plate. Apply pressure to 2.5-3.0 KN until the carbon fiber layer 130 in this area breaks.

[0109] 10) Pick out the inner protective layer 120 and the optical fiber 110 wrapped in it from the broken carbon fiber layer 130, and use needle-nose pliers to apply a tearing force in a direction perpendicular to the first side 131 or the second side 132 to separate the carbon fiber layer 130 from the inner protective layer 120 until the tear length of the carbon fiber layer 130 is 30cm (that is, the tear seam of the carbon fiber layer 130 extends to the actual peeling position line 105).

[0110] 11) Insert a support rod with a diameter of 3 mm and a length of 5 cm into the bottom of the tear in the carbon fiber layer 130 to open the tear and expose the optical fiber 110 wrapped with the inner protective layer 120.

[0111] 12) Apply tearing force to the inner protective layer 120 with needle-nose pliers, and keep the separation angle less than 30° and the tearing speed less than 1cm / min until the tear length of the inner protective layer 120 is 30cm (that is, the tear seam of the inner protective layer 120 extends to the actual peeling position line 105).

[0112] 13) Using the actual stripping position line 105 as the cutting line, cut off the outer protective layer 140, carbon fiber layer 130 and inner protective layer 120. The separation length of the optical fiber 110 is 30cm.

[0113] The fiber stripping method and stripping equipment embedded in the carbon fiber composite core rod of this application can adopt different removal methods for different layers with different structures and properties, avoid the problem of insufficient stripping or damage to the fiber 110, and improve the success rate of fiber 110 stripping, the reliability of the operation and the efficiency.

[0114] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method of stripping an optical fiber embedded in a carbon fiber composite mandrel for stripping an optical fiber embedded in a carbon fiber composite mandrel, the carbon fiber composite mandrel including, in order from the inside out, an optical fiber, an inner protective layer, a carbon fiber layer, and an outer protective layer, characterized by, The method for stripping the optical fiber embedded in the carbon fiber composite core rod comprises the following steps: S100, defining a stripping treatment area on the carbon fiber composite core rod to be treated; S200, performing surface heating treatment on the stripping treatment area; S300, stripping the outer protective layer subjected to the surface heating treatment; S400, applying radial pressure to the stripping treatment area until the carbon fiber layer is fragmented; S500, stripping the fragmented carbon fiber layer; S600, tearing the inner protective layer; The step S100 specifically comprises: S110, defining a reserved area from the stripping end face of the carbon fiber composite core rod to be treated to a reserved position, the distance from the reserved position to the stripping end face being H1; S120, marking a to-be-stripped mark in the reserved area, the distance from the to-be-stripped mark to the stripping end face being H2, and the H1 being greater than the H2; The step S500 specifically comprises: S510, applying a tearing force to the fragmented carbon fiber layer at the stripping end face until the tearing seam of the carbon fiber layer extends to a preset tearing position, the preset tearing position being within the range of the stripping treatment area; S520, inserting a support at the bottom of the tearing seam to expand the tearing seam.

2. The method of claim 1, wherein the carbon fiber composite mandrel is a carbon fiber composite rod. In the step S200, the heating temperature of the surface heating treatment is 320-400°C, and the heating duration is 40-90s.

3. The method of claim 1, wherein the carbon fiber composite mandrel is a carbon fiber composite rod. The step S300 specifically comprises: The outer protective layer located at the first side face and the second side face of the carbon fiber layer is removed by cutting, the first side face and the second side face being parallel to each other, or the first side face and the second side face being arranged at an angle.

4. The method for stripping optical fibers embedded in a carbon fiber composite core rod as described in claim 1, characterized in that, Before the step S110, the following step is further included: Performing planarization treatment on the stripping end face to be treated so that the stripping end face is a plane.

5. The method for stripping optical fibers embedded in a carbon fiber composite core rod as described in claim 1, characterized in that, The step S600 specifically comprises: Tearing the inner protective layer at a preset separation angle, the preset separation angle being less than 30°.

6. A stripping apparatus for an in-line optical fiber in a carbon fiber composite mandrel for implementing the method of stripping an in-line optical fiber in a carbon fiber composite mandrel according to any one of claims 1 to 5, characterized in that The device comprises a heating device, a peeling device and a pressurizing device; The heating device is used for performing surface heating treatment, the peeling device is used for stripping the outer protective layer, and the pressurizing device is used for applying radial pressure to the stripping treatment area.

7. The stripped optical fiber in a carbon fiber composite mandrel according to claim 6, wherein, A heating cavity is formed in the heating device, a side wall of the heating device is formed with a jack that is in communication with the heating cavity, and the difference between the inner diameter of the jack and the outer diameter of the carbon fiber composite core rod is 1-3mm.

8. The stripped optical fiber in a carbon fiber composite mandrel according to claim 6, wherein, The peeling device comprises: A fixed seat that is provided with an accommodation groove for accommodating the carbon fiber composite core rod and is further provided with a lifting adjustment channel that is in communication with the accommodation groove; A lifting adjustment member that is movably arranged in the lifting adjustment channel and has a top end capable of extending into the accommodation groove; and A planing device that is located above the fixed seat and is movable along a preset direction, the preset direction being arranged at an angle to the vertical direction.

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