Aerospace lightweight optical cable and method of making same

Abstract

The application discloses a light optical cable for aerospace and a preparation method thereof. The light optical cable for aerospace comprises a first protective sleeve and a second protective sleeve, a plurality of optical fibers are coaxially arranged in the first protective sleeve, the second protective sleeve is coaxially arranged outside the first protective sleeve, a first cavity is formed between the second protective sleeve and the first protective sleeve, and the first cavity is used for flowing cooling liquid. The light optical cable for aerospace has the first cavity arranged in the optical cable, the cooling liquid is injected into the first cavity and flows in the first cavity, and the cooling liquid absorbs heat generated during the operation of the optical cable during the flowing process, so that the temperature of the optical cable is reduced. The temperature of the optical cable can be effectively adjusted through the cooling liquid, and the optical cable can maintain a good working state in a high-temperature environment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of cable, in particular to a light optical cable for aerospace and a preparation method thereof. BACKGROUND

[0002] As a transmission medium, optical fiber has the advantages of ultra-light, wide bandwidth, anti-electromagnetic interference, good security, etc. compared with traditional copper cable. In recent years, with the development of the aviation industry, the application research of optical fiber cable in the field of aerospace is becoming more and more extensive. The optical cable for aerospace is different from the ordinary optical fiber cable. Its applicability and safety are fully considered. It requires light weight, thin diameter, high temperature resistance, mechanical and optical stability in long-term high temperature range, high strength, bending resistance, impact resistance, aging resistance, acid and alkali resistance, resistance to various fuels and oils, flame retardant, low smoke and low toxicity and other special requirements.

[0003] However, the conventional optical cable has a service temperature of-40℃ to +70℃. In the fields of aviation, shipping, wind power generation, etc., the working environment is harsh, and the temperature can reach above 125℃ during work and can reach-60℃. When the temperature exceeds 70℃ or is lower than-40℃, the performance of the optical fiber and the outer sheath material in the optical cable will decrease sharply, the optical fiber is easy to break, and the outer sheath is severely aged, which cannot guarantee the normal work of the optical cable. Therefore, the conventional optical cable cannot meet the application requirements in harsh environments such as aerospace. SUMMARY

[0004] The present application aims to overcome the shortcomings of the prior art, and provides a light optical cable for aerospace and a preparation method thereof, so as to solve the technical problem that the existing optical cable cannot meet the harsh environment of aerospace.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0006] In a first aspect, the present application provides a light optical cable for aerospace, comprising: a first protective sleeve and a second protective sleeve, a plurality of optical fibers are coaxially arranged in the first protective sleeve; the second protective sleeve is coaxially arranged outside the first protective sleeve, and a first cavity is formed between the second protective sleeve and the first protective sleeve; the first cavity is used for circulating cooling liquid.

[0007] As a preferred technical solution of the present application, the second protective sleeve is provided with a first one-way valve and a second one-way valve communicating with the first cavity, the first one-way valve is communicated from the outside of the optical cable to the first cavity, and the second one-way valve is communicated from the first cavity to the outside of the optical cable.

[0008] As a preferred technical solution of the present application, a quantitative pump is arranged at the first one-way valve, and the output end of the quantitative pump is communicated with the input end of the first one-way valve.

[0009] As a preferred technical solution of the present application, a third protective sleeve is coaxially sleeved outside the second protective sleeve, a second cavity is arranged in the third protective sleeve, and a current variable fluid and a conductor wire are arranged in the second cavity, and the conductor wire is electrically connected to the controller.

[0010] As a preferred technical solution of the present application, the controller is a control system provided for an aircraft to which the optical cable is applied.

[0011] As a preferred technical solution of the present application, the current variable fluid comprises polymethyl methacrylate microsphere particles, silicon oil, polyethylene glycol and a dyeing agent.

[0012] As a preferred technical solution of the present application, a flow detection device is arranged at the second one-way valve, and the flow detection device is electrically connected to the controller.

[0013] When the flow detection device detects that the flow variation of the second one-way valve is greater than a preset variable value, the controller supplies power to the conductor wire; and when the flow detection device detects that the flow variation of the second one-way valve is less than the preset variable value, the controller makes the conductor wire be powered off.

[0014] As a preferred technical solution of the present application, the flow detection device comprises a shell, a rotor and a Hall switch, a third cavity is arranged in the shell, a liquid inlet and a liquid outlet communicating with the third cavity are respectively arranged at opposite sides of the shell, the liquid inlet is communicated with an output end of the second one-way valve, the rotor is rotatably arranged between the liquid inlet and the liquid outlet, and the rotor comprises a magnetic member, the Hall switch is arranged outside the shell, the Hall switch detects the flow variation of the second one-way valve through the magnetic field change generated by the rotation of the magnetic member, and the Hall switch is electrically connected to the controller.

[0015] In a second aspect, the present application provides a preparation method of a lightweight optical cable for aerospace, comprising the lightweight optical cable for aerospace as described in the first aspect, and comprising the following steps:

[0016] A plurality of optical fibers are woven together, and a first protective sleeve is sleeved outside the plurality of optical fibers after weaving;

[0017] A second protective sleeve is sleeved outside the first protective sleeve, a flow detection device is connected to a controller, and a first one-way valve and a second one-way valve are respectively connected to an outlet and an inlet of a cooling liquid tank;

[0018] A third protective sleeve is sleeved outside the second protective sleeve, and a conductor wire in a second cavity is connected to the controller.

[0019] As a preferred technical scheme of the present application, the second protective sleeve is sleeved outside the first protective sleeve, the flow detection device is connected to the controller, and the cooling liquid is injected into the first cavity through the first one-way valve, comprising:

[0020] The cooling liquid is injected into the first cavity through the first one-way valve, and after the flow measured by the flow detection device is stable, the flow measured by the flow detection device at this time is set as the reference flow of the second one-way valve;

[0021] The flow change amount of the second one-way valve is set as the difference between the real-time flow detected by the flow detection device and the reference flow;

[0022] The preset variable value is input, and the preset variable value and the flow change amount of the second one-way valve are compared in real time.

[0023] The aerospace light optical cable of the present application, by setting a first cavity inside the optical cable, the cooling liquid is injected into the first cavity and flows inside, the cooling liquid absorbs the heat generated during the operation of the optical cable during the flow process, thereby reducing the temperature of the optical cable, the temperature of the optical cable can be effectively adjusted by the cooling liquid, and the optical cable can maintain good working state in high temperature environment.

[0024] The above description is only a summary of the technical scheme of the present application, in order to more clearly understand the technical means of the present application, the content of the specification can be implemented, and in order to make the above and other purposes, characteristics and advantages of the present application more obvious and easy to understand, the following preferred embodiments are described in detail as follows. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 It is a first structure schematic diagram of the aerospace light optical cable of the embodiment of the present application.

[0026] Figure 2 It is a second structure schematic diagram of the aerospace light optical cable of the embodiment of the present application.

[0027] Figure 3 It is a schematic diagram of the external structure of the flow detection device of the aerospace light optical cable of the embodiment of the present application.

[0028] Figure 4 It is an exploded view of the flow detection device of the aerospace light optical cable of the embodiment of the present application.

[0029] Figure 5 It is a flow chart of the preparation method of the aerospace light optical cable of the embodiment of the present application.

[0030] Figure 6 It is a sub-flow chart of the preparation method of the aerospace light optical cable of the embodiment of the present application.

[0031] Explanation of reference signs:

[0032] 10, first protective sleeve; 11, optical fiber; 12, coolant; 20, second protective sleeve; 21, first one-way valve; 22, second one-way valve; 30, third protective sleeve; 31, electrorheological fluid; 32, conductor wire; 40, constant flow pump; 50, flow detection device; 51, housing; 511, liquid inlet; 512, liquid outlet; 52, rotor; 53, Hall switch. DETAILED DESCRIPTION

[0033] In order to make the objects, technical solutions and advantages of the present application clearer, further specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0034] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0035] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship based on the drawings described, and are only for the purpose of facilitating the description of the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0036] In addition, the terms "first" and "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first" and "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise specifically limited.

[0037] In the present application, unless otherwise specifically defined and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood broadly, for example, it can be connected, or detachable, or integrated; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0038] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0039] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. The illustrative expressions of the above terms in this specification should not be construed as necessarily referring to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0040] In the aerospace field, optical cables face extreme temperature conditions and complex environmental challenges. Traditional optical cables typically operate within a temperature range of -40°C to +70°C, but in aerospace applications, they may be exposed to a wider temperature range, ranging from temperatures above 125°C to as low as -60°C. Under such conditions, the performance of the optical fiber (11) and the outer sheath material deteriorates rapidly, leading to problems such as fiber breakage and sheath aging, thus affecting the normal operation of the optical cable. Therefore, designing an optical cable structure capable of maintaining stable performance under harsh temperature conditions is of paramount importance.

[0041] Please see Figures 1 to 2 , Figure 1 This is a schematic diagram of the first structure of a lightweight optical cable for aerospace applications according to an embodiment of the present invention. Figure 2This is a schematic diagram of the second structure of a lightweight optical cable for aerospace applications according to an embodiment of the present invention. The present invention provides a lightweight optical cable for aerospace applications, comprising: a first protective sleeve 10 and a second protective sleeve 20. Multiple optical fibers 11 are coaxially arranged within the first protective sleeve 10. The second protective sleeve 20 is coaxially sleeved outside the first protective sleeve 10, forming a first cavity between the second protective sleeve 20 and the first protective sleeve 10. The first cavity is used for the flow of coolant 12. Specifically, this embodiment provides a first cavity inside the optical cable, into which coolant 12 is injected and flows. During its flow, the coolant 12 absorbs the heat generated during the operation of the optical cable, thereby reducing the temperature of the optical cable. The coolant 12 effectively regulates the temperature of the optical cable, ensuring it maintains good working condition in high-temperature environments.

[0042] Furthermore, the second protective sleeve 20 is provided with a first one-way valve 21 and a second one-way valve 22 connected to the first cavity. The first one-way valve 21 is open from the outside of the lightweight optical cable for aerospace to the first cavity, and the second one-way valve 22 is open from the first cavity to the outside of the lightweight optical cable for aerospace.

[0043] Understandably, in the coolant 12 circulation system, the liquid needs to flow in a predetermined direction to effectively remove the heat generated by the optical cable. If backflow occurs, it will not only affect the heat dissipation effect but may also cause liquid to accumulate in a certain part of the optical cable, resulting in problems such as excessive pressure and uneven local heat dissipation. In this embodiment, by setting the first one-way valve 21 and the second one-way valve 22, it can be ensured that the coolant 12 always flows in the predetermined direction, that is, it flows into the first cavity from the outside of the optical cable and then flows out of the first cavity to the outside of the optical cable, thereby ensuring the efficiency and stability of the heat dissipation process.

[0044] In some embodiments, the aircraft using the optical cable in this embodiment is equipped with a cooling tower. A first one-way valve 21 is connected to the outlet end of the cooling tower, and a second one-way valve 22 is connected to the inlet end of the cooling tower. Specifically, coolant 12 flows from the outside of the optical cable into the first cavity through the first one-way valve 21. The coolant 12 flowing into the first cavity flows along the cavity and exchanges heat with the first protective sleeve 10 of the optical cable, absorbing the heat generated when the optical cable is working, thereby cooling the optical cable. After absorbing heat, the coolant 12 flows out of the first cavity through the second one-way valve 22 and returns to the outside of the optical cable. The outflowing coolant 12 is collected and transported back to the external cooling tower. After being cooled, it is injected back into the first cavity through the first one-way valve 21. This cycle is repeated to achieve continuous cooling of the optical cable.

[0045] Furthermore, a metering pump 40 is installed at the first check valve 21, and the output end of the metering pump 40 is connected to the input end of the first check valve 21. The metering pump 40 is a pump capable of precisely controlling the output liquid flow rate. Through the precise control of the metering pump 40, the flow rate of the coolant 12 can be ensured to remain constant. This avoids resource waste and excessive system pressure caused by excessive flow, while also preventing poor heat dissipation caused by insufficient flow, thus improving the efficiency and reliability of the entire cooling system.

[0046] In some embodiments, the optical cable further includes a third protective sleeve 30, which is coaxially sleeved outside the second protective sleeve 20. The third protective sleeve 30 has a second cavity inside, and an electrorheological fluid 31 and a conductor wire 32 are disposed inside the second cavity. The conductor wire 32 is electrically connected to the controller.

[0047] It should be explained that optical cables in the aerospace field not only need to withstand high-temperature environments, but may also face various complex working conditions such as mechanical impacts, compression, and vibration. In this embodiment, a third protective sleeve 30 is added outside the second protective sleeve 20, and a second cavity containing an electrorheological fluid 31 and a conductor wire 32 is provided within it. This provides additional protection and buffering when the optical cable is subjected to external impacts or compression, preventing damage to the optical fiber 11 and ensuring the stability and reliability of optical signal transmission. Specifically, the electrorheological fluid 31 is a substance whose apparent viscosity or yield stress changes significantly under the action of an electric field. Without an electric field, the electrorheological fluid 31 has low viscosity and fluidity; when an electric field is applied, its internal charge distribution changes, and the interaction between particles is enhanced, leading to an increase in the viscosity of the electrorheological fluid 31 or the formation of a solid-like structure, thereby achieving a transformation from a fluid state to a semi-solid state. In this embodiment, by connecting the conductor wire 32 to the controller and utilizing the characteristics of the electrorheological fluid 31, the optical cable possesses the ability to intelligently respond to changes in the external environment.

[0048] In some embodiments, the controller is a control system provided for an aircraft in which aerospace lightweight optical cables are used.

[0049] It should be explained that aircraft are already equipped with complex control systems to manage various functions and parameters during flight. Integrating the fiber optic cable's control system with the aircraft's existing control system can avoid setting up a separate control device for the fiber optic cable, thereby saving space, reducing costs and energy consumption. At the same time, this integration also helps to improve the integration and synergy of the entire aircraft system, making it easier to manage and maintain in a unified manner.

[0050] In some embodiments, the electrorheological fluid 31 comprises polymethyl methacrylate (PMMA) microspheres, silicone oil, polyethylene glycol (PEG), and a dye. The PMMA microspheres, as the dispersed phase, possess excellent dielectric properties and mechanical strength, enabling them to rapidly align under an electric field. This allows the electrorheological fluid 31 to undergo a rapid phase transition under the influence of the electric field, changing from a fluid state to a semi-solid state, thereby enhancing the strength and rigidity of the optical cable and resisting external impacts or compression. The silicone oil, as the dispersion medium, has a low dielectric constant, high chemical stability, and good flowability, providing a favorable dispersion environment for the microspheres. This allows them to disperse uniformly in the absence of an electric field and rapidly and orderly align under an electric field. Furthermore, the stability of the silicone oil ensures the stable performance of the electrorheological fluid 31 over a wide temperature range. PEG, as a surfactant, reduces the interfacial tension between the microspheres and the silicone oil, improving the dispersion stability of the microspheres in the silicone oil and preventing particle aggregation and sedimentation. In addition, PEG can improve the flowability and uniformity of the electrorheological fluid 31, enhancing its electrorheological performance. The dyeing agent can give the electrorheological fluid 31 a distinct color. When the optical cable leaks, the leaking electrorheological fluid 31 will show the color of the dye, making it easy to visually identify the leak location. At the same time, the dyeing agent should have good compatibility with silicone oil and not affect the performance of the electrorheological fluid 31.

[0051] Optionally, the dye can be oil-soluble Sudan IV, which is soluble in silicone oil and has a bright red color, significantly improving the visibility of the electrorheological fluid 31 and facilitating rapid detection in case of leakage. Optionally, the electrorheological fluid 31 also includes a fluorescent whitening agent, which absorbs ultraviolet light and emits blue or violet light. Combined with the red color of Sudan IV, it can produce a brighter and more eye-catching color effect.

[0052] Please see Figure 1 and Figure 3 , Figure 4 , Figure 3 This is a schematic diagram of the external structure of the flow detection device for aerospace lightweight optical cables according to an embodiment of the present invention. Figure 4 This is an exploded view of a flow detection device for aerospace lightweight optical cables according to an embodiment of the present invention. In some embodiments, a flow detection device 50 is provided at the second one-way valve 22, and the flow detection device 50 is electrically connected to the controller; when the flow detection device 50 detects that the flow change of the second one-way valve 22 is greater than a preset variable value, the controller supplies power to the conductor line 32; when the flow detection device 50 detects that the flow change of the second one-way valve 22 is less than the preset variable value, the controller de-energizes the conductor line 32.

[0053] In this embodiment, the conductor line 32 connects the second cavity to the controller to form an intelligent control system. The controller monitors the flow change information fed back by the flow detection device 50 in real time. When the flow change exceeds the preset variable value, the controller determines that the optical cable may be subjected to impact or compression. It then sends a command to the conductor line 32 to apply an electric field to the electrorheological fluid 31 in the second cavity, triggering the phase change of the electrorheological fluid 31 and enhancing the optical cable's impact and compression resistance.

[0054] In some practical applications, when the optical cable is working normally and not subjected to impact or compression, the electrorheological fluid 31 in the second cavity is in a fluid-like state. At this time, the third protective sleeve 30 provides basic physical protection for the optical cable without affecting its flexibility and bendability. When the optical cable is subjected to external impact or compression, the flow rate of the coolant 12 in the first cavity changes. The flow detection device 50 monitors this change in real time and transmits the signal to the controller. After receiving the signal from the flow detection device 50, the controller determines whether the flow rate change exceeds a preset variable value. If it does, the controller sends a command to the conductor wire 32, which is energized and generates an electric field. Under the action of the electric field, the internal structure of the electrorheological fluid 31 in the second cavity changes, its viscosity increases, and it gradually changes from a fluid-like state to a semi-solid state. This significantly improves the strength and rigidity of the optical cable, effectively resisting external impact or compression and protecting the internal optical fiber 11 from damage. When the external impact or compression is eliminated, the controller can de-energize the conductor wire 32, the electrorheological fluid 31 loses the electric field effect, gradually returns to a fluid-like state, and the optical cable returns to its normal working state.

[0055] In some embodiments, the flow detection device 50 includes a housing 51, a rotor 52, and a Hall switch 53. The housing 51 has a third cavity, and an inlet 511 and an outlet 512 communicating with the third cavity are respectively provided on opposite sides of the housing 51. The inlet 511 is connected to the output end of the second check valve 22. The rotor 52 is rotatably disposed between the inlet 511 and the outlet 512, and the rotor 52 includes a magnetic element. The Hall switch 53 is disposed on the outside of the housing 51. The Hall switch 53 detects the flow change of the second check valve 22 by the change in the magnetic field generated by the rotation of the magnetic element. The Hall switch 53 is electrically connected to the controller.

[0056] Specifically, after the coolant 12 flows out from the output of the second one-way valve 22, it enters the third cavity through the inlet 511 of the flow detection device 50. Under the impact of the coolant 12, the rotor 52 begins to rotate, and the magnetic component on the rotor 52 rotates accordingly. When the rotor 52 rotates, the magnetic field generated by the magnetic component changes periodically at the position of the Hall switch 53. The Hall switch 53 senses the change in the magnetic field and generates a corresponding electrical signal. The frequency and amplitude of the electrical signal are proportional to the rotational speed of the rotor 52, and thus proportional to the flow rate of the coolant 12. The electrical signal generated by the Hall switch 53 is transmitted to the controller through a wire. The controller processes and analyzes the signal, calculates the current flow rate value, and compares it with a preset flow rate reference value. If the flow rate change exceeds the preset value, the controller determines that the optical cable may be subjected to impact or compression, and then sends a command to the conductor 32 to activate the protection measures. After the conductor 32 is energized, the electrorheological fluid 31 undergoes a phase change under the action of the electric field, changing from a fluid state to a semi-solid state, which enhances the strength and rigidity of the optical cable, resists external impact or compression, and protects the internal optical fiber 11 from damage.

[0057] This invention provides a method for manufacturing a lightweight optical cable for aerospace applications, including the aforementioned lightweight optical cable for aerospace applications. Figure 5 As shown, Figure 5 This is a flowchart of a method for preparing a lightweight optical cable for aerospace applications according to an embodiment of the present invention, including the following steps S100-S300:

[0058] S100. Braid multiple optical fibers together and cover the outside of the braided optical fibers with a first protective sleeve.

[0059] S200. A second protective sleeve is fitted over the outside of the first protective sleeve, the flow detection device is connected to the controller, and the first check valve and the second check valve are respectively connected to the outlet and inlet of the coolant tank.

[0060] S300, a third protective sleeve is fitted over the outside of the second protective sleeve, and the conductor wire in the second cavity is connected to the controller.

[0061] Furthermore, such as Figure 6 As shown, Figure 6 This is a sub-flowchart of the method for manufacturing lightweight optical cables for aerospace applications according to an embodiment of the present invention. Step S200 includes steps S210-230:

[0062] S210. Coolant is injected into the first cavity through the first check valve. After the flow rate measured by the flow detection device stabilizes, the flow rate measured by the flow detection device at this time is set as the reference flow rate of the second check valve.

[0063] S220. Set the flow rate change of the second check valve to the difference between the real-time flow rate detected by the flow detection device and the reference flow rate;

[0064] S230. Input a preset variable value and compare the preset variable value with the flow rate change of the second one-way valve in real time.

[0065] In this embodiment, by comparing the difference between the real-time traffic and the reference traffic, i.e. the traffic change, with a preset variable value, it can be determined whether the optical cable has been subjected to impact or compression, resulting in abnormal traffic changes.

[0066] The above examples are merely illustrative of the technical content of the present invention to facilitate easier understanding by the reader, but do not imply that the implementation of the present invention is limited to these examples. Any technical extensions or re-creations made based on the present invention are protected by the present invention. The scope of protection of the present invention is defined by the claims.

Claims

1. A lightweight optical cable for aerospace applications, characterized in that, include: A first protective sleeve and a second protective sleeve, wherein multiple optical fibers are coaxially arranged inside the first protective sleeve; the second protective sleeve is coaxially sleeved on the outside of the first protective sleeve, and a first cavity is formed between the second protective sleeve and the first protective sleeve; the first cavity is used for the flow of coolant. The second protective sleeve is provided with a first one-way valve and a second one-way valve communicating with the first cavity. The first one-way valve is open from the outside of the optical cable to the first cavity, and the second one-way valve is open from the first cavity to the outside of the optical cable. It also includes a third protective sleeve, which is coaxially sleeved on the outside of the second protective sleeve. The third protective sleeve has a second cavity inside, in which electrorheological fluid and a conductor wire are disposed, and the conductor wire is electrically connected to the controller.

2. The lightweight optical cable for aerospace applications according to claim 1, characterized in that, A metering pump is provided at the first check valve, and the output end of the metering pump is connected to the input end of the first check valve.

3. The lightweight optical cable for aerospace applications according to claim 1, characterized in that, The controller is a control system provided in the aircraft to which the optical cable is applied.

4. The lightweight optical cable for aerospace applications according to claim 1, characterized in that, The electrorheological fluid comprises polymethyl methacrylate microspheres, silicone oil, polyethylene glycol, and a dyeing agent.

5. The lightweight optical cable for aerospace applications according to claim 1, characterized in that, A flow detection device is provided at the second check valve, and the flow detection device is electrically connected to the controller; When the flow detection device detects that the flow change of the second check valve is greater than a preset variable value, the controller supplies power to the conductor line; when the flow detection device detects that the flow change of the second check valve is less than the preset variable value, the controller de-energizes the conductor line.

6. The lightweight optical cable for aerospace applications according to claim 5, characterized in that, The flow detection device includes a housing, a rotor, and a Hall switch. The housing has a third cavity, and an inlet and an outlet are respectively provided on opposite sides of the housing, communicating with the third cavity. The inlet is connected to the output end of the second check valve. The rotor is rotatably disposed between the inlet and the outlet, and the rotor includes a magnetic element. The Hall switch is disposed on the outside of the housing. The Hall switch detects the flow change of the second check valve by the change in the magnetic field generated by the rotation of the magnetic element. The Hall switch is electrically connected to the controller.

7. A method for preparing a lightweight optical cable for aerospace applications as described in claim 5 or 6, characterized in that, Includes the following steps: Multiple optical fibers are braided together, and a first protective sleeve is placed on the outside of the braided optical fibers. A second protective sleeve is fitted over the outside of the first protective sleeve, the flow detection device is connected to the controller, and the first check valve and the second check valve are connected to the outlet and inlet of the coolant tank, respectively. A third protective sleeve is fitted over the outside of the second protective sleeve, and the conductor wire in the second cavity is connected to the controller.

8. The method for preparing a lightweight optical cable for aerospace applications according to claim 7, characterized in that, The process of fitting a second protective sleeve over the outside of the first protective sleeve, connecting the flow detection device to the controller, and injecting coolant into the first cavity through the first one-way valve includes: Coolant is injected into the first cavity through the first check valve. After the flow rate measured by the flow detection device stabilizes, the flow rate measured by the flow detection device at this time is set as the reference flow rate of the second check valve. The flow rate change of the second check valve is set to the difference between the real-time flow rate detected by the flow detection device and the reference flow rate; Input a preset variable value and compare the preset variable value with the flow rate change of the second check valve in real time.

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