Light optical cable for aerospace and preparation method thereof

Abstract

The invention 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, and a plurality of optical fibers are coaxially arranged in the first protective sleeve; the second protective sleeve coaxially sleeves the outer side 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 circulation of cooling liquid. According to the light optical cable for aerospace, the first cavity is formed 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 when the optical cable works in the flowing process, so that the temperature of the optical cable is reduced, and the temperature of the optical cable can be effectively adjusted through the cooling liquid; and a good working state is kept in a high-temperature environment.

Description

Technical Field

[0001] The present invention relates to the technical field of cables, and in particular to a lightweight optical cable for aerospace and a preparation method thereof. Background Art

[0002] As a transmission medium, optical fiber has the advantages of being ultra-light, wide bandwidth, anti-electromagnetic interference, good confidentiality, etc. compared with traditional copper cables; with the development of the aviation industry, in recent years, the application research of optical fiber cables in the aerospace field has become increasingly extensive. The optical cable for aerospace is different from ordinary optical fiber cables. Considering its applicability and safety, it is required to be light in weight, thin in wire diameter, high-temperature resistant, and have mechanical and optical stability, high strength, bend resistance, impact resistance, aging resistance, acid and alkali resistance, resistance to various fuels and oils, flame retardancy, low smoke and low toxicity, etc. within a long-term high-temperature range.

[0003] However, the operating temperature of traditional optical cables is between -40°C and +70°C. In fields such as aviation, ships, and wind power generation, the operating environment is harsh. During operation, the high temperature can reach above 125°C, and the low temperature can reach -60°C. When the operating temperature exceeds 70°C or is lower than -40°C, the performance of the optical fiber and the outer sheath material in the optical cable drops sharply, the optical fiber is easily broken, and the outer sheath ages seriously, which cannot ensure the normal operation of the optical cable. Therefore, conventional optical cables cannot meet the application requirements in harsh environments such as aerospace. Summary of the Invention

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a lightweight optical cable for aerospace and a preparation method thereof, so as to solve the technical problem that existing optical cables cannot meet harsh environments such as aerospace.

[0005] To achieve the above purpose, the present invention adopts the following technical solutions: In a first aspect, an embodiment of the present invention provides a lightweight optical cable for aerospace, including: 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 sleeved 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 the coolant to flow through.

[0006] 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 conducts from the outside of the optical cable to the first cavity, and the second one-way valve conducts from the first cavity to the outside of the optical cable.

[0007] As a preferred technical solution of the present application, a metering pump is provided at the first one-way valve, and the output end of the metering pump is communicated with the input end of the first one-way valve.

[0008] As a preferred technical solution of the present application, it further includes a third protective sleeve, the third protective sleeve is coaxially sleeved outside the second protective sleeve, a second cavity is provided in the third protective sleeve, and an electrorheological fluid and a conductor wire are arranged in the second cavity, and the conductor wire is electrically connected to the controller.

[0009] As a preferred technical solution of the present application, the controller is a control system provided for the aircraft to which the optical cable is applied.

[0010] As a preferred technical solution of the present application, the electrorheological fluid includes polymethyl methacrylate microsphere particles, silicone oil, polyethylene glycol and a dyeing agent.

[0011] 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; When the flow detection device detects that the flow change amount of the second one-way valve is greater than a preset variable value, the controller supplies power to the conductor wire; when the flow detection device detects that the flow change amount of the second one-way valve is less than the preset variable value, the controller cuts off the power supply of the conductor wire.

[0012] As a preferred technical solution of the present application, the flow detection device includes a housing, a rotor and a Hall switch. A third cavity is provided in the housing. Liquid inlets and outlets communicating with the third cavity are respectively arranged on opposite sides of the housing, and the liquid inlet communicates with the output end of the second one-way valve; the rotor is rotatably arranged between the liquid inlet and the liquid outlet, and the rotor includes a magnetic member; the Hall switch is arranged outside the housing, and the Hall switch detects the flow change amount 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.

[0013] In a second aspect, an embodiment of the present invention provides a preparation method for a lightweight optical cable for aerospace, including the lightweight optical cable for aerospace as described in the first aspect, and including the following steps: Weave a plurality of optical fibers together and sleeved a first protective sleeve outside the woven plurality of optical fibers; Sleeve a second protective sleeve outside the first protective sleeve, connect the flow detection device to the controller, and connect the first one-way valve and the second one-way valve to the outlet and the inlet of the coolant tank respectively; Sleeve a third protective sleeve outside the second protective sleeve, and connect the conductor wire in the second cavity to the controller.

[0014] As a preferred technical solution of the present application, the step of sleeving a second protective sleeve outside 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 one-way valve. After waiting for the flow rate measured by the flow rate detection device to stabilize, the flow rate measured by the flow rate detection device at this time is set as the reference flow rate of the second one-way valve; The flow rate change of the second one-way valve is set as the difference between the real-time flow rate detected by the flow rate detection device and the reference flow rate; Input the preset variable value, and compare the preset variable value with the flow rate change of the second one-way valve in real time.

[0015] The lightweight optical cable for aerospace of the present invention, by arranging a first cavity inside the optical cable, coolant is injected into the first cavity and flows inside it. During the flow process, the coolant absorbs the heat generated when the optical cable works, thereby reducing the temperature of the optical cable. The temperature of the optical cable can be effectively adjusted through the coolant to ensure that it maintains a good working state in a high-temperature environment.

[0016] The above description is only an overview of the technical solution of the present invention. In order to be able to understand the technical means of the present invention more clearly, it can be implemented according to the content of the specification. And in order to make the above and other purposes, features and advantages of the present invention more obvious and understandable, the following preferred embodiments are specifically described in detail as follows. Brief Description of the Drawings

[0017] Figure 1 It is the first structural schematic diagram of the lightweight optical cable for aerospace of the embodiment of the present invention; Figure 2 It is the second structural schematic diagram of the lightweight optical cable for aerospace of the embodiment of the present invention; Figure 3 It is the external structural schematic diagram of the flow rate detection device of the lightweight optical cable for aerospace of the embodiment of the present invention; Figure 4 It is the exploded view of the flow rate detection device of the lightweight optical cable for aerospace of the embodiment of the present invention; Figure 5 It is the flow chart of the preparation method of the lightweight optical cable for aerospace of the embodiment of the present invention; Figure 6 It is the sub-flow chart of the preparation method of the lightweight optical cable for aerospace of the embodiment of the present invention.

[0018] Description of the Reference Numerals: 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. Conductive wire; 40. Dosing pump; 50. Flow rate detection device; 51. Housing; 511. Liquid inlet; 512. Liquid outlet; 52. Rotor; 53. Hall switch. Detailed Description of the Embodiment

[0019] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0020] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part rather than all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0021] In the description of the present invention, 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", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.

[0022] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more unless otherwise specifically defined.

[0023] In the present invention, unless otherwise clearly defined and limited, the terms "mounted", "connected", "coupled", "fixed", etc. shall be construed in a broad sense. For example, it may be a connection, a detachable connection, or an integral body; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0024] In the present invention, unless otherwise clearly specified or limited, the first feature being "on" or "under" the second feature may include the direct contact between the first and second features, and may also include the situation where the first and second features are not in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over" and "on top of" the second feature includes that the first feature is directly above and obliquely above the second feature, or simply means that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "below" and "beneath" the second feature includes that the first feature is directly below and obliquely below the second feature, or simply means that the horizontal height of the first feature is lower than that of the second feature.

[0025] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms should not be understood as necessarily referring to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0026] In the field of aerospace, optical cables need to face extreme temperature conditions and complex environmental challenges. The operating temperature range of traditional optical cables is usually between -40°C and +70°C. However, in aerospace applications, optical cables may be exposed to a wider temperature range. For example, the high temperature can reach above 125°C, and the low temperature can be as low as -60°C. Under such conditions, the performance of the optical fiber 11 and the outer sheath material in the optical cable will drop sharply, resulting in problems such as easy fracture of the optical fiber 11 and aging of the outer sheath, thus affecting the normal operation of the optical cable. To solve these problems, it has become an urgent task to design an optical cable structure that can maintain stable performance under harsh temperature conditions.

[0027] Please refer to Figures 1 to 2 , Figure 1 which is the first schematic structural diagram of the lightweight optical cable for aerospace in the embodiment of the present invention, Figure 2The second structural schematic diagram of the lightweight optical cable for aerospace according to the embodiment of the present invention. The embodiment of the present invention provides a lightweight optical cable for aerospace, including: a first protective cover 10 and a second protective cover 20, wherein a plurality of optical fibers 11 are coaxially arranged in the first protective cover 10; the second protective cover 20 is coaxially sleeved on the outside of the first protective cover 10, and a first cavity is formed between the second protective cover 20 and the first protective cover 10; the first cavity is used for the circulation of the coolant 12. Specifically, in this embodiment, by setting a first cavity inside the optical cable, the coolant 12 is injected into the first cavity and flows inside the first cavity, and the coolant 12 absorbs the heat generated when the optical cable is working during the flow process, thereby reducing the temperature of the optical cable. The temperature of the optical cable can be effectively adjusted by the coolant 12 to ensure that it maintains a good working condition in a high temperature environment.

[0028] Furthermore, the second protective cover 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 connected from the outside of the aerospace lightweight optical cable to the first cavity, and the second one-way valve 22 is connected from the first cavity to the outside of the aerospace lightweight optical cable.

[0029] It is understandable that in the cooling liquid 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 also may cause the liquid to accumulate in a certain part of the optical cable, causing 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 cooling liquid 12 always flows in a predetermined direction, that is, flows from the outside of the optical cable into the first cavity, and then flows out from the first cavity to the outside of the optical cable, thereby ensuring the efficiency and stability of the heat dissipation process.

[0030] In some embodiments, the aircraft in which the optical cable is used in this embodiment is provided with a cooling water tower, the first one-way valve 21 is connected to the outlet end of the cooling water tower, and the second one-way valve 22 is connected to the inlet end of the cooling water tower. Specifically, the cooling liquid 12 flows into the first cavity from the outside of the optical cable through the first one-way valve 21, and the cooling liquid 12 flowing into the first cavity flows along the cavity, performs heat exchange with the first protective cover 10 of the optical cable, absorbs the heat generated when the optical cable is working, and thus cools the optical cable; the cooling liquid 12 after absorbing the heat flows out of the first cavity through the second one-way valve 22 and returns to the outside of the optical cable, and the outflowing cooling liquid 12 is collected and transported back to the external cooling water tower, and after cooling treatment, is injected into the first cavity again through the first one-way valve 21, and this cycle is repeated to achieve continuous cooling of the optical cable.

[0031] Further, a metering pump 40 is provided at the first one-way valve 21, and the output end of the metering pump 40 communicates with the input end of the first one-way valve 21. Among them, the metering pump 40 is a pump that can accurately control the output liquid flow rate. Through the precise control of the metering pump 40, it can ensure that the flow rate of the coolant 12 is always in a constant state, which not only avoids resource waste and excessive system pressure caused by excessive flow rate, but also prevents poor heat dissipation caused by insufficient flow rate, improving the efficiency and reliability of the entire cooling system.

[0032] In some embodiments, the optical cable further includes a third protective sleeve 30, which is coaxially sleeved outside the second protective sleeve 20. A second cavity is provided in the third protective sleeve 30, and an electrorheological fluid 31 and a conductor wire 32 are arranged in the second cavity. The conductor wire 32 is electrically connected to the controller.

[0033] It should be noted that the optical cables in the aerospace field not only need to cope with high-temperature environments, but may also face various complex working conditions such as mechanical impacts, squeezes, and vibrations. 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 therein, which can provide additional protection and buffering when the optical cable is subjected to external impacts or squeezes, prevent the optical fiber 11 from being damaged, and ensure the stability and reliability of optical signal transmission. Specifically, the electrorheological fluid 31 is a substance whose apparent viscosity or yield stress will change significantly under the action of an electric field. When there is no electric field, the electrorheological fluid 31 has a low viscosity and fluidity; when an electric field is applied, the charge distribution inside it changes, and the interaction between particles is enhanced, resulting in an increase in the viscosity of the electrorheological fluid 31 or the formation of a solid-like structure, thus realizing the transition from a flowing 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 is enabled to have the ability to intelligently respond to changes in the external environment.

[0034] In some embodiments, the controller is a control system provided for the aircraft to which the aerospace lightweight optical cable is applied.

[0035] It should be noted that the aircraft itself is already equipped with a complex control system for managing various functions and parameters during flight. Integrating the control system of the optical cable with the existing control system of the aircraft can avoid setting up a separate set of control equipment for the optical cable, thereby saving space, reducing costs, and reducing energy consumption. At the same time, this integration is also conducive to improving the integration and coordination of the entire aircraft system, facilitating unified management and maintenance.

[0036] In some embodiments, the electrorheological fluid 31 includes polymethyl methacrylate microsphere particles, silicone oil, polyethylene glycol, and a dye. Among them, the polymethyl methacrylate microsphere particles serve as the dispersed phase, which have good dielectric properties and mechanical strength, and can rapidly align under the action of an electric field, causing the electrorheological fluid 31 to quickly undergo a phase change under the action of an electric field, changing from a flowing state to a semi-solid state, thereby enhancing the strength and rigidity of the optical cable and withstanding external impacts or squeezes. The silicone oil serves as the dispersion medium, which has a low dielectric constant, high chemical stability, and good fluidity, and can provide a good dispersion environment for the microsphere particles, enabling them to be evenly dispersed without the action of an electric field and quickly and orderly arranged under the action of an electric field. At the same time, the stability of the silicone oil ensures the stable performance of the electrorheological fluid 31 within a wide temperature range. Polyethylene glycol serves as a surfactant, which can reduce the interfacial tension between the microsphere particles and the silicone oil, improve the dispersion stability of the microsphere particles in the silicone oil, prevent particle agglomeration and sedimentation. In addition, polyethylene glycol can also improve the fluidity and uniformity of the electrorheological fluid 31 and enhance its electrorheological properties. The dye can make the electrorheological fluid 31 have an obvious color. When the optical cable leaks, the leaked electrorheological fluid 31 will show the color of the dye, which is convenient for visually detecting the leakage location. At the same time, the dye should have good compatibility with the silicone oil and does not affect the performance of the electrorheological fluid 31.

[0037] Optionally, the dye can be selected as oil-soluble Sudan Ⅳ. Sudan Ⅳ can dissolve in silicone oil and has a bright red color, which can significantly improve the visibility of the electrorheological fluid 31 and facilitate quick detection in case of leakage. Optionally, the electrorheological fluid 31 further includes a fluorescent whitening agent. The fluorescent whitening agent can absorb ultraviolet light and emit blue or purple light, which combines with the red color of Sudan Ⅳ to produce a brighter and more eye-catching color effect.

[0038] Please refer to Figure 1 and Figure 3 、 Figure 4 , Figure 3 which is a schematic diagram of the external structure of the flow detection device for the lightweight optical cable used in the aerospace application of the embodiments of the present invention, Figure 4 and is an exploded view of the flow detection device for the lightweight optical cable used in the aerospace application of the embodiments 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 amount 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 amount of the second one-way valve 22 is less than the preset variable value, the controller cuts off the power supply to the conductor line 32.

[0039] In this embodiment, the conductor line 32 connects the second cavity to the controller, forming an intelligent control system. The controller monitors in real time the flow rate change information fed back by the flow rate detection device 50. When the flow rate change amount exceeds the preset variable value, the controller determines that the optical cable may be impacted or squeezed, and then sends an instruction to the conductor line 32, causing 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 impact resistance and extrusion resistance of the optical cable.

[0040] In some actual application scenarios, when the optical cable is working normally and not impacted or squeezed, the electrorheological fluid 31 in the second cavity is in a flowing state. At this time, the third protective sleeve 30 provides basic physical protection for the optical cable, while not affecting the flexibility and bendability of the optical cable. When the optical cable is impacted or squeezed externally, it will cause a change in the flow rate of the coolant 12 in the first cavity. The flow rate detection device 50 monitors this change in real time and transmits the signal to the controller. After receiving the signal from the flow rate detection device 50, the controller determines whether the flow rate change amount exceeds the preset variable value. If it exceeds the preset variable value, the controller sends an instruction to the conductor line 32. The conductor line 32 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, the viscosity increases, and it gradually changes from a flowing state to a semi-solid state, significantly improving the strength and rigidity of the optical cable, thereby effectively resisting external impacts or squeezes and protecting the internal optical fiber 11 from damage. When the external impact or squeeze is eliminated, the controller can control the conductor line 32 to be de-energized, the electrorheological fluid 31 loses the action of the electric field, and gradually returns to the flowing state, and the optical cable also returns to the normal working state.

[0041] In some embodiments, the flow rate detection device 50 includes a housing 51, a rotor 52, and a Hall switch 53. A third cavity is provided in the housing 51. 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 communicates with the output end of the second one-way valve 22. The rotor 52 is rotatably provided between the inlet 511 and the outlet 512, and the rotor 52 includes a magnetic member. The Hall switch 53 is provided outside the housing 51. The Hall switch 53 detects the flow rate change amount of the second one-way valve 22 through the magnetic field change generated by the rotation of the magnetic member, and the Hall switch 53 is electrically connected to the controller.

[0042] Specifically, after the coolant 12 flows out from the output end of the second one-way valve 22, it enters the third cavity through the liquid inlet 511 of the flow detection device 50. Under the impact of the coolant 12, the rotor 52 starts to rotate, and the magnetic member on the rotor 52 rotates accordingly. When the rotor 52 rotates, the magnetic field generated by the magnetic member produces a periodic change 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 rotation 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 impacted or squeezed, and then sends an instruction to the conductor line 32 to activate the protection measure. After the conductor line 32 is energized, the electro-rheological fluid 31 undergoes a phase change under the action of an electric field, changing from a flowing state to a semi-solid state, enhancing the strength and rigidity of the optical cable, resisting external impacts or squeezes, and protecting the internal optical fiber 11 from damage.

[0043] The embodiment of the present invention provides a preparation method for a lightweight optical cable for aerospace, including the lightweight optical cable for aerospace as above, as Figure 5 shown, Figure 5 is a flowchart of the preparation method for the lightweight optical cable for aerospace in the embodiment of the present invention, including the following steps S100 - S300: S100. Weave multiple optical fibers together and sleeved a first protective sleeve outside the woven multiple optical fibers; S200. Sleeve a second protective sleeve outside the first protective sleeve, connect the flow detection device to the controller, and connect the first one-way valve and the second one-way valve to the outlet and inlet of the coolant tank respectively; S300. Sleeve a third protective sleeve outside the second protective sleeve and connect the conductor line in the second cavity to the controller.

[0044] Further, as Figure 6 shown, Figure 6 is a sub - flowchart of the preparation method for the lightweight optical cable for aerospace in the embodiment of the present invention. The above step S200 includes S210 - 230: S210. Inject coolant into the first cavity through the first one - way valve. After waiting for the flow rate measured by the flow detection device to be stable, set the flow rate measured by the flow detection device at this time as the reference flow rate of the second one - way valve; S220. Set the flow rate change of the second one - way valve as the difference between the real - time flow rate detected by the flow detection device and the reference flow rate; 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.

[0045] In this embodiment, by comparing the difference between the real-time flow rate and the reference flow rate, that is, the flow rate change amount, with a preset variable value, it is possible to determine whether the optical cable has been impacted or squeezed, etc., resulting in an abnormal change in the flow rate.

[0046] The above only uses embodiments to further illustrate the technical content of the present invention to make it easier for readers to understand, but it does not mean that the implementation manners of the present invention are limited thereto. Any technical extension or re-creation made according to the present invention is protected by the present invention. The protection scope of the present invention is subject to the claims.

Claims

1. A lightweight optical cable for aerospace applications, characterized in that, Including: A first protective sleeve and a second protective sleeve, wherein a plurality of optical fibers are coaxially arranged inside the first protective sleeve; the second protective sleeve is coaxially sleeved 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 the coolant to flow through.

2. The lightweight optical cable for aerospace according to claim 1, characterized in that, 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 conducts from the outside of the optical cable to the first cavity, and the second one-way valve conducts from the first cavity to the outside of the optical cable.

3. The lightweight optical cable for aerospace according to claim 2, characterized in that, A metering pump is arranged at the first one-way valve, and the output end of the metering pump is communicated with the input end of the first one-way valve.

4. The lightweight optical cable for aerospace according to claim 2, wherein It further includes a third protective sleeve, which is coaxially sleeved outside the second protective sleeve. A second cavity is provided inside the third protective sleeve, and an electrorheological fluid and a conductor wire are arranged in the second cavity. The conductor wire is electrically connected to a controller.

5. The lightweight optical cable for aerospace according to claim 4, characterized in that, The controller is a control system provided for the aircraft to which the optical cable is applied.

6. The lightweight optical cable for aerospace according to claim 4, wherein The electrorheological fluid includes polymethyl methacrylate microsphere particles, silicone oil, polyethylene glycol and a coloring agent.

7. The lightweight optical cable for aerospace according to claim 4, characterized in that, A flow detection device is arranged at the second one-way valve, and the flow detection device is electrically connected to the controller; When the flow detection device detects that the flow change amount of the second one-way valve is greater than a preset variable value, the controller supplies power to the conductor wire; when the flow detection device detects that the flow change amount of the second one-way valve is less than the preset variable value, the controller cuts off the power supply to the conductor wire.

8. The lightweight optical cable for aerospace according to claim 7, wherein, The flow detection device includes a housing, a rotor and a Hall switch. A third cavity is provided inside the housing. Liquid inlets and outlets communicating with the third cavity are respectively arranged on opposite sides of the housing. The liquid inlet is communicated with the output end of the second one-way valve; the rotor is rotatably arranged between the liquid inlet and the liquid outlet, and the rotor includes a magnetic member; the Hall switch is arranged outside the housing, and the Hall switch detects the flow change amount of the second one-way valve through the magnetic field change generated by the rotation of the magnetic member. The Hall switch is electrically connected to the controller.

9. A preparation method of a lightweight optical cable for aerospace, characterized in that, Including a lightweight optical cable for aerospace as described in claim 7 or 8, including the following steps: Weave a plurality of optical fibers together, and sleeved a first protective sleeve outside the woven plurality of optical fibers; Sleeve a second protective sleeve outside the first protective sleeve, connect the flow detection device to the controller, and connect the first one-way valve and the second one-way valve to the outlet and inlet of the coolant tank respectively; Sleeve a third protective sleeve outside the second protective sleeve, and connect the conductor wire in the second cavity to the controller.

10. The preparation method of a lightweight optical cable for aerospace according to claim 9, characterized in that, The step of sleeving a second protective sleeve outside 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: Inject coolant into the first cavity through the first one-way valve. After waiting for the flow measured by the flow detection device to stabilize, set the flow measured by the flow detection device at this time as the reference flow of the second one-way valve; Set the flow change amount of the second one-way valve as the difference between the real-time flow detected by the flow detection device and the reference flow; Input the preset variable value and compare the preset variable value with the flow rate change of the second one-way valve in real time.

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