Composite cable for aerospace and preparation method thereof

Abstract

The invention belongs to the technical field of cables, and discloses a composite cable for aerospace and a preparation method thereof. The composite cable for aerospace sequentially comprises a conductor, an insulating layer, a shielding layer and an outer sheath layer from inside to outside, the shielding layer sequentially comprises a lead-tin alloy composite braid layer and a metal foil wrapping layer from inside to outside, the lead-tin alloy composite braid layer contains nano bismuth oxide, and the nano bismuth oxide accounts for 3-5% of the mass of the lead-tin alloy composite braid layer; the outer sheath layer comprises the following raw materials: polyether-ether-ketone, polyphenylene sulfide, microencapsulated siloxane, nano titanium dioxide and carbon nanotubes, and the microencapsulated siloxane accounts for 3-5% of the outer sheath layer in percentage by mass. The composite cable for aerospace has excellent aging resistance and embrittlement resistance in a cosmic ray environment, is not easy to crack at an extreme temperature (-150 DEG C to 300 DEG C), and effectively resists cosmic rays and electromagnetic interference; and in addition, the light weight characteristic is realized.

Description

Technical Field

[0001] This invention belongs to the field of cable technology, and specifically relates to a composite cable for aerospace applications and its preparation method. Background Technology

[0002] Aerospace cables connect various electrical, communication, and control systems, transmitting power, control signals, and data. Aerospace cables are continuously evolving towards higher strength, flexibility, resistance to high and low temperatures, oxidation resistance, and corrosion resistance, demanding higher performance and reliability. Furthermore, with the development of the aerospace industry, higher requirements are being placed on the functionality, safety, and service life of the cables used.

[0003] Traditional aerospace cables have the following shortcomings during use: 1. They are prone to aging and embrittlement when exposed to cosmic rays (high-energy particles, ultraviolet rays) for a long time; 2. They are prone to cracking due to mismatch in the thermal expansion coefficient of the insulation layer at extreme temperatures (-150℃ to 300℃); 3. They have insufficient electromagnetic shielding performance and are susceptible to electromagnetic interference (EMI) from space.

[0004] Therefore, how to improve the anti-aging performance, high and low temperature resistance, and electromagnetic shielding performance of cables is a technical problem that urgently needs to be solved in this field. Summary of the Invention

[0005] This invention aims to solve at least one of the technical problems existing in the prior art. Therefore, the object of this invention is to provide a composite cable for aerospace applications and its manufacturing method. The aerospace composite cable of this invention exhibits excellent anti-aging and anti-embrittlement capabilities under cosmic ray environments, is not prone to cracking at extreme temperatures (-150℃ to 300℃), and can effectively resist cosmic rays and electromagnetic interference; in addition, it is lightweight, meeting the weight reduction requirements of aerospace applications.

[0006] In a first aspect, the present invention provides a composite cable for aerospace applications, comprising, from the inside out, a conductor, an insulation layer, a shielding layer, and an outer sheath layer; the shielding layer comprises, from the inside out, a lead-tin alloy composite braided layer and a metal foil wrapping layer, wherein nano-bismuth oxide is distributed in the lead-tin alloy composite braided layer, and the nano-bismuth oxide accounts for 3-5% of the mass percentage of the lead-tin alloy composite braided layer; the raw materials of the outer sheath layer include polyetheretherketone, polyphenylene sulfide, microencapsulated siloxane, nano-titanium dioxide, and carbon nanotubes, wherein the microencapsulated siloxane accounts for 3-5% of the mass percentage of the outer sheath layer.

[0007] In some embodiments of the present invention, the conductor is formed by multiple strands of a nickel-plated copper-silver alloy. The multi-strand stranded structure of the conductor improves high-temperature conductivity (temperature resistance ≥400℃), increases flexibility, and reduces the skin effect. Preferably, the number of strands is 7×7 (49 strands in total). This 49-strand stranding allows the conductor's outer diameter to be controlled within 1.2-1.5 mm, meeting the requirements for lightweight and flexibility, and reducing skin effect losses by approximately 12%.

[0008] In some embodiments of the present invention, the silver content in the copper-silver alloy is 0.05-0.2% by mass.

[0009] In some embodiments of the present invention, the thickness of the nickel plating layer obtained by nickel plating is 5-10 μm.

[0010] In some embodiments of the present invention, the insulating layer comprises an inner insulating layer and an outer insulating layer; the raw materials of the inner insulating layer include inorganic nanofillers and polyimide; the raw materials of the outer insulating layer include fluorinated ethylene propylene copolymer or polytetrafluoroethylene. The inner insulating layer is an inorganic nanofiller-doped polyimide (PI) film, which has the characteristics of high temperature resistance and low dielectric loss; the outer insulating layer is coated with fluorinated ethylene propylene copolymer (FEP) or polytetrafluoroethylene, which can resist ultraviolet rays and chemical corrosion.

[0011] In some embodiments of the present invention, the inorganic nanofiller includes nano-ceramic powder and / or nano-alumina. By adding high-temperature resistant nanofillers such as nano-ceramic powder and / or nano-alumina, the high-temperature resistance is improved.

[0012] In some embodiments of the present invention, the inorganic nanofiller accounts for 2-8% of the mass percentage of the polyimide. This mass percentage can be any point value or any two points within the range of 2-8%, such as 2%, 3%, 4%, 5%, 6%, 7%, 8%, etc.; preferably 4-6%. Controlling the appropriate amount allows the temperature resistance of the PI film to be increased from 260°C to above 320°C.

[0013] In some embodiments of the present invention, the thickness of the outer insulating layer is 0.15-0.5 mm, which allows the ultraviolet transmittance to be ≤0.5%, meeting the radiation resistance requirements of the space environment.

[0014] In some embodiments of the present invention, the braiding density of the lead-tin alloy composite braided layer is 82-88%.

[0015] In some embodiments of the present invention, the overlap rate of the metal foil wrapping layer is 45-55%. The present invention, through the lead-tin alloy composite braided layer and the metal foil wrapping layer, can form a double shielding effect, effectively shielding high-energy particles and electromagnetic interference; by controlling the appropriate braiding density and overlap rate, the shielding efficiency against 1MeV gamma rays can be ≥90%.

[0016] In some embodiments of the present invention, the lead-tin alloy used in the lead-tin alloy braided layer has a tin content of 8-12%.

[0017] In some embodiments of the present invention, the particle size of the nano-bismuth oxide is ≤50 nm; preferably 10-50 nm. Adding nano-bismuth oxide can enhance the absorption capacity for γ-rays and neutrons, and controlling the appropriate particle size can increase the neutron absorption cross-section by more than 20%.

[0018] In some embodiments of the present invention, the metal foil used for the metal foil wrapping layer includes aluminum foil or copper foil.

[0019] In some embodiments of the present invention, the mass ratio of polyetheretherketone (PEEK) to polyphenylene sulfide (PPS) is 7:(1-5). The outer sheath layer uses a blend of polyetheretherketone (PEEK) and polyphenylene sulfide (PPS) as the base material, and the appropriate mass ratio is controlled to achieve a temperature resistance of over 300°C and a tensile strength ≥120 MPa. Furthermore, microencapsulated siloxanes are embedded in the outer sheath layer. When microcracks develop in the outer sheath layer due to radiation, the capsules rupture and release a repair agent, achieving in-situ repair. Nano-titanium dioxide (TiO2) and carbon nanotubes (CNTs) are also added to the outer sheath layer to synergistically enhance its resistance to ultraviolet aging.

[0020] In some embodiments of the present invention, the nano-titanium dioxide accounts for 0.1-0.3% of the mass of the outer sheath layer.

[0021] In some embodiments of the present invention, the carbon nanotubes account for 0.1-0.3% of the mass of the outer sheath layer.

[0022] In some embodiments of the present invention, the outer surface of the outer sheath layer is provided with a silicon carbide nano-coating. The silicon carbide (SiC) nano-coating reflects ultraviolet light and reduces surface charge accumulation.

[0023] In some embodiments of the present invention, the thickness of the silicon carbide nanocoating is 1-5 μm. Controlling the appropriate thickness can reduce the surface charge accumulation rate by more than 80%.

[0024] A second aspect of the present invention provides a method for preparing the aerospace composite cable described in the first aspect of the present invention, comprising the following steps: An insulating layer is extruded around the outer periphery of the conductor; A shielding layer is wrapped around the outer periphery of the insulating layer; An outer sheath layer is extruded around the outer periphery of the shielding layer and cross-linked by irradiation to obtain the aerospace composite cable.

[0025] In some embodiments of the present invention, the extrusion speed ratio of the extruded insulating layer to the extruded outer sheath layer is 1:(1.1-1.3).

[0026] In some embodiments of the present invention, the pressure at the extruder die head is 15-20 MPa. The present invention ensures interlayer adhesion strength ≥5 N / mm by controlling appropriate extrusion speed and pressure, reducing interface defects and interlayer bubbles, with an interlayer bubble rate ≤0.3%.

[0027] In some embodiments of the present invention, the radiation crosslinking is performed using an electron beam radiation crosslinking process, which crosslinks the material of the outer sheath layer by electron beam irradiation, thereby improving the temperature resistance and mechanical strength.

[0028] In some embodiments of the present invention, the radiation dose of the electron beam radiation crosslinking process is 140-160 kGy. Controlling an appropriate radiation dose can enable the crosslinking degree of the PEEK / PPS blend to reach 65%-70%, improve the temperature resistance to above 350°C, and maintain the elongation at break ≥80%.

[0029] In some embodiments of the present invention, the preparation process of the lead-tin alloy composite braided layer is as follows: Nano-bismuth oxide is mixed with conventional adhesives in the art and ultrasonically treated to uniformly disperse the nano-bismuth oxide in the adhesive, thus obtaining a composite adhesive. Lead-tin alloy wires are braided around the outer periphery of the insulating layer to obtain a lead-tin alloy braided layer. The composite adhesive is applied to the surface of the lead-tin alloy braided layer, and after curing, the lead-tin alloy composite braided layer is obtained.

[0030] A third aspect of the present invention provides the application of the aerospace composite cable described in the first aspect of the present invention, or the aerospace composite cable prepared by the preparation method described in the second aspect of the present invention, in aerospace applications.

[0031] Compared with the prior art, the beneficial effects of the present invention are as follows: Composite shielding system: The shielding layer of this invention achieves full-band radiation protection through the combined action of a lead-tin alloy composite braided layer, a metal foil wrapping layer, and nano-bismuth oxide, effectively resisting cosmic rays and electromagnetic interference, and improving the reliability of the cable in extreme environments.

[0032] Self-repair mechanism: This invention enables in-situ repair of microcracks in the cable when they occur in a radiation environment by adding microencapsulated siloxane to the outer sheath layer, thus extending the cable's service life.

[0033] Excellent temperature resistance: Through the rational selection and synergistic effect of the materials in each layer, this invention enables the cable to operate stably in an extreme temperature range of -150℃ to 300℃, and the insulation layer is not prone to cracking.

[0034] UV aging resistance: This invention improves the cable’s UV aging resistance by adding nano-titanium dioxide and carbon nanotubes to the outer sheath layer, reducing the aging problem caused by long-term exposure to ultraviolet light. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the aerospace composite cable of the present invention.

[0036] Reference numerals: 100-Conductor; 200-Insulating layer; 201-Inner insulating layer; 202-Outer insulating layer; 300-Shielding layer; 400-Outer sheath layer; 500-Silicon carbide nano-coating. Detailed Implementation

[0037] The present invention will be further described in detail below through specific embodiments. Unless otherwise specified, the raw materials, reagents, or apparatus used in the embodiments can be obtained from conventional commercial sources or by existing technical methods. Unless otherwise specified, the experimental or testing methods are conventional methods in the art.

[0038] The nano-alumina used in the following examples was purchased from Evonik, Germany, and is designated Aeroxide® Alu C.

[0039] The microencapsulated siloxane uses commercially available self-healing microcapsule products, provided by 3M, which are polymer microcapsules with siloxane as the core material.

[0040] Example 1: Composite Cable for Aerospace Applications and its Preparation Reference Figure 1 A composite cable for aerospace applications, comprising, from the inside out, a conductor 100, an insulation layer 200, a shielding layer 300, an outer sheath layer 400, and a silicon carbide nano-coating 500; the insulation layer 200 includes an inner insulation layer 201 and an outer insulation layer 202.

[0041] Conductor: It is made of a copper-silver alloy with nickel plating on the surface, which is stranded in multiple strands; wherein, the silver content of the copper-silver alloy is 0.1% by mass, the thickness of the nickel plating layer is, and the number of strands is 7×7 (49 strands in total).

[0042] The inner insulating layer in the insulating layer is made of nano-alumina-doped polyimide film with a nano-alumina doping mass percentage of 5%.

[0043] The outer insulation layer in the insulation layer is made of fluorinated ethylene propylene copolymer with a coating thickness of 0.15 mm.

[0044] The shielding layer consists of a lead-tin alloy composite braided layer and an aluminum foil wrapping layer, from the inside out. The lead-tin alloy composite braided layer has a tin content of 10% by mass, a braiding density of 85%, and an aluminum foil wrapping overlap rate of 50%. The lead-tin alloy composite braided layer contains nano-bismuth oxide, which accounts for 4% of the mass of the lead-tin alloy composite braided layer.

[0045] Outer sheath layer: The base material is a blend of polyetheretherketone and polyphenylene sulfide in a mass ratio of 7:3. Microencapsulated siloxane, nano titanium dioxide and carbon nanotubes are added to the base material. The microencapsulated siloxane accounts for 4% of the mass of the outer sheath layer, and the nano titanium dioxide and carbon nanotubes each account for 0.25% of the mass of the outer sheath layer.

[0046] The manufacturing method of aerospace composite cables includes the following steps: An insulating layer is extruded around the outer periphery of the conductor; Nano-bismuth oxide is mixed with conventional adhesives in the art and ultrasonically treated to uniformly disperse the nano-bismuth oxide in the adhesive, thus obtaining a composite adhesive. Lead-tin alloy wires are braided around the outer periphery of the insulating layer to obtain a lead-tin alloy braided layer. The composite adhesive is coated onto the surface of the lead-tin alloy braided layer, and after curing, the lead-tin alloy composite braided layer is obtained. Aluminum foil is wrapped around the outer periphery of the lead-tin alloy composite braided layer to obtain an aluminum foil wrapping layer; An outer sheath is extruded around the outer periphery of the aluminum foil wrapping layer and cross-linked by electron beam irradiation (radiation dose of 150 kGy). A silicon carbide nano-coating (2 μm thick) was prepared by coating the outer periphery of the outer sheath layer to obtain a composite cable for aerospace applications.

[0047] In the above preparation method, the extrusion speed ratio of the extrusion insulation layer to the extrusion speed of the extrusion outer sheath layer is 1:1.2; the pressure of the extruder head is 18MPa.

[0048] Example 2: Composite Cable for Aerospace Applications and its Preparation A composite cable for aerospace applications comprises, from the inside out, a conductor, an insulation layer, a shielding layer, an outer sheath layer, and a silicon carbide nano-coating; the insulation layer includes an inner insulation layer and an outer insulation layer.

[0049] Conductor: It is made of a copper-silver alloy with nickel plating on the surface, which is stranded in multiple strands; wherein, the silver content of the copper-silver alloy is 0.1% by mass, the thickness of the nickel plating layer is, and the number of strands is 7×7 (49 strands in total).

[0050] The inner insulating layer in the insulating layer is made of nano-alumina-doped polyimide film with a nano-alumina doping mass percentage of 2%.

[0051] The outer insulation layer in the insulation layer is made of fluorinated ethylene propylene copolymer with a coating thickness of 0.3 mm.

[0052] The shielding layer consists of a lead-tin alloy composite braided layer and an aluminum foil wrapping layer, from the inside out. The lead-tin alloy composite braided layer has a tin content of 10% by mass, a braiding density of 82%, and an aluminum foil wrapping overlap rate of 45%. The lead-tin alloy composite braided layer contains nano-bismuth oxide, which accounts for 3% of the mass of the lead-tin alloy composite braided layer.

[0053] Outer sheath layer: The base material is a blend of polyetheretherketone and polyphenylene sulfide in a mass ratio of 7:1. Microencapsulated siloxane, nano titanium dioxide and carbon nanotubes are added to the base material. The mass percentage of microencapsulated siloxane in the outer sheath layer is 3%, and the mass percentage of nano titanium dioxide and carbon nanotubes in the outer sheath layer is 0.1% each.

[0054] The preparation method of the aerospace composite cable in this embodiment is the same as that in Embodiment 1, except that: the thickness of the silicon carbide nano-coating is adjusted to 1 μm, the ratio of the extrusion speed of the insulation layer to the extrusion speed of the outer sheath layer is adjusted to 1:1.1, and the pressure of the extruder head is adjusted to 15 MPa.

[0055] Example 3: Composite Cable for Aerospace Applications and its Preparation A composite cable for aerospace applications comprises, from the inside out, a conductor, an insulation layer, a shielding layer, an outer sheath layer, and a silicon carbide nano-coating; the insulation layer includes an inner insulation layer and an outer insulation layer.

[0056] Conductor: It is made of a copper-silver alloy with nickel plating on the surface, which is stranded in multiple strands; wherein, the silver content of the copper-silver alloy is 0.1% by mass, the thickness of the nickel plating layer is, and the number of strands is 7×7 (49 strands in total).

[0057] The inner insulating layer in the insulating layer is made of nano-alumina-doped polyimide film with a nano-alumina doping mass percentage of 8%.

[0058] The outer insulation layer in the insulation layer is made of fluorinated ethylene propylene copolymer with a coating thickness of 0.5 mm.

[0059] The shielding layer consists of a lead-tin alloy composite braided layer and an aluminum foil wrapping layer, from the inside out. The lead-tin alloy composite braided layer has a tin content of 10% by mass, a braiding density of 88%, and an aluminum foil wrapping overlap rate of 55%. The lead-tin alloy composite braided layer contains nano-bismuth oxide, which accounts for 5% of the mass of the lead-tin alloy composite braided layer.

[0060] Outer sheath layer: The base material is a blend of polyetheretherketone and polyphenylene sulfide in a mass ratio of 7:5. Microencapsulated siloxane, nano titanium dioxide and carbon nanotubes are added to the base material. The mass percentage of microencapsulated siloxane in the outer sheath layer is 5%, and the mass percentage of nano titanium dioxide and carbon nanotubes in the outer sheath layer is 0.3% each.

[0061] The preparation method of the aerospace composite cable in this embodiment is the same as that in Embodiment 1, except that: the thickness of the silicon carbide nano-coating is adjusted to 5μm, the ratio of the extrusion speed of the insulation layer to the extrusion speed of the outer sheath layer is adjusted to 1:1.3, and the pressure of the extruder head is adjusted to 20MPa.

[0062] Comparative Example 1 The only difference from Example 1 is that the mass percentage of nano-bismuth oxide in the lead-tin alloy composite braided layer is adjusted from 4% to 2%.

[0063] Comparative Example 2 The only difference from Example 2 is that the mass percentage of microencapsulated siloxane in the outer sheath layer is adjusted from 4% to 6%.

[0064] Performance testing of aerospace composite cable prepared in Example 1 (1) Radiation resistance test Radiation dose: 500 kGy (gamma rays); Test results: Insulation resistance retention rate was 92%, and mechanical property (tensile strength) retention rate was 88%.

[0065] Reference basis: According to NASA standards, deep space exploration cables must withstand ≥500kGy of radiation and have an insulation resistance retention rate of ≥90% to be considered qualified (NASA-STD-6001D).

[0066] (2) Temperature resistance test Temperature range: -150℃ to 300℃, 100 cycles; Test results: The insulation layer showed no cracks, and the conductivity changed by ±2%.

[0067] Reference basis: ISO 18797:2015 stipulates that aerospace cables have a temperature resistance cycle of ≥100 cycles and a conductivity change rate of ≤±5%.

[0068] (3) Electromagnetic shielding performance test Frequency range: 10MHz to 10GHz; Shielding effectiveness: 85dB.

[0069] Reference basis: GJB151B-2013 requires that the shielding effectiveness of spacecraft cables in the 10MHz-10GHz frequency band be ≥80dB. The aerospace composite cable prepared by this invention exceeds the standard by 5dB.

[0070] (4) Self-healing performance test Microcrack repair time: 24 hours; Strength recovery rate after repair: 95%.

[0071] Reference basis: According to the International Association of Self-Healing Materials (SAMPE 2020) standard, a strength recovery rate of ≥90% after repair by polymer-based materials is considered excellent.

[0072] The performance of the aerospace composite cables prepared in Examples 2 and 3 is similar to that in Example 1, with no significant difference.

[0073] The performance of the aerospace composite cables prepared in Comparative Example 1 and Comparative Example 2 were tested using the same test methods and standards as in Example 1.

[0074] Performance test results of aerospace composite cables prepared in Comparative Example 1 (1) Radiation resistance: After being irradiated with 500 kGy of γ rays, the insulation resistance retention rate was 75% (significantly lower than 92% in Example 1), and the mechanical property (tensile strength) retention rate was 68% (significantly lower than 88% in Example 1).

[0075] (2) Electromagnetic shielding effectiveness: In the 10MHz-10GHz frequency band, the shielding effectiveness is 78dB (lower than 85dB in Example 1).

[0076] Cause analysis: Insufficient content of nano-bismuth oxide in Comparative Example 1 leads to a decrease in the absorption capacity of gamma rays and neutrons, exacerbates radiation damage, and reduces the overall density of the shielding layer.

[0077] Performance test results of aerospace composite cables prepared in Comparative Example 2 (1) Self-healing performance: The microcrack repair time was 36 hours (significantly higher than 24 hours in Example 1), and the strength recovery rate after repair was 80% (significantly lower than 95% in Example 1).

[0078] (2) Mechanical properties: In the non-radiated state, the tensile strength of the outer sheath is 105 MPa (120 MPa in Example 1) and the elongation at break is 25% (35% in Example 1).

[0079] (3) Temperature resistance cycle test: After 100 cycles, micro-cracks appeared in the outer sheath layer, and the change rate of conductivity was ±4.5% (±2% in Example 1).

[0080] Cause analysis: Excessive addition of microencapsulated siloxane can disrupt the continuity of the PEEK / PPS matrix, reduce the mechanical properties of the material itself, and cause bubbles to form after the excessive repair agent is released, affecting the interlayer bonding force.

[0081] The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the embodiments described. Those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present invention, and these equivalent modifications or substitutions are all included within the scope defined by the claims of this application.

Claims

1. A composite cable for aerospace applications, characterized in that, From the inside out, the structure comprises a conductor, an insulating layer, a shielding layer, and an outer sheath layer. The shielding layer, from the inside out, comprises a lead-tin alloy composite braided layer and a metal foil wrapping layer. The lead-tin alloy composite braided layer contains nano-bismuth oxide, and the nano-bismuth oxide accounts for 3-5% of the mass of the lead-tin alloy composite braided layer. The outer sheath layer is made of polyetheretherketone, polyphenylene sulfide, microencapsulated siloxane, nano-titanium dioxide, and carbon nanotubes. The microencapsulated siloxane accounts for 3-5% of the mass of the outer sheath layer.

2. The aerospace composite cable according to claim 1, characterized in that, The insulating layer includes an inner insulating layer and an outer insulating layer; the raw materials of the inner insulating layer include inorganic nanofillers and polyimide; the raw materials of the outer insulating layer include fluorinated ethylene propylene copolymer or polytetrafluoroethylene.

3. The aerospace composite cable according to claim 2, characterized in that, The inorganic nanofiller comprises nano-ceramic powder and / or nano-alumina; the inorganic nanofiller accounts for 2-8% of the mass of the polyimide.

4. The aerospace composite cable according to claim 1, characterized in that, The braiding density of the lead-tin alloy composite braided layer is 82-88%; and / or, the overlap rate of the metal foil wrapping layer is 45-55%.

5. The aerospace composite cable according to claim 1, characterized in that, The particle size of the nano-bismuth oxide is ≤50nm.

6. The aerospace composite cable according to claim 1, characterized in that, The mass ratio of polyetheretherketone to polyphenylene sulfide is 7:(1-5).

7. The aerospace composite cable according to claim 1, characterized in that, The outer surface of the outer sheath layer is provided with a silicon carbide nano-coating.

8. The method for preparing the aerospace composite cable according to any one of claims 1-7, characterized in that, Includes the following steps: An insulating layer is extruded around the outer periphery of the conductor; A shielding layer is wrapped around the outer periphery of the insulating layer; An outer sheath layer is extruded around the outer periphery of the shielding layer and cross-linked by irradiation to obtain the aerospace composite cable.

9. The preparation method according to claim 8, characterized in that, The ratio of the extrusion speed of the extruded insulation layer to the extrusion speed of the extruded outer sheath layer is 1:(1.1-1.3).

10. The aerospace composite cable according to any one of claims 1-7, or the aerospace composite cable prepared by the preparation method according to claim 8, in aerospace applications.

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