CN111243789B - High-temperature-resistant aerospace cable and preparation method thereof - Google Patents

High-temperature-resistant aerospace cable and preparation method thereof Download PDF

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CN111243789B
CN111243789B CN202010090101.8A CN202010090101A CN111243789B CN 111243789 B CN111243789 B CN 111243789B CN 202010090101 A CN202010090101 A CN 202010090101A CN 111243789 B CN111243789 B CN 111243789B
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cable
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CN111243789A (en
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曾智
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Guoyou Cable Group Henan Co ltd
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Guoyou Cable Group Co Ltd
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
    • H01B7/00—Insulated conductors or cables characterised by their form
    • H01B7/17—Protection against damage caused by external factors, e.g. sheaths or armouring
    • H01B7/29—Protection against damage caused by extremes of temperature or by flame
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
    • H01B13/00—Apparatus or processes specially adapted for manufacturing conductors or cables
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
    • H01B13/00—Apparatus or processes specially adapted for manufacturing conductors or cables
    • H01B13/22—Sheathing; Armouring; Screening; Applying other protective layers
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
    • H01B7/00—Insulated conductors or cables characterised by their form
    • H01B7/17—Protection against damage caused by external factors, e.g. sheaths or armouring
    • H01B7/29—Protection against damage caused by extremes of temperature or by flame
    • H01B7/292—Protection against damage caused by extremes of temperature or by flame using material resistant to heat
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    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
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    • C08K3/20—Oxides; Hydroxides
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    • C08K2003/2231—Oxides; Hydroxides of metals of tin
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    • C08L2203/00—Applications
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Abstract

The invention discloses a high-temperature-resistant aerospace cable and a preparation method thereof, and relates to the technical field of cables, wherein the cable comprises a high-temperature-resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core; the cable core comprises a core material formed by twisting a plurality of wires and a polyimide lapping covering the outside of the core material, and nano inorganic particles with certain mass fraction are added in the polyimide lapping covering; the composite heat insulation layer wrapping bag comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, and glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders.

Description

High-temperature-resistant aerospace cable and preparation method thereof
Technical Field
The invention relates to the technical field of cables, in particular to a high-temperature-resistant aerospace cable and a preparation method thereof.
Background
The wire and cable is used for transmitting electric (magnetic) energy, information and wire products for realizing electromagnetic energy conversion. A wire cable in a broad sense, also referred to as a cable for short, refers to an insulated cable, which can be defined as: an aggregate consisting of; one or more insulated wire cores, and a coating layer, a total protective layer and an outer protective layer which may be respectively arranged on the insulated wire cores, the cable also can be provided with an additional uninsulated conductor, and the wire and the cable are used as a main carrier of power transmission and are widely applied to the aspects of electric equipment, lighting circuits, household appliances and the like, and the quality of the wire and the cable directly influences the engineering quality and the personal and property safety. At present, the types of electric wires and cables are various, and proper electric wires and cables are adopted according to the needs of the users.
In aerospace operation, because many electronic devices are used, all parts need to be connected through cables. Due to the particularity of the working environment, the working temperature of the cable has a large fluctuation range and is easily influenced by high temperature, and if the cable cannot tolerate the high temperature, a fire disaster is possibly caused, so that great economic loss and personal injury are caused.
The existing aerospace cable is often accelerated to age at high temperature, so that the insulation, heat insulation and tensile resistance are reduced to different degrees, the use is influenced, and how to provide a high-temperature-resistant aerospace cable becomes a current research hotspot.
Chinese patent CN105845238A discloses a tensile low-temperature-resistant silver-copper composite conductor aerospace cable, which comprises a plurality of strands of insulated wire cores and an outer sheath coated outside the insulated wire cores; each insulated wire core is formed by extruding a silicon rubber insulating layer outside a conductor, the insulated wire cores and a glass fiber rope are twisted together to form a cable core, and the cable core is sequentially coated with a shielding layer, a flame-retardant layer, an inner sheath and a reticular nylon layer from inside to outside; the conductor consists of a silver-copper alloy conductor and a soft copper bundle, and the soft copper bundle is wrapped outside the silver-copper alloy conductor. The cable has reliable signal transmission, strong anti-interference capability, good conductivity, wear resistance and fusion welding resistance, can ensure the normal operation of aerospace equipment in a special environment, improves the safety of the aerospace equipment, has excellent heat resistance, cold resistance, dielectric property, ozone resistance, atmospheric aging resistance and other properties, can be used for a long time at the temperature of minus 60 ℃ to 250 ℃, wherein a silver-copper alloy conductor consists of copper, silver and graphene, but the graphene as an inorganic component is poor in compatibility with metals such as copper, silver and the like without modification treatment, can generate crystallization and even cracks at low temperature, and is not beneficial to use.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a high-temperature-resistant aerospace cable and a preparation method thereof.
In order to achieve the purpose, the invention adopts the following technical scheme:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of wires and a polyimide wrapping the core material, wherein the polyimide wrapping is added with nano inorganic particles with a certain mass fraction, and the current more mature wire materials applied in the aerospace field comprise tinned copper wires, silvered copper wires, nickel-plated copper wires, silvered copper alloy wires and nickel-plated copper alloy wires, and the nickel-plated copper alloy wires are preferably selected in consideration of the cost performance;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant sheath layer comprises the following components in parts by weight:
40-50 parts of nitrile rubber, 20-26 parts of methyl vinyl phenyl silicone rubber, 8-12 parts of acrylonitrile-butadiene-styrene copolymer, 30-40 parts of precipitated white carbon black, 780.1-0.5 part of easy colloidal element T, 5-10 parts of zinc borate monohydrate, 15-20 parts of tin oxide, 2-5 parts of hydroxyl silicone oil, 3-6 parts of sepiolite, 1-2 parts of titanate coupling agent, 1-2 parts of microcrystalline paraffin and 3-5 parts of stearic acid.
Further, the nano inorganic particles are made of TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The particles are mixed according to a certain weight ratio.
Further, TiO2Particles and Al2O3The weight ratio of the particles is 3-6: 1.
further, the addition amount of the nano inorganic particles in the polyimide lapping is 20.5-21.3% of the mass of the polyimide.
Further, the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
5-10 parts of metakaolin base polymer, 2-8 parts of activated alumina, 1-3 parts of tabular corundum, 2-3 parts of silica micropowder, 4-6 parts of magnesium oxide, 0.1-1 part of calcium aluminate cement, 0.1-0.2 part of fiber expanding agent, 0.4-0.8 part of alkali activator and 15-20 parts of sodium silicate.
Further, the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
5.5 parts of metakaolin base polymer, 4 parts of activated alumina, 3 parts of tabular corundum, 2.2 parts of silica micropowder, 4 parts of magnesium oxide, 0.3 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.5 part of alkali activator and 18 parts of sodium silicate.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
(1) stranding the lead to prepare a core material;
(2) performing polyimide lapping by using a lapping machine to obtain cable cores, twisting a plurality of cable cores, performing composite thermal insulation layer lapping by using the lapping machine, and winding a glass fiber braided layer on the cable cores to obtain cable blanks;
(3) the cable blank is drawn by a motor to enter a sintering furnace for sintering, the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the first area, the second area, the third area and the fourth area are respectively 10-15m, 20-40m and 5-10m, and the temperatures are respectively 200-minus-one-year-over-;
(4) and finally, compounding the high-temperature-resistant sheath layer to the surface of the sintered cable blank through hot pressing.
Further, the wrapping machine in the step (2) is a vertical wrapping machine or a horizontal wrapping machine, when the vertical wrapping machine is adopted, the wrapping included angle is 40-65 degrees, and when the horizontal wrapping machine is adopted, the wrapping included angle is 15-30 degrees.
Further, when sintering is carried out in the step (3), the drawing speed of the cable blank is 1-1.5 m/min.
Compared with the prior art, the invention has the beneficial effects that:
the aerospace cable adopts the structure of the inner protective layer and the outer protective layer, the inner protective layer is wrapped by polyimide added with nano inorganic particles, compared with pure polyimide wrapping, chemical bond connection exists between polyimide molecular chains and inorganic particle networks, the thermal stability of the polyimide wrapping is obviously improved along with the increase of the content of nano inorganic particles, mainly because nano inorganic particles form continuous and complete inorganic three-dimensional networks in the polyimide organic network, the two networks mutually penetrate by taking the nano inorganic particles as crosslinking points to form an organic-inorganic interpenetrating network, the formation of the interpenetrating network effectively limits the heated motion of polyimide molecular chain segments, improves the high temperature resistance, the outer protective layer adopts the structure of a high temperature resistant sheath layer, a glass fiber woven layer and a composite heat insulation layer wrapping, and can further improve the heat insulation and insulation performance, the cable not only can improve the tensile and lateral pressure resistance, but also can transmit part of heat to a region with lower temperature when the cable is locally heated, so as to play a role in reducing the temperature and improve the local heat resistance of the cable.
Drawings
FIG. 1 is a block diagram of an aerospace cable according to the invention.
The reference numbers in the figures represent respectively:
1-core material, 2-polyimide lapping, 3-composite heat insulation layer lapping, 4-glass fiber weaving layer and 5-high temperature resistant sheath layer.
FIG. 2 is a flow chart of the preparation method of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Example 1:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide lapping covering the outside of the core material, wherein 20.5 mass percent of nano inorganic particles are added in the polyimide lapping, and the nano inorganic particles are formed by TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 5: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
5.5 parts of metakaolin base polymer, 4 parts of activated alumina, 3 parts of tabular corundum, 2.2 parts of silica micropowder, 4 parts of magnesium oxide, 0.3 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.5 part of alkali activator and 18 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
42 parts of nitrile rubber, 25 parts of methyl vinyl phenyl silicone rubber, 9 parts of acrylonitrile-butadiene-styrene copolymer, 30 parts of precipitated white carbon black, T780.2 parts of colloidal element, 6 parts of zinc borate monohydrate, 18 parts of tin oxide, 4 parts of hydroxyl silicone oil, 5 parts of sepiolite, 1 part of titanate coupling agent, 2 parts of microcrystalline wax and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
the manufacturing method comprises the steps of stranding wires to prepare a core material, carrying out polyimide wrapping by using a vertical wrapping machine to obtain a cable core, stranding a plurality of cable cores, carrying out composite heat insulation layer wrapping by using the vertical wrapping machine, wherein wrapping included angles are 45 degrees, winding a glass fiber braided layer on the cable core to obtain a cable blank, leading the cable blank to enter a sintering furnace for sintering at the speed of 1.2m/min through motor traction, wherein the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the sintering furnace are respectively 15m, 25m, 30m and 10m, the temperatures of the sintering furnace are respectively 210 ℃, 300 ℃, 380 ℃ and 180 ℃, and finally compounding a high-temperature-resistant sheath layer on the surface of the sintered cable blank through hot pressing.
Example 2:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide lapping covering the outside of the core material, wherein 21% of nano inorganic particles with mass fraction are added in the polyimide lapping covering, and the nano inorganic particles are formed by TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 3: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
6 parts of metakaolin base polymer, 4 parts of activated alumina, 1 part of tabular corundum, 2 parts of silica micropowder, 5 parts of magnesium oxide, 0.3 part of calcium aluminate cement, 0.1 part of fiber expanding agent, 0.5 part of alkali activator and 18 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
50 parts of nitrile rubber, 25 parts of methyl vinyl phenyl silicone rubber, 10 parts of acrylonitrile-butadiene-styrene copolymer, 30 parts of precipitated white carbon black, 780.1 parts of colloidal element T, 5 parts of zinc borate monohydrate, 18 parts of tin oxide, 5 parts of hydroxyl silicone oil, 5 parts of sepiolite, 1 part of titanate coupling agent, 1 part of microcrystalline wax and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
stranding the lead to prepare a core material; the method comprises the steps of utilizing a vertical wrapping machine to carry out polyimide wrapping to obtain cable cores, wherein the wrapping included angle is 45 degrees, twisting a plurality of cable cores, utilizing a horizontal wrapping machine to carry out composite heat insulation layer wrapping, the wrapping included angle is 15 degrees, then winding a glass fiber braided layer on the glass fiber braided layer to obtain a cable blank, enabling the cable blank to enter a sintering furnace for sintering at the speed of 1.5m/min through motor traction, wherein the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the sintering furnace are respectively 10m, 40m, 30m and 10m, the temperatures of the sintering furnace are respectively 220 ℃, 280 ℃, 360 ℃ and 200 ℃, and finally compounding a high-temperature-resistant sheath layer on the surfaces of the sintered cable blanks through hot pressing.
Example 3:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide lapping covering the outside of the core material, wherein 20.5 mass percent of nano inorganic particles are added in the polyimide lapping, and the nano inorganic particles are formed by TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 3: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
8 parts of metakaolin base polymer, 4 parts of activated alumina, 1 part of tabular corundum, 3 parts of silica micropowder, 5 parts of magnesium oxide, 0.1 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.6 part of alkali activator and 20 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
45 parts of nitrile rubber, 20 parts of methyl vinyl phenyl silicone rubber, 12 parts of acrylonitrile-butadiene-styrene copolymer, 30 parts of precipitated white carbon black, 780.1 parts of colloidal element T, 10 parts of zinc borate monohydrate, 16 parts of tin oxide, 5 parts of hydroxyl silicone oil, 3 parts of sepiolite, 1 part of titanate coupling agent, 1.2 parts of microcrystalline paraffin and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
the manufacturing method comprises the steps of stranding wires to prepare a core material, carrying out polyimide lapping by using a vertical lapping machine to obtain cable cores with a lapping included angle of 65 degrees, stranding a plurality of cable cores, carrying out composite heat insulation layer lapping by using the lapping machine with a lapping included angle of 30 degrees, winding a glass fiber braided layer on the cable cores to obtain cable blanks, enabling the cable blanks to enter a sintering furnace for sintering at the speed of 1m/min through motor traction, wherein the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the first area, the second area, the third area and the fourth area are 12m, 30m, 40m and 5m respectively, the temperatures of the first area, the second area, the third area and the fourth area are 200 ℃, 280 ℃, 380 ℃ and 160 ℃, and finally compounding a high-temperature resistant.
Example 4:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide lapping covering the outside of the core material, wherein 21.3 mass percent of nano inorganic particles are added in the polyimide lapping, and the nano inorganic particles are formed by TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 6: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
5 parts of metakaolin base polymer, 6 parts of activated alumina, 3 parts of tabular corundum, 2 parts of silica micropowder, 5 parts of magnesium oxide, 0.2 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.5 part of alkali activator and 18 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
50 parts of nitrile rubber, 24 parts of methyl vinyl phenyl silicone rubber, 10 parts of acrylonitrile-butadiene-styrene copolymer, 30 parts of precipitated white carbon black, T780.2 parts of colloidal element, 10 parts of zinc borate monohydrate, 16 parts of tin oxide, 5 parts of hydroxy silicone oil, 3 parts of sepiolite, 1.2 parts of titanate coupling agent, 2 parts of microcrystalline wax and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
stranding the lead to prepare a core material; polyimide is wrapped by a vertical wrapping machine to obtain cable cores, the wrapping included angle is 65 degrees, a plurality of cable cores are twisted, then a horizontal wrapping machine is used for wrapping a composite heat insulation layer, the wrapping included angle is 30 degrees, and then a glass fiber woven layer is wound on the glass fiber woven layer to obtain a cable blank; the cable blank is led by a motor to enter a sintering furnace for sintering at the speed of 1m/min, and the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the first area, the second area, the third area and the fourth area are respectively 15m, 20m and 10m, and the temperatures are respectively 200 ℃, 280 ℃, 380 ℃ and 200 ℃; and finally, compounding the high-temperature-resistant sheath layer to the surface of the sintered cable blank through hot pressing.
Example 5:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide lapping covering the outside of the core material, wherein 20.8 mass percent of nano inorganic particles are added in the polyimide lapping, and the nano inorganic particles are formed by TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 6: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
10 parts of metakaolin-based geopolymer, 3 parts of activated alumina, 2 parts of tabular corundum, 2 parts of silica micropowder, 5 parts of magnesium oxide, 0.3 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.6 part of alkali activator and 20 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
50 parts of nitrile rubber, 24 parts of methyl vinyl phenyl silicone rubber, 12 parts of acrylonitrile-butadiene-styrene copolymer, 35 parts of precipitated white carbon black, 780.5 parts of colloidal element T, 8 parts of zinc borate monohydrate, 18 parts of tin oxide, 2 parts of hydroxyl silicone oil, 6 parts of sepiolite, 1 part of titanate coupling agent, 1.5 parts of microcrystalline paraffin and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
the manufacturing method comprises the steps of stranding wires to prepare a core material, carrying out polyimide lapping by using a vertical lapping machine to obtain a cable core, wherein a lapping included angle is 45 degrees, stranding a plurality of cable cores, then carrying out composite heat insulation layer lapping by using a horizontal lapping machine, wherein the lapping included angle is 30 degrees, then winding a glass fiber braided layer on the cable core to obtain a cable blank, putting the cable blank into a sintering furnace for sintering at the speed of 1.5m/min by motor traction, wherein the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the sintering furnace are respectively 15m, 30m and 10m, the temperatures are respectively 210 ℃, 300 ℃, 380 ℃ and 180 ℃, and finally compounding a high-temperature-resistant sheath layer on the surface of the sintered cable blank by hot pressing.
Example 6:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide wrapping the core material, wherein 20.5% of nano inorganic particles with mass fraction are added in the polyimide wrapping, and the nano inorganic particlesThe inorganic particles are made of TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 5: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
10 parts of metakaolin base polymer, 4 parts of activated alumina, 2 parts of tabular corundum, 2.5 parts of silica micropowder, 5 parts of magnesium oxide, 0.2 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.6 part of alkali activator and 18 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
50 parts of nitrile rubber, 22 parts of methyl vinyl phenyl silicone rubber, 10 parts of acrylonitrile-butadiene-styrene copolymer, 40 parts of precipitated white carbon black, 780.1 parts of colloidal element T, 8 parts of zinc borate monohydrate, 16 parts of tin oxide, 5 parts of hydroxyl silicone oil, 3 parts of sepiolite, 2 parts of titanate coupling agent, 1 part of microcrystalline wax and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
stranding the lead to prepare a core material; polyimide is wrapped by a horizontal wrapping machine to obtain cable cores, the wrapping included angle is 15 degrees, after a plurality of cable cores are twisted, a composite heat insulation layer is wrapped by the horizontal wrapping machine, the wrapping included angle is 15 degrees, and then a glass fiber woven layer is wound on the glass fiber woven layer to obtain a cable blank; the cable blank is led by a motor to enter a sintering furnace for sintering at the speed of 1.4m/min, the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the sintering furnace are 12m, 40m and 10m respectively, and the temperatures are 220 ℃, 280 ℃, 380 ℃ and 160 ℃; and finally, compounding the high-temperature-resistant sheath layer to the surface of the sintered cable blank through hot pressing.
Example 7:
a high-temperature resistant aerospace cable comprises a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of nickel-plated copper alloy wires and a polyimide lapping covering the outside of the core material, wherein 21.3 mass percent of nano inorganic particles are added in the polyimide lapping, and the nano inorganic particles are formed by TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The weight ratio of the particles is 6: 1, mixing;
the composite heat insulation wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat insulation wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant inorganic binder comprises the following components in parts by weight:
10 parts of metakaolin base polymer, 8 parts of activated alumina, 3 parts of tabular corundum, 3 parts of silica micropowder, 6 parts of magnesium oxide, 1 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.8 part of alkali activator and 20 parts of sodium silicate.
The high-temperature-resistant sheath layer comprises the following components in parts by weight:
50 parts of nitrile rubber, 26 parts of methyl vinyl phenyl silicone rubber, 12 parts of acrylonitrile-butadiene-styrene copolymer, 40 parts of precipitated white carbon black, 780.5 parts of colloidal element T, 10 parts of zinc borate monohydrate, 20 parts of tin oxide, 5 parts of hydroxyl silicone oil, 6 parts of sepiolite, 2 parts of titanate coupling agent, 2 parts of microcrystalline paraffin and 5 parts of stearic acid.
The preparation method of the high-temperature resistant aerospace cable comprises the following steps:
stranding wires into a core material, performing polyimide lapping by using a vertical lapping machine to obtain a cable core with a lapping included angle of 65 degrees, stranding a plurality of cable cores, performing composite heat insulation layer lapping by using the vertical lapping machine with a lapping included angle of 40 degrees, winding a glass fiber braided layer on the cable core to obtain a cable blank, and sintering the cable blank in a sintering furnace by motor traction at a speed of 1.5m/min, wherein the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the sintering furnace are respectively 15m, 40m and 10m, and the temperatures are respectively 220 ℃, 300 ℃, 380 ℃ and 200 ℃; and finally, compounding the high-temperature-resistant sheath layer to the surface of the sintered cable blank through hot pressing.
And (3) performance testing:
the aerospace cables in embodiments 1, 2, and 3 of the present invention were subjected to performance testing, and the test results and related data are shown in table 1 below:
table 1:
Figure BDA0002383403010000151
as can be seen from table 1 above, the aerospace cable of the present invention has excellent performance, extremely high normal temperature insulation resistance and high temperature insulation resistance, and good electrical performance, and not only meets the performance requirements of all aerospace cables, but also considers various environmental conditions that may exist in the application process, and in addition, the aerospace cable of embodiments 4, 5, 6, and 7 of the present invention also meets the performance requirements.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (6)

1. A high-temperature resistant aerospace cable is characterized by comprising a high-temperature resistant sheath layer, a glass fiber woven layer, a composite thermal insulation layer wrapping and a cable core;
the cable core comprises a core material formed by twisting a plurality of wires and a polyimide lapping covering the outside of the core material, wherein nano inorganic particles with certain mass fraction are added in the polyimide lapping;
the nano inorganic particles are made of TiO with the particle size of 10-20nm2Particles and Al having a particle size of 50 to 100nm2O3The particles are mixed according to a certain weight ratio;
TiO2particles and Al2O3The weight ratio of the particles is 3-6: 1;
the composite heat-insulating layer wrapping comprises a synthetic mica paper substrate, wherein iron oxide red silica gel tapes are adhered to two surfaces of the synthetic mica paper substrate through high-temperature-resistant inorganic binders, glass paper is adhered to the outer sides of the iron oxide red silica gel tapes through the high-temperature-resistant inorganic binders, and the composite heat-insulating layer wrapping lasts for more than or equal to 30min at the high temperature of 1000 ℃;
the high-temperature-resistant sheath layer comprises the following components in parts by weight:
40-50 parts of nitrile rubber, 20-26 parts of methyl vinyl phenyl silicone rubber, 8-12 parts of acrylonitrile-butadiene-styrene copolymer, 30-40 parts of precipitated white carbon black, 780.1-0.5 part of easy colloidal element T, 5-10 parts of zinc borate monohydrate, 15-20 parts of tin oxide, 2-5 parts of hydroxyl silicone oil, 3-6 parts of sepiolite, 1-2 parts of titanate coupling agent, 1-2 parts of microcrystalline paraffin and 3-5 parts of stearic acid;
the preparation method of the high-temperature resistant aerospace cable comprises the following steps:
(1) stranding the lead to prepare a core material;
(2) performing polyimide lapping by using a lapping machine to obtain cable cores, twisting a plurality of cable cores, performing composite thermal insulation layer lapping by using the lapping machine, and winding a glass fiber braided layer on the glass fiber braided layer to obtain a cable blank;
(3) the cable blank is drawn by a motor to enter a sintering furnace for sintering, the sintering furnace is divided into a first area, a second area, a third area and a fourth area, the lengths of the first area, the second area, the third area and the fourth area are respectively 10-15m, 20-40m and 5-10m, and the temperatures are respectively 200-minus-one-year-over-;
(4) and finally, compounding the high-temperature-resistant sheath layer to the surface of the sintered cable blank through hot pressing.
2. The high temperature resistant aerospace cable of claim 1, wherein the nano inorganic particles in the polyimide lapping are added in an amount of 20.5-21.3% by mass of the polyimide.
3. The high-temperature resistant aerospace cable of claim 1, wherein the high-temperature resistant inorganic binder comprises the following components in parts by weight:
5-10 parts of metakaolin base polymer, 2-8 parts of activated alumina, 1-3 parts of tabular corundum, 2-3 parts of silica micropowder, 4-6 parts of magnesium oxide, 0.1-1 part of calcium aluminate cement, 0.1-0.2 part of fiber expanding agent, 0.4-0.8 part of alkali activator and 15-20 parts of sodium silicate.
4. The high-temperature resistant aerospace cable of claim 3, wherein the high-temperature resistant inorganic binder comprises the following components in parts by weight:
5.5 parts of metakaolin base polymer, 4 parts of activated alumina, 3 parts of tabular corundum, 2.2 parts of silica micropowder, 4 parts of magnesium oxide, 0.3 part of calcium aluminate cement, 0.2 part of fiber expanding agent, 0.5 part of alkali activator and 18 parts of sodium silicate.
5. The method for preparing the high-temperature-resistant aerospace cable according to claim 1, wherein the lapping machine in the step (2) is a vertical lapping machine or a horizontal lapping machine, and the lapping included angle is 40-65 degrees when the vertical lapping machine is adopted and 15-30 degrees when the horizontal lapping machine is adopted.
6. The method for preparing a high temperature resistant aerospace cable according to claim 1, wherein the pulling speed of the cable blank during sintering in step (3) is 1-1.5 m/min.
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Publication number Priority date Publication date Assignee Title
CN103154139A (en) * 2010-09-29 2013-06-12 纳幕尔杜邦公司 Polyimide resins for high temperature applications
CN104812113A (en) * 2015-05-12 2015-07-29 青岛海越机电科技有限公司 High temperature-resistant induction heating cable
CN205282157U (en) * 2015-11-16 2016-06-01 安徽光复电缆有限公司 Regional high temperature fire resisting cable that uses of aeroengine

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Publication number Priority date Publication date Assignee Title
US8176943B2 (en) * 2008-11-21 2012-05-15 Parker-Hannifin Corporation High temperature fire sleeve

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103154139A (en) * 2010-09-29 2013-06-12 纳幕尔杜邦公司 Polyimide resins for high temperature applications
CN104812113A (en) * 2015-05-12 2015-07-29 青岛海越机电科技有限公司 High temperature-resistant induction heating cable
CN205282157U (en) * 2015-11-16 2016-06-01 安徽光复电缆有限公司 Regional high temperature fire resisting cable that uses of aeroengine

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