CN113727477A - Space wire heater and preparation method thereof - Google Patents
Space wire heater and preparation method thereof Download PDFInfo
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- CN113727477A CN113727477A CN202110871527.1A CN202110871527A CN113727477A CN 113727477 A CN113727477 A CN 113727477A CN 202110871527 A CN202110871527 A CN 202110871527A CN 113727477 A CN113727477 A CN 113727477A
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- heater
- conductor
- insulating material
- insulating layer
- space
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- 238000002360 preparation method Methods 0.000 title abstract description 5
- 239000004020 conductor Substances 0.000 claims abstract description 73
- 239000011810 insulating material Substances 0.000 claims abstract description 40
- 229910052751 metal Inorganic materials 0.000 claims abstract description 14
- 239000002184 metal Substances 0.000 claims abstract description 14
- 230000005855 radiation Effects 0.000 claims description 24
- 238000004132 cross linking Methods 0.000 claims description 13
- 238000001125 extrusion Methods 0.000 claims description 13
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 9
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 3
- 229910001006 Constantan Inorganic materials 0.000 claims description 3
- VGGSQFUCUMXWEO-UHFFFAOYSA-N Ethene Chemical compound C=C VGGSQFUCUMXWEO-UHFFFAOYSA-N 0.000 claims description 3
- 239000005977 Ethylene Substances 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 229910002091 carbon monoxide Inorganic materials 0.000 claims description 3
- 230000015556 catabolic process Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 claims description 3
- -1 polytetrafluoroethylene Polymers 0.000 claims description 3
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 3
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 3
- 239000003039 volatile agent Substances 0.000 claims description 3
- 239000010410 layer Substances 0.000 description 56
- 238000000034 method Methods 0.000 description 6
- 239000003365 glass fiber Substances 0.000 description 5
- 238000009413 insulation Methods 0.000 description 4
- 239000010935 stainless steel Substances 0.000 description 4
- 229910001220 stainless steel Inorganic materials 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical group O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000002085 irritant Substances 0.000 description 2
- 231100000021 irritant Toxicity 0.000 description 2
- 229910044991 metal oxide Inorganic materials 0.000 description 2
- 150000004706 metal oxides Chemical class 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/40—Heating elements having the shape of rods or tubes
- H05B3/54—Heating elements having the shape of rods or tubes flexible
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/40—Heating elements having the shape of rods or tubes
- H05B3/54—Heating elements having the shape of rods or tubes flexible
- H05B3/56—Heating cables
Landscapes
- Resistance Heating (AREA)
Abstract
The application discloses line heater for space and preparation method thereof, this heater includes: the cable comprises one or more conductors, an insulating layer arranged outside each conductor, and a sheath layer arranged outside the insulating layer of the one or more conductors, wherein each conductor is a single wire-shaped metal conductor, and the outer diameter of the single wire-shaped metal conductor is not more than 0.2 mm. The application solves the technical problems that the outer diameter of the heater is large, the weight is large, and the insulating material cannot meet the requirement of space environment performance outside aerospace in the prior art.
Description
Technical Field
The application relates to the technical field of heater processing, in particular to a space wire heater and a preparation method thereof.
Background
The space environment outside the aerospace is very severe, and the environment temperature of a wire harness product connected with the aerospace equipment is low, so that the wire harness product is easy to crack when working at a low temperature for a long time, and the wire harness is easy to be damaged in insulation, so that an electrical accident is caused, and serious consequences are caused. Therefore, the wire heater is often wound on the outer surface of the wire harness to heat and maintain the wire harness at a certain proper temperature, so that the service life of the wire harness is prolonged.
At present, a common linear heater is a quartz glass fiber armored heater, and consists of a stainless steel thin-wall pipe and a heating wire, wherein the outer diameter of the stainless steel thin-wall pipe is about 2-3mm generally, and metal oxide solid powder is filled between the heating wire and the inner wall of the stainless steel thin-wall pipe; as the quartz glass fiber armored heater is filled with the stainless steel thin-wall tube and the metal oxide, the outer diameter and the weight of the heater are large, and the insulating material can not meet the requirement of space environment performance outside aerospace.
Disclosure of Invention
The technical problem that this application was solved is: aiming at the conditions that the space linear heater in the prior art has large outer diameter and heavy weight and an insulating material cannot meet the requirement of space environment performance outside aerospace, the application provides the space linear heater and the preparation method thereof, and in the scheme provided by the embodiment of the application, on one hand, the heater consisting of a single or a plurality of conductors with the outer diameter of a single filiform metal conductor not more than 0.2mm is adopted, and compared with the glass fiber heater used in the past, the space linear heater has the characteristics of small outer diameter, light weight and the like, so that the outer diameter and the weight of the heater are reduced; on the other hand, the insulating layer and the sheath layer which have the characteristics of high temperature resistance, radiation resistance, vacuum atomic oxygen resistance, small space quality loss and the like are adopted, so that the heater provided by the embodiment of the application has the advantages of certain radiation resistance, high and low temperature resistance, vacuum atomic oxygen resistance, small space quality loss and the like, is suitable for the field of aerospace, and meets the space environment performance requirements outside aerospace.
In a first aspect, an embodiment of the present application provides a space wire heater, including: the cable comprises one or more conductors, an insulating layer arranged outside each conductor, and a sheath layer arranged outside the insulating layer of the one or more conductors, wherein each conductor is a single wire-shaped metal conductor, and the outer diameter of the single wire-shaped metal conductor is not more than 0.2 mm.
In one possible implementation, the single wire-shaped metal conductor has a tensile strength not less than 390N/mm2And the elongation at break is not less than 12%.
In one possible implementation, the single wire-like metallic conductor material is an alloy constantan.
In a possible implementation manner, the insulating layer and the sheath layer are both formed by extruding an insulating material by high-temperature extrusion equipment and performing radiation crosslinking through an electronic heater.
In one possible implementation, the insulating material is ethylene polytetrafluoroethylene.
In one possible implementation, the insulating layer and the sheath layer both satisfy the following criteria:
the tensile strength is more than 34.5 MPa; the elongation is more than 75 percent; the density range is (1.5 g/cm)3，1.9g/cm3) (ii) a Flexural modulus not greater than 870 MPa; the breakdown voltage is not less than 70 KV/mm; a dielectric constant of 1.75; dielectric loss 0.009.
In one possible implementation, the insulating layer and the sheath layer are resistant to temperatures in the range (-100 ℃, +200 ℃).
In one possible implementation, the total radiation-resistant dose of the insulating layer and the sheath layer is not more than 5 × 108rad；
The heater has a denudation rate of not more than 5 x 10 under irradiation of atomic oxygen having an energy of 5eV-29m3/AO；
The total mass loss of the heater is no greater than 1% and the condensable volatiles are no greater than 0.1%.
In a possible realization mode, under the conditions of normal atmospheric environment, 101.325kPa, 50 ℃ and 72 hours, the odor grade of the irritant and special odor gas discharged by the insulating layer and the sheathing layer is not more than 1.5 grade; the carbon monoxide is removed by no more than 25 ug/g; the total organic matters removed is not more than 100 mu g/g.
In a second aspect, embodiments of the present application provide a method for manufacturing a space wire heater, the method including:
extruding an insulating material by high-temperature extrusion equipment, attaching the insulating material to each conductor, and performing radiation crosslinking on the insulating material outside each conductor by using an electronic heater to obtain an insulating layer;
extruding an insulating material by high-temperature extrusion equipment, attaching the insulating material to the insulating layers of one or more conductors, and performing radiation crosslinking on the insulating material outside each conductor by an electronic heater to obtain a sheath layer so as to obtain the space wire heater.
Compared with the prior art, the scheme provided by the embodiment of the application has at least the following beneficial effects:
1. in the scheme provided by the embodiment of the application, the heater formed by the single or multiple conductors with the outer diameter of the single wire-shaped metal conductor not larger than 0.2mm is adopted, and compared with the conventional glass fiber heater, the heater has the characteristics of small outer diameter, light weight and the like, so that the outer diameter and the weight of the heater are reduced.
2. In the scheme provided by the embodiment of the application, the insulating layer and the sheath layer which have the characteristics of high temperature resistance, radiation resistance, vacuum atomic oxygen resistance, small space quality loss and the like are adopted, so that the heater provided by the embodiment of the application has the advantages of certain radiation resistance, high and low temperature resistance, vacuum atomic oxygen resistance, small space quality loss and the like, is suitable for the field of aerospace, and meets the requirement of space environment performance outside aerospace.
Drawings
FIG. 1 is a schematic view of a space wire heater according to an embodiment of the present disclosure;
fig. 2A is a three-dimensional schematic view of a space wire heater according to an embodiment of the present disclosure;
FIG. 2B is a top view of a space wire heater according to an embodiment of the present disclosure;
fig. 3A is a three-dimensional schematic view of a space wire heater according to an embodiment of the present disclosure;
FIG. 3B is a top view of a space wire heater according to an embodiment of the present disclosure;
FIG. 4 is a schematic flow chart illustrating a method for manufacturing a space wire heater according to an embodiment of the present disclosure;
fig. 5 is a flow chart illustrating a process of manufacturing a space wire heater according to an embodiment of the present invention.
Detailed Description
In the solutions provided in the embodiments of the present application, the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
Referring to fig. 1, a schematic diagram of a space line heater according to an embodiment of the present disclosure is shown. In fig. 1, the heater includes: the cable comprises one or more conductors 1, an insulating layer 2 arranged outside each conductor 1, and a sheath layer 3 arranged outside the insulating layer 2 of the one or more conductors, wherein each conductor 1 is a single filiform metal conductor, and the outer diameter of the single filiform metal conductor is not more than 0.2 mm.
Specifically, in the solution provided in the embodiment of the present application, the space wire heater may include a conductor 1; a plurality of conductors 1 may also be included, for example, the heater may include 2 conductors, 3 conductors, or N conductors, N being a positive integer not less than 3. The above two cases will be described separately below for ease of understanding.
A space wire heater comprises a conductor
Referring to fig. 2A and 2B, fig. 2A is a three-dimensional schematic view of a space line heater according to an embodiment of the present disclosure; fig. 2B is a top view of a space wire heater according to an embodiment of the present disclosure. In fig. 2A and 2B, the space line heater includes one conductor 1, an insulating layer 2, and a sheath layer 3, which are sequentially disposed, wherein the insulating layer 2 is disposed on the one conductor 1, and the sheath layer 3 is disposed on the insulating layer 2.
Second, the space line heater comprises a plurality of conductors
Referring to fig. 3A and 3B, fig. 3A is a three-dimensional schematic view of a space line heater according to an embodiment of the present disclosure; fig. 3B is a top view of a space wire heater according to an embodiment of the present disclosure. In fig. 3A and 3B, the space line heater includes 2 conductors 1 arranged in parallel, an insulating layer 2 is disposed outside each conductor 1, and a sheath layer 3 is disposed outside the insulating layer 2 of two conductors 1 arranged in parallel, that is, the sheath layer 3 is wrapped around the two conductors 1.
Further, in order to reduce the outer diameter and weight of the heater, in the solution provided in the embodiments of the present application, each conductor in the heater is a very thin wire-shaped metal conductor. By way of example, the very thin wire conductor has an outer diameter of not more than 0.2 mm.
Further, in the solution provided in the embodiment of the present application, the conductor in the heater is a high-strength conductor. By way of example, in one possible implementation, the tensile strength of a single wire conductor is not less than 390N/mm2And the elongation at break is not less than 12%.
Further, in the solution provided in the embodiments of the present application, there are various materials of the single wire-shaped metal conductor that satisfy the above conditions. By way of example, in one possible implementation, the single wire-like metallic conductor material is an alloy constantan.
Further, in the solution provided in the embodiment of the present application, in order to improve the space compactness of the heater, in a possible implementation manner, the insulating layer and the sheath layer are both formed by extruding an insulating material by using a high-temperature extrusion device and performing radiation crosslinking through an electronic heater.
Specifically, the flexible high-temperature radiation-resistant insulating material is extruded on high-temperature extrusion equipment (such as a high-temperature plastic extruding machine) by selecting a proper extruding pipe type mould, and is subjected to radiation crosslinking by an electron accelerator to prepare the flexible high-temperature radiation-resistant insulating material.
Further, in the solution provided in the examples of the present application, there are various insulating materials for preparing the insulating layer and the sheathing layer, for example, the insulating material is an aerospace insulating material. By way of example, the insulating material is ethylene polytetrafluoroethylene.
Further, the insulating material is extruded by the high-temperature extrusion equipment, and the insulating layer and the sheath layer which are formed by radiation crosslinking of the electronic heater meet the following indexes:
the tensile strength is more than 34.5 MPa; the elongation is more than 75 percent; secret keyThe degree range is (1.5 g/cm)3，1.9g/cm3) (ii) a Flexural modulus not greater than 870 MPa; the breakdown voltage is not less than 70 KV/mm; a dielectric constant of 1.75; dielectric loss 0.009.
Further, in a possible implementation, the temperature resistance range of the insulating layer and the sheath layer is (-100 ℃, +200 ℃).
Further, in a possible implementation scheme, the total radiation-resistant dose of the insulating layer and the sheath layer is not more than 5 x 108rad；
The heater has a denudation rate of not more than 5 x 10 under irradiation of atomic oxygen having an energy of 5eV-29m3/AO；
The total mass loss of the heater is no greater than 1% and the condensable volatiles are no greater than 0.1%.
Further, in a possible implementation scheme, under the conditions of normal atmospheric environment, 101.325kPa, 50 ℃ and 72 hours, the odor grade of irritant and special odor gas discharged by the insulating layer and the sheath layer is not more than 1.5 grade; the carbon monoxide is removed by no more than 25 ug/g; the total organic matters removed is not more than 100 mu g/g.
In the scheme provided by the embodiment of the application, the heater formed by the single or multiple conductors with the outer diameter of the single wire-shaped metal conductor not larger than 0.2mm is adopted, and compared with the conventional glass fiber heater, the heater has the characteristics of small outer diameter, light weight and the like, so that the outer diameter and the weight of the heater are reduced.
Further, in the scheme provided by the embodiment of the application, the insulating layer and the sheath layer which have the characteristics of high temperature resistance, radiation resistance, vacuum atomic oxygen resistance, small space quality loss and the like are adopted, so that the heater provided by the embodiment of the application has the advantages of certain radiation resistance, high and low temperature resistance, vacuum atomic oxygen resistance, small space quality loss and the like, is suitable for the field of aerospace, and meets the requirement of space environment performance outside aerospace.
Referring to fig. 4, a method for manufacturing a space wire heater according to an embodiment of the present application includes:
step 401, extruding an insulating material through a high-temperature extrusion device, attaching the insulating material to each conductor, and performing radiation crosslinking on the insulating material outside each conductor through an electronic heater to obtain an insulating layer.
And 402, extruding an insulating material through high-temperature extrusion equipment, attaching the insulating material to the insulating layers of one or more conductors, and performing radiation crosslinking on the insulating material outside each conductor through an electronic heater to obtain a sheath layer so as to obtain the space wire heater.
Specifically, in the scheme provided by the embodiment of the application, the insulating material is extruded by a high-temperature extrusion device and is attached to the outer surface of each conductor. By way of example, a single layer of insulating material (inner layer insulation) may be attached to the outer surface of each conductor, or a double layer of insulating material (inner layer insulation and outer layer insulation) may be attached. Carrying out radiation crosslinking on the insulating material outside each conductor by using an electronic heater to obtain an insulating layer; then set up the restrictive coating outside the insulating layer of one or more conductors that arrange side by side, specifically, extrude insulating material through high temperature extrusion equipment, attach this insulating material on the insulating layer of one or more conductors, carry out the radiation crosslinking through electronic heater to the insulating material outside every conductor and obtain the restrictive coating, and then obtain space line heater. Fig. 5 is a flow chart of a process of a space wire heater according to an embodiment of the present disclosure.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A space wire heater, comprising: the cable comprises one or more conductors, an insulating layer arranged outside each conductor, and a sheath layer arranged outside the insulating layer of the one or more conductors, wherein each conductor is a single wire-shaped metal conductor, and the outer diameter of the single wire-shaped metal conductor is not more than 0.2 mm.
2. The heater of claim 1, wherein said single wire conductor has a tensile strength of no less than 390N/mm2And the elongation at break is not less than 12%.
3. The heater of claim 2, wherein said single wire conductor material is an alloy constantan.
4. The heater of any one of claims 1 to 3, wherein the insulating layer and the sheath layer are formed by extruding an insulating material by high-temperature extrusion equipment and performing radiation crosslinking through an electronic heater.
5. A heater as claimed in any of claims 1 to 3 wherein said insulating material is ethylene polytetrafluoroethylene.
6. The heater of claim 5, wherein the insulating layer and the jacket layer each meet the following criteria:
the tensile strength is more than 34.5 MPa; the elongation is more than 75 percent; the density range is (1.5 g/cm)3，1.9g/cm3) (ii) a Flexural modulus not greater than 870 MPa; the breakdown voltage is not less than 70 KV/mm; a dielectric constant of 1.75; dielectric loss 0.009.
7. A heater as claimed in any one of claims 1 to 3, wherein the heater is resistant to temperatures in the range (-100 ℃ and +200 ℃).
8. The heater of claim 7, wherein the heater has a total radiation dose resistance of no more than 5 x 108rad；
The heater has a denudation rate of not more than 5 x 10 under irradiation of atomic oxygen having an energy of 5eV-29m3/AO；
The total mass loss of the heater is no greater than 1% and the condensable volatiles are no greater than 0.1%.
9. The heater of claim 8, wherein the odor level of the pungent and special odor gases emitted by the heater is no greater than 1.5 under normal atmospheric conditions, at 101.325kPa, 50 ℃, 72 hours; the carbon monoxide is removed by no more than 25 ug/g; the total organic matters removed is not more than 100 mu g/g.
10. A method of making a space wire heater comprising:
extruding an insulating material by high-temperature extrusion equipment, attaching the insulating material to each conductor, and performing radiation crosslinking on the insulating material outside each conductor by using an electronic heater to obtain an insulating layer;
extruding an insulating material by high-temperature extrusion equipment, attaching the insulating material to the insulating layers of one or more conductors, and performing radiation crosslinking on the insulating material outside each conductor by an electronic heater to obtain a sheath layer so as to obtain the space wire heater.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110871527.1A CN113727477A (en) | 2021-07-30 | 2021-07-30 | Space wire heater and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110871527.1A CN113727477A (en) | 2021-07-30 | 2021-07-30 | Space wire heater and preparation method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN113727477A true CN113727477A (en) | 2021-11-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110871527.1A Pending CN113727477A (en) | 2021-07-30 | 2021-07-30 | Space wire heater and preparation method thereof |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111556599A (en) * | 2020-05-12 | 2020-08-18 | 北京宏宇航天技术有限公司 | Pipeline heating belt for spacecraft and manufacturing method thereof |
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2021
- 2021-07-30 CN CN202110871527.1A patent/CN113727477A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111556599A (en) * | 2020-05-12 | 2020-08-18 | 北京宏宇航天技术有限公司 | Pipeline heating belt for spacecraft and manufacturing method thereof |
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