CN115474301A - Heating assembly of metal hearth for spaceflight - Google Patents
Heating assembly of metal hearth for spaceflight Download PDFInfo
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- CN115474301A CN115474301A CN202211073064.5A CN202211073064A CN115474301A CN 115474301 A CN115474301 A CN 115474301A CN 202211073064 A CN202211073064 A CN 202211073064A CN 115474301 A CN115474301 A CN 115474301A
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- 238000010438 heat treatment Methods 0.000 title claims abstract description 116
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 77
- 239000002184 metal Substances 0.000 title claims abstract description 77
- 239000000835 fiber Substances 0.000 claims abstract description 64
- -1 iron-chromium-aluminum Chemical compound 0.000 claims abstract description 40
- 239000004642 Polyimide Substances 0.000 claims abstract description 17
- 229920001721 polyimide Polymers 0.000 claims abstract description 17
- 239000004744 fabric Substances 0.000 claims abstract description 13
- 238000004804 winding Methods 0.000 claims abstract description 12
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 21
- 239000000919 ceramic Substances 0.000 claims description 21
- 239000010453 quartz Substances 0.000 claims description 21
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 21
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims description 14
- 239000002390 adhesive tape Substances 0.000 claims description 9
- 229910052697 platinum Inorganic materials 0.000 claims description 7
- 230000001681 protective effect Effects 0.000 claims description 7
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 6
- 238000005245 sintering Methods 0.000 claims description 4
- 238000004321 preservation Methods 0.000 claims description 3
- QRRWWGNBSQSBAM-UHFFFAOYSA-N alumane;chromium Chemical compound [AlH3].[Cr] QRRWWGNBSQSBAM-UHFFFAOYSA-N 0.000 claims description 2
- 238000009413 insulation Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 238000010248 power generation Methods 0.000 description 7
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 238000005498 polishing Methods 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 238000009529 body temperature measurement Methods 0.000 description 2
- 238000005219 brazing Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 230000005486 microgravity Effects 0.000 description 2
- 238000002203 pretreatment Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- QQHSIRTYSFLSRM-UHFFFAOYSA-N alumanylidynechromium Chemical compound [Al].[Cr] QQHSIRTYSFLSRM-UHFFFAOYSA-N 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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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
- H05B3/62—Heating elements specially adapted for furnaces
- H05B3/64—Heating elements specially adapted for furnaces using ribbon, rod, or wire heater
-
- 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
- H05B1/00—Details of electric heating devices
- H05B1/02—Automatic switching arrangements specially adapted to apparatus ; Control of heating devices
- H05B1/0227—Applications
-
- 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
- H05B3/02—Details
-
- 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
- H05B3/02—Details
- H05B3/06—Heater elements structurally combined with coupling elements or holders
-
- 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
- H05B3/10—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor
- H05B3/12—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
Landscapes
- Furnace Housings, Linings, Walls, And Ceilings (AREA)
Abstract
The invention relates to a heating assembly of a metal hearth for spaceflight. The heating assembly of the metal hearth for spaceflight comprises: the heating layer, the insulating sleeve layer and the polyimide rubberized fabric layer are sequentially arranged on the outer surface of the metal hearth from inside to outside and formed by spirally winding an iron-chromium-aluminum heating wire. According to the invention, the high-temperature-resistant insulating fiber sleeve is used for winding the heating wire, and then the heating wire is fastened by using the metal half, so that the heating assembly meets the requirements of mechanical impact, safety and reliability, long service life and the like of space launching.
Description
Technical Field
The invention relates to a heating assembly of a metal hearth for spaceflight, belonging to the technical field of high-temperature heating.
Background
In recent years, with the development of space exploration, spacecrafts fly farther and farther, and the time for living in space is longer and longer, which puts higher requirements on the power supply of the space. Currently, a space vehicle can be provided with sustainable electric power through solar cells, however, when the vehicle is far away from the sun, the energy density of solar energy is lower and lower, and even sufficient energy can not be provided. Solar radiation, 1374W/m near the earth 2 Reduced to 50W/m near Jupiter 2 Only 1W/m near the meditation 2 . Therefore, in deep space exploration far from the sun, the solar energy cannot provide enough power, and a new sustainable energy source must be searched for to provide enough power for the aircraft.
Atomic energy is a very promising long-life energy source and is expected to play an important role in deep space exploration. The heat generated by the nuclear reaction drives a power generation system to generate power so as to provide power for the aerospace craft, and the nuclear power generation system is an energy solution actively developed in the aerospace field. Of course, the corresponding heat energy can be generated in other forms and then converted into electric energy. There are many techniques for converting heat energy into electric energy in a space, and among them, the stirling generator is a new and efficient technique. The gas sealed in the metal cavity is heated by external heat energy to expand and do work, so that the piston is pushed to do reciprocating motion to cut magnetic lines of force and generate electric energy. In order to verify the feasibility of the principle, the hot end of the Stirling generator is heated by the electric heating wire in the ground research process, so that the fact that the Stirling system can generate electricity and realize thermoelectric conversion is proved to be feasible in principle.
After the verification experiment is carried out on the ground, a corresponding experiment needs to be carried out in the space to verify the feasibility of the Stirling power generation under the microgravity. The Stirling generator to be launched for the experiment in the last day is required to be small in size and light in weight, and also required to have the characteristics of good launching impact resistance, high safety and reliability, long service life and the like. Therefore, the design needs to be different from the structure of the ground-verified Stirling generator so as to meet the requirement of aerospace. The Stirling generator cavity stores specific gas, and the gas expanded by heating does work to push the piston to do reciprocating motion to generate power. Therefore, the chamber must have good vacuum tightness, can bear large pressure, and has good mechanical properties. According to these requirements, the cavity must be of a metallic material. In order to meet the requirements of compact volume, low energy consumption and the like required by space launching, the metal heating wire must be close to a generator cavity, namely the cavity is a metal hearth of the heating wire. How to ensure the insulativity between the heating wire and the metal hearth, especially the insulativity and the safety and reliability under special conditions of space launching, microgravity environment and the like. On the premise of insulation, how to transfer the heat of the heating wire to the gas in the metal cavity more efficiently. How to design the insulating material can not only bear high temperature, but also resist the mechanical impact of space launching. How to realize the accurate measurement and control of the temperature of the heating assembly and ensure that the thermocouple and the metal hearth keep good insulation.
Disclosure of Invention
To this end, the invention provides a heating assembly for an aerospace metal hearth, comprising: the heating layer, the insulating sleeve layer and the polyimide rubberized fabric layer are sequentially arranged on the outer surface of the metal hearth from inside to outside and formed by spirally winding an iron-chromium-aluminum heating wire.
Preferably, the surface of the iron-chromium-aluminum heating wire is provided with an insulating protective film; the insulating protective film is obtained by pre-sintering an iron-chromium-aluminum heating wire at high temperature; the high-temperature presintering temperature is 700-950 ℃, and the heat preservation time is 4-12 hours.
Preferably, the iron-chromium-aluminum heating wire is sleeved into the first high-temperature-resistant insulating fiber sleeve, the first high-temperature-resistant insulating fiber sleeve embedded with the iron-chromium-aluminum heating wire is sleeved into the second high-temperature-resistant insulating fiber sleeve, and finally the first high-temperature-resistant insulating fiber sleeve is spirally wound on the outer surface of the metal hearth to form a heating layer;
the diameter of the first high-temperature-resistant insulating fiber sleeve is 0.9-1.5 mm; the diameter of the second high-temperature-resistant insulating sleeve is 1.8-2.5 mm;
the first high-temperature-resistant insulating fiber sleeve is made of alumina or quartz, and the second high-temperature-resistant insulating fiber sleeve is made of alumina or quartz.
Preferably, a spiral-shaped tooth-shaped groove for filling and fixing the iron-chromium-aluminum heating wire is formed in the surface of the metal hearth; the section of the tooth-shaped groove is rectangular; the width and the depth of the tooth-shaped groove exceed the diameter of the iron-chromium-aluminum heating wire by 1-2mm.
Preferably, the surface of the metal hearth is provided with a spiral-shaped tooth-shaped groove for filling and fixing the iron-chromium-aluminum heating wire; the section of the tooth-shaped groove is rectangular; the width and the depth of the tooth-shaped groove exceed the diameter of the second high-temperature-resistant insulating sleeve by 1-2mm.
Preferably, the iron-chromium-aluminum heating wire is cut flat at the wire inlet and outlet positions in the tooth-shaped groove.
Preferably, the insulating sleeve layer is obtained by spirally winding a third high-temperature-resistant insulating fiber sleeve on the surface of the metal hearth for 1-5 circles; the diameter of the third high-temperature-resistant insulating fiber sleeve is 4-8mm, and the third high-temperature-resistant insulating fiber sleeve is made of alumina or quartz;
the total thickness of the polyimide rubber cloth layer is 0.1 mm-1 mm.
Preferably, a first high-temperature-resistant insulating fiber sleeve and a second high-temperature-resistant insulating fiber sleeve are sleeved on a wire outlet of the iron-chromium-aluminum heating wire, and a ceramic tube is sleeved finally after the first high-temperature-resistant insulating fiber sleeve and the second high-temperature-resistant insulating fiber sleeve are tightly wound by a polyimide adhesive tape;
the diameter of the first high-temperature-resistant insulating fiber sleeve is 0.9-1.5 mm; the diameter of the second high-temperature-resistant insulating sleeve is 1.8-2.5 mm; the inner diameter of the ceramic tube is 4-8mm, and the thickness of the ceramic tube is 2-4 mm.
The first high-temperature-resistant insulating fiber sleeve is made of alumina or quartz, and the second high-temperature-resistant insulating fiber sleeve is made of alumina or quartz; the ceramic tube is made of aluminum oxide.
Preferably, a ceramic pipe is sleeved at the wire outlet of the iron-chromium-aluminum heating wire; the inner diameter of the ceramic tube is 4-8mm, and the thickness of the ceramic tube is 2-4 mm; the ceramic tube is made of aluminum oxide.
Preferably, the metal foil also comprises a metal half layer and a platinum reflecting screen which are sequentially distributed on the surface of the polyimide rubberized fabric layer; the thickness of the metal half layer is 0.5-3 mm; the metal half layer is provided with a hole, and an iron-chromium-aluminum heating wire is led out to be connected with a lead; the thickness of the platinum reflecting screen is 0.02-0.06 mm.
Preferably, the iron-chromium-aluminum heating wire also comprises at least 1 temperature thermocouple arranged at the starting position or/and the ending position of the iron-chromium-aluminum heating wire; the head of the temperature thermocouple is sleeved with a double-hole ceramic sleeve, and the wire part of the thermocouple is sleeved with a 4-layer high-temperature-resistant insulating fiber sleeve; the material of the double-hole ceramic sleeve is alumina; the high-temperature-resistant insulating fiber sleeve is made of aluminum oxide or quartz.
Preferably, the circumference of the starting part or/and the ending part of the chromium-aluminum heating wire is provided with at least 1 hole for fixing a temperature thermocouple; the depth of the hole is 5-10mm, and the diameter is 4-7 mm; the bottom of the hole is padded with high-temperature-resistant insulating fiber cloth; the high-temperature insulating fiber cloth is made of alumina or quartz.
Has the advantages that:
with the development of deep space exploration and the residence time of a space aircraft, the requirement on space power technology is higher and higher, and the source of power cannot be limited to solar power generation, but is diversified. The Stirling power generation technology based on thermoelectric conversion is efficient, clean, small in size and light in weight, and is very suitable for being used in outer space. The Stirling power generation mainly realizes power generation by driving a piston to reciprocate through the expansion of gas in a closed cavity by heating. The cavity body not only has good sealing performance, but also can bear certain pressure, and is generally made of metal materials. Therefore, the insulation between the metal heating wire and the cavity (metal hearth) is a key technology. The heating wire is subjected to high-temperature pre-sintering treatment, an insulating protective film is formed on the surface, and 2 layers of high-temperature-resistant insulating fiber sleeves are sleeved on the heating wire, so that the insulating property of the heating wire is improved. The outer surface of the metal hearth is provided with a spiral tooth-shaped groove, and the heating wire is spirally wound on the surface of the metal hearth, so that the energy transfer efficiency between the heating wire and the metal hearth is improved. The thermocouple head for temperature measurement and control is sleeved with an insulating ceramic tube, and the wire part is sleeved with 4 layers of high-temperature-resistant insulating sleeves and fixed in a hole of a metal hearth, so that insulation and accurate temperature measurement and control are ensured. The heating wire is wound by using the high-temperature-resistant insulating fiber sleeve and then fastened by using the metal half, so that the heating assembly meets the requirements of mechanical impact, safety and reliability, long service life and the like of space launching.
Drawings
FIG. 1 is a schematic view of a heating element; wherein, the metal furnace hearth is 1 part, the tooth-shaped groove is 2 parts, the insulating sleeve layer is 3 parts, the polyimide rubberized fabric layer is 4 parts, the metal half is 5 parts, and the platinum reflecting screen is 6 parts.
Detailed Description
The present invention is further illustrated by the following examples, which are to be understood as merely illustrative and not restrictive.
The invention aims to provide a heating assembly of a metal hearth for spaceflight. In order to achieve the above object, the present invention firstly provides a pretreatment method of an iron-chromium-aluminum heating wire. The pretreatment method is that before the iron-chromium-aluminum heating wire is wound, the heat preservation time is 4 to 12 hours at 700 to 950 ℃, and an insulating protective film is formed on the surface of the iron-chromium-aluminum heating wire.
After the iron-chromium-aluminum heating wire is pretreated at high temperature, the insulating conductivity of the surface of the heating wire is measured by using a universal meter, and a layer of insulating protective film is formed on the surface and is in an insulating state. Then, a first high-temperature-resistant insulating fiber sleeve (the diameter of the sleeve is 0.9-1.5 mm) is sleeved on the heating wire, and a second high-temperature-resistant insulating fiber sleeve (the diameter of the sleeve is 1.8-2.5 mm) is sleeved on the outer part of the heating wire. Wherein, the first and the second high temperature resistant insulating fiber sleeve materials can be alumina or quartz.
In order to fix the iron-chromium-aluminum heating wire, a tooth-shaped groove is processed on the outer surface of the metal hearth, and the length can be set according to the heating area. The size of the tooth-shaped groove is related to the size of the iron-chromium-aluminum heating wire, and the width and the depth of the groove are 1-2mm larger than the diameter of the heating wire; or the size of the tooth-shaped groove is related to the size of the second high-temperature-resistant insulating fiber sleeve, and the groove width and the groove depth are 1-2mm larger than the diameter of the second high-temperature-resistant insulating fiber sleeve. In order to avoid the sharp corner from generating cutting damage to the heating wire or the second high-temperature-resistant insulating fiber sleeve in the process of space launching and operation, the tooth-shaped groove is rectangular. Preferably, the corners of the tooth-shaped groove are rounded. The initial part of the tooth-shaped groove for winding the iron-chromium-aluminum heating wire and the end part of the tooth-shaped groove after winding are respectively called as a wire inlet part and a wire outlet part. At the wire inlet and the wire outlet of the iron-chromium-aluminum heating wire, because the two free moving spaces are large, the heating wire is easy to rub or cut with peripheral metal in the launching process, so that the insulating sleeve is broken, and the insulativity is poor. Therefore, the tooth-shaped grooves at the wire inlet and the wire outlet are preferably flattened, and the corners are rounded.
On the surface of the metal hearth, the iron-chromium-aluminum heating wire is wound up around the tooth-shaped groove and fixed in the tooth-shaped groove, and then a third high-temperature-resistant insulating fiber sleeve is tightly wound on the surface of the metal hearth for 1-5 circles. The third refractory insulating fiber sleeve may have a diameter of 4-8mm and may be made of alumina or quartz. Through the mode that the third high temperature resistant insulating fiber sleeve pipe twines closely, tightly fix indisputable chromium aluminium heater strip in the tooth-shaped groove, avoid popping out. Meanwhile, the combination of the iron-chromium-aluminum heating wire and the metal hearth is increased, so that heat can be conveniently and efficiently transferred from the heating wire to the metal hearth, and the energy utilization efficiency is improved. Finally, the fixed fiber sleeve is wound and glued by utilizing the polyimide adhesive tape, the fastening performance of the heating assembly is enhanced, meanwhile, the polyimide has certain high temperature resistance, and the damage of scratches and the like on the surface of the heating assembly in the subsequent processing process can be avoided.
Two layers of high temperature resistant insulating fiber sleeves (made of alumina or quartz) are sleeved on the outlet of the heating wire of the heating assembly, and are tightly wound by polyimide adhesive tapes, and finally, ceramic tubes are sleeved on the sleeves. The heating wire is prevented from rubbing and cutting with surrounding metal parts, the insulating property is ensured, and the mechanical resistance is improved. And (4) polishing the exposed part of the iron-chromium-aluminum heating wire by using a file, and polishing the surface insulation oxide film till the conduction is realized. Bending and hooking the exposed head part of the iron-chromium-aluminum heating wire, connecting the bent and hooked head part with 1-6 leads, and brazing by utilizing a silver-plated copper pipe.
The heating component is provided with at least 1 temperature thermocouple for measuring and controlling the heating temperature. The thermocouple head is sleeved with a double-hole ceramic sleeve and is packaged by utilizing polyimide adhesive tapes. The thermocouple wire sleeve has 4 layers of high temperature resistant insulating fiber sleeve made of alumina or quartz.
At least 1 hole is symmetrically arranged on the circumference of the starting or ending part of the wire winding on the outer surface of the metal hearth and used for fixing a thermocouple. The hole depth is 5-10mm, the diameter is 4-7mm, and the bottom of the hole is padded with high-temperature resistant insulating fiber cloth. And inserting the head part of the thermocouple which is well insulated and sealed into the hole, and binding and fixing by using the fiber sleeve.
And finally, installing a metal half outside the heating assembly, wherein holes are formed in the metal half and used for leading out heating wires and thermocouples, and the holes all need to be rounded. The two metal half are connected and fixed through screws, a layer of platinum reflecting screen is wrapped on the side face of the metal half, and the reflecting screen is fixed by binding iron-chromium-aluminum heating wires for 1-5 circles.
The present invention will be described in detail by way of examples. It is also to be understood that the following examples are illustrative of the present invention and are not to be construed as limiting the scope of the invention, and that certain insubstantial modifications and adaptations of the invention by those skilled in the art may be made in light of the above teachings. The specific process parameters of time, temperature, pressure, power, etc. in the following examples are also only one example of suitable ranges, i.e., those skilled in the art can select them within suitable ranges through the description herein, and are not intended to be limited to the specific values exemplified below.
Based on the requirements, the novel heating assembly is innovatively designed and is specially used for heating the aerospace metal hearth. Heating element can closely laminate with metal furnace, keeps efficient heat-conduction, is favorable to reducing the volume moreover. Through the design and processing of the insulating material, the safety and reliability of spaceflight can be kept while high temperature is borne, the aerospace mechanical impact is resisted, and the long-life operation is realized. The head of the thermocouple and the filament are correspondingly insulated and protected, so that the thermocouple not only can accurately reflect the temperature of the heating assembly, but also can keep good insulating property with a metal hearth and a metal heating wire.
A spiral tooth-shaped groove is processed on the outer surface of a metal cylinder with the outer diameter of 60mm, the groove depth and the groove width are both 2.5mm, a rectangular groove is formed, and the number of turns of the groove is 12. Meanwhile, two holes are symmetrically formed in the wire feeding position along the circumference of the metal cylinder, the diameter of each hole is 6mm, and the depth of each hole is 8mm. And at the wire inlet and outlet positions, the teeth are flattened to protect the wire inlet and outlet. Selecting a FeCrAl heating wire with the diameter of 0.9mm, heating to 750 ℃ at the speed of 10 ℃/min, preserving the heat for 6 hours, and finishing pre-sintering in air atmosphere. After the heating wire is pre-sintered, the insulation conductivity of the surface of the heating wire is measured by using a universal meter, the surface insulation is good, and the heating wire can be used. The inner sleeve is provided with a 1mm alumina fiber sleeve, and the outer sleeve is provided with a 2mm quartz fiber sleeve. Then winding in a tooth-shaped groove on the surface of the metal hearth until 12 turns are finished. And 2 circles of alumina fiber sleeves with the diameter of 7mm are wound on the outer surface of the metal hearth, and polyimide adhesive tapes are used for winding protection.
And sleeving 2 layers of quartz fiber sleeves at the filament outlet of the heating filament, and tightly winding with a polyimide adhesive tape. Then, an alumina ceramic tube is sleeved on the sleeve. And (4) polishing the silk outlet part by using a file until the silk outlet part is communicated. Bending and hooking the wire outlet part of the heating wire, connecting the bent and hooked heating wire with 4 wires, and carrying out silver brazing by using a silver-plated copper pipe.
The head of the thermocouple is sleeved into a double-hole alumina ceramic head, the diameter of the ceramic head is 5 multiplied by 9mm, and a polyimide adhesive tape is pasted on the ceramic to prevent the head of the thermocouple from jumping out. The outer surface of the thermocouple wire is sleeved with 4 layers of high-temperature-resistant insulating fiber sleeves, and a layer of quartz fiber cloth is padded at the bottom of a thermocouple hole in the surface of the metal hearth. The heads of 2 thermocouples are respectively inserted into the holes, and then are bound and fixed by using insulating fiber tubes.
Two metal half are arranged outside the heating assembly, 6 holes are formed in the metal half and used for leading out heating wires and 2 thermocouples, and the holes in the metal half are rounded, so that cutting or friction between the metal half and the outgoing wires is avoided, and insulativity is reduced. The two metal half pieces are connected and fixed through screws. And coating a layer of platinum reflecting screen on the side surface of the metal half, binding 2 circles by using an FeCrAl heating wire, and fixing the reflecting screen and the heating assembly.
Claims (10)
1. A heating assembly for an aerospace metal hearth, comprising: the heating layer, the insulating sleeve layer and the polyimide rubberized fabric layer are sequentially arranged on the outer surface of the metal hearth from inside to outside and formed by spirally winding an iron-chromium-aluminum heating wire.
2. The heating element of metal hearth for space flight according to claim 1, characterized in that the surface of said iron chromium aluminum heating wire has insulating protective film; the insulating protective film is obtained by pre-sintering an iron-chromium-aluminum heating wire at high temperature; the high-temperature presintering temperature is 700-950 ℃, and the heat preservation time is 4-12 hours.
3. The heating component of the metal hearth for spaceflight according to the claim 1, wherein the iron-chromium-aluminum heating wire is sleeved into the first high-temperature resistant insulating fiber sleeve, then the first high-temperature resistant insulating fiber sleeve embedded with the iron-chromium-aluminum heating wire is sleeved into the second high-temperature resistant insulating fiber sleeve, and finally the first high-temperature resistant insulating fiber sleeve is spirally wound on the outer surface of the metal hearth to form the heating layer;
the diameter of the first high-temperature-resistant insulating fiber sleeve is 0.9-1.5 mm; the diameter of the second high-temperature-resistant insulating sleeve is 1.8-2.5 mm;
the first high-temperature-resistant insulating fiber sleeve is made of alumina or quartz, and the second high-temperature-resistant insulating fiber sleeve is made of alumina or quartz.
4. The heating element of an aerospace metal hearth according to claim 1, wherein spiral-shaped tooth-shaped grooves for filling and fixing iron chromium aluminum heating wires are formed on the surface of the metal hearth; the section of the tooth-shaped groove is rectangular; the width and the depth of the tooth-shaped groove exceed the diameter of the iron-chromium-aluminum heating wire by 1-2mm.
5. The aerospace metal hearth heating assembly of claim 4, wherein the gullets are flattened at the wire inlet and outlet of the iron chromium aluminum heater wire in the gullet.
6. The heating assembly of the metal hearth for spaceflight according to claim 1, wherein the insulating sleeve layer is obtained by spirally winding a third high-temperature-resistant insulating fiber sleeve on the surface of the metal hearth for 1-5 circles; the diameter of the third high-temperature-resistant insulating fiber sleeve is 4-8mm, and the third high-temperature-resistant insulating fiber sleeve is made of alumina or quartz;
the total thickness of the polyimide rubber cloth layer is 0.1 mm-1 mm.
7. The heating assembly of the metal hearth for spaceflight according to claim 1, wherein a first high temperature resistant insulating fiber sleeve and a second high temperature resistant insulating fiber sleeve are sleeved on the wire outlet of the iron-chromium-aluminum heating wire, and a ceramic tube is sleeved on the wire outlet after the wire outlet is tightly wound by a polyimide adhesive tape;
the diameter of the first high-temperature-resistant insulating fiber sleeve is 0.9-1.5 mm; the diameter of the second high-temperature-resistant insulating sleeve is 1.8-2.5 mm;
the inner diameter of the ceramic tube is 4-8mm, and the thickness of the ceramic tube is 2-4 mm;
the first high-temperature-resistant insulating fiber sleeve is made of alumina or quartz, and the second high-temperature-resistant insulating fiber sleeve is made of alumina or quartz; the ceramic tube is made of aluminum oxide.
8. The heating assembly of the metal hearth for spaceflight according to claim 1, further comprising a metal half layer and a platinum reflecting screen which are sequentially distributed on the surface of the polyimide adhesive tape layer; the thickness of the metal half layer is 0.5-3 mm; a hole is formed in the metal half layer, and an iron-chromium-aluminum heating wire is led out to be connected with a lead;
the thickness of the platinum reflecting screen is 0.02-0.06 mm.
9. The heating component of the metal hearth for spaceflight according to claim 1, further comprising at least 1 temperature thermocouple arranged at the starting or/and ending part of the iron-chromium-aluminum heating wire; the head part of the temperature thermocouple is sleeved with a double-hole ceramic sleeve, and the wire part of the thermocouple is sleeved with 4 layers of high-temperature-resistant insulating fiber sleeves; the double-hole ceramic sleeve is made of aluminum oxide; the high-temperature-resistant insulating fiber sleeve is made of aluminum oxide or quartz.
10. The heating assembly of metal hearth for spaceflight according to claim 9, wherein the circumference of the starting or/and ending part of the chromium-aluminum heating wire is provided with not less than 1 hole for fixing the temperature thermocouple; the depth of the hole is 5-10mm, and the diameter is 4-7 mm; and the bottom of the hole is padded with high-temperature-resistant insulating fiber cloth; the high-temperature insulating fiber cloth is made of alumina or quartz.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211073064.5A CN115474301A (en) | 2022-09-02 | 2022-09-02 | Heating assembly of metal hearth for spaceflight |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211073064.5A CN115474301A (en) | 2022-09-02 | 2022-09-02 | Heating assembly of metal hearth for spaceflight |
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| Publication Number | Publication Date |
|---|---|
| CN115474301A true CN115474301A (en) | 2022-12-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211073064.5A Pending CN115474301A (en) | 2022-09-02 | 2022-09-02 | Heating assembly of metal hearth for spaceflight |
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| Country | Link |
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| CN (1) | CN115474301A (en) |
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2022
- 2022-09-02 CN CN202211073064.5A patent/CN115474301A/en active Pending
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