CN218998311U - Heating assembly of metal hearth for spaceflight - Google Patents
Heating assembly of metal hearth for spaceflight Download PDFInfo
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- CN218998311U CN218998311U CN202222337263.4U CN202222337263U CN218998311U CN 218998311 U CN218998311 U CN 218998311U CN 202222337263 U CN202222337263 U CN 202222337263U CN 218998311 U CN218998311 U CN 218998311U
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Abstract
The utility model relates to a heating component of a metal hearth for spaceflight. The heating component of the metal hearth for aerospace comprises: the metal hearth, the heating layer, the insulating sleeve layer and the polyimide adhesive layer which are formed by spirally winding iron-chromium-aluminum heating wires and are sequentially arranged on the outer surface of the metal hearth from inside to outside. According to the utility model, the high-temperature-resistant insulating fiber sleeve is used for winding the heating wire, and then the metal half is used for fastening, so that the heating component meets the requirements of mechanical impact, safety reliability, long service life and the like of space launching.
Description
Technical Field
The utility model relates to a heating component of a metal hearth for spaceflight, and belongs to the technical field of high-temperature heating.
Background
In recent years, with the development of aerospace exploration, a spacecraft flies farther and longer, and the survival time in space is longer and longer, which puts higher demands on the power supply of the space. Currently, sustainable electricity can be provided to aerospace vehicles by solar cells, however, as the vehicle moves away from the sun, the energy density of solar energy is getting lower and lower, and even insufficient energy is being provided. Solar radiation, at 1374W/m near the earth 2 Reduced to 50W/m near the wood star 2 Only 1W/m near the meditation 2 . Thus, in deep space exploration away from the sun, solar energy has not been able to provide enough power, and new sustainable energy sources must be found to provide enough power for the aircraft.
Atomic energy is a very promising energy source with long service life and is expected to play an important role in deep space exploration. The heat generated by the atomic nucleus reaction drives the power generation system to generate power, so that the power is provided for the aerospace craft, and the energy solution scheme is actively developed in the aerospace field. Of course, the corresponding thermal energy may also be generated in other forms and then converted into electrical energy. There are various techniques for converting thermal energy into electric energy in space, and a stirling generator is a novel 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, magnetic force lines are cut, and electric energy is generated. In order to verify the feasibility of the principle, in the ground research process, the electric heating wire is used for heating the hot end of the Stirling generator, so that the Stirling system is proved to be capable of generating electricity, and the thermoelectric conversion is realized, so that the principle is feasible.
After the verification experiment is carried out on the ground, a corresponding experiment is carried out in space to verify the feasibility of Stirling power generation under microgravity. The Stirling generator to be used for carrying out experiments on the day is required to be small in size and light in weight, and has the characteristics of good emission impact resistance, high safety and reliability, long service life and the like. Therefore, in design, the Stirling generator needs to be different from the structure of a Stirling generator verified on the ground to meet the requirement of aerospace. The Stirling generator cavity is used for storing specific gas, and the heated and expanded gas is used for acting to push the piston to do reciprocating motion to generate power. Therefore, the cavity must have good vacuum tightness, be able to withstand large pressures, and have good mechanical properties. According to these requirements, the cavity must be of 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 needs to be closely abutted against the cavity of the generator, namely, the cavity is a metal hearth of the heating wire. How to ensure the insulativity between the heating wire and the metal hearth, in particular to the insulativity and the safety and the reliability under special conditions of aerospace emission, 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, so that the insulating material can not only bear high temperature, but also resist mechanical impact of spaceflight emission. How to realize accurate measurement and control of the temperature of the heating component and keep the thermocouple well insulated from the metal hearth.
Disclosure of Invention
To this end, the utility model provides a heating assembly for a metal hearth for aerospace, comprising: the metal hearth, the heating layer, the insulating sleeve layer and the polyimide adhesive layer which are formed by spirally winding iron-chromium-aluminum heating wires and are sequentially arranged on the outer surface of the metal hearth from inside to outside.
Preferably, the surface of the iron-chromium-aluminum heating wire is provided with an insulating protective film; the insulating protective film is obtained by presintering an iron-chromium-aluminum heating wire at a 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 firstly, 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 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 sleeve is made of alumina or quartz.
Preferably, a spiral tooth-shaped groove for filling and fixing the iron-chromium-aluminum heating wire is arranged on the surface of the metal hearth; the section of the tooth-shaped groove is rectangular; the width and depth of the tooth-shaped groove exceed the diameter of the iron-chromium-aluminum heating wire by 1-2mm.
Preferably, a spiral tooth-shaped groove for filling and fixing the iron-chromium-aluminum heating wire is arranged on the surface of the metal hearth; the section of the tooth-shaped groove is rectangular; the width and depth of the tooth-shaped groove exceed the diameter of the second high-temperature-resistant insulating sleeve by 1-2mm.
Preferably, the tooth-shaped groove is flattened at the positions of the wire inlet and outlet of the iron-chromium-aluminum heating wire 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 adhesive 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 at the wire outlet of the iron-chromium-aluminum heating wire, and a ceramic tube is sleeved after the first high-temperature-resistant insulating fiber sleeve and the second high-temperature-resistant insulating fiber sleeve are tightly wound by polyimide rubberized fabric;
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 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 sleeve is made of alumina or quartz; the ceramic tube is made of aluminum oxide.
Preferably, a ceramic tube 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 is 2-4 mm; the ceramic tube is made of aluminum oxide.
Preferably, the polyimide adhesive tape also comprises 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; punching holes on the metal half layer, and leading out an iron-chromium-aluminum heating wire connected with the lead; the thickness of the platinum reflecting screen is 0.02-0.06 mm.
Preferably, the device also comprises at least 1 temperature thermocouple arranged at the starting or/and ending part of the iron-chromium-aluminum heating wire; the head of the temperature thermocouple is sleeved with a double-hole ceramic sleeve, and the thermocouple wire part is sleeved with 4 layers of high-temperature-resistant insulating fiber sleeves; the double-hole ceramic sleeve is made of alumina; the high-temperature-resistant insulating fiber sleeve is made of alumina or quartz.
Preferably, at least 1 hole is formed on the circumference of the starting or/and ending part of the chromium-aluminum heating wire for fixing the 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.
The beneficial effects are that:
with the development of deep space exploration and space craft residence time, the requirements for space electric power technology are increasing, and the source of electric power cannot be limited to solar power generation only, but is diversified. The Stirling power generation technology based on thermoelectric conversion is an efficient, clean, small-size and light-weight technology, and is very suitable for space use. The Stirling power generation mainly comprises the steps of heating and expanding gas in a closed cavity to drive a piston to reciprocate, so that power generation is realized. The cavity is not only good in sealing performance, but also can bear certain pressure, and is generally made of metal materials. Therefore, insulation between the metal heating wire and the cavity (metal hearth) is a key technology. The heating wire is subjected to high-temperature presintering treatment, an insulating protective film is formed on the surface of the heating wire, and the heating wire is sleeved with 2 layers of high-temperature-resistant insulating fiber sleeves, so that the self-insulating performance is improved. The spiral tooth-shaped grooves are processed on the outer surface of the metal hearth, and the heating wires are spirally wound on the surface of the metal hearth, so that the energy transfer efficiency between the spiral tooth-shaped grooves and the heating wires is improved. The thermocouple head for temperature measurement and control is sleeved with an insulating ceramic tube, the wire part is sleeved with 4 layers of high-temperature resistant insulating sleeves, and the insulating ceramic sleeves are fixed in holes of a metal hearth, so that insulation and accurate temperature measurement and control are ensured. The high-temperature-resistant insulating fiber sleeve is used for winding the heating wire, and then the heating wire is fastened by using metal half, so that the heating assembly meets the requirements of mechanical impact, safety, reliability, long service life and the like of space launching.
Drawings
FIG. 1 is a schematic diagram of a heating assembly; wherein, the metal furnace chamber is 1-, the tooth-shaped groove is 2-, the insulating sleeve layer is 3-, the polyimide adhesive layer is 4-, the half is 5-and the platinum reflecting screen is 6-.
Detailed Description
The utility model is further illustrated by the following embodiments, which are to be understood as merely illustrative of the utility model and not limiting thereof.
The utility model aims to provide a heating component of a metal hearth for aerospace. In order to achieve the above purpose, the present utility model firstly provides a pretreatment method for 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 4-12 hours at 700-950 ℃, and a layer of 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 insulation conductivity of the surface of the heating wire is measured by using a universal meter, so that the surface is ensured to form a layer of insulation protection film, and the insulation protection film is in an insulation state. Then, a layer of 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 layer of second high-temperature-resistant insulating fiber sleeve (the diameter of the sleeve is 1.8-2.5 mm) is sleeved outside the heating wire. Wherein the first and second high temperature resistant insulating fiber sleeve materials may be alumina or quartz.
In order to fix the iron-chromium-aluminum heating wire, tooth-shaped grooves are processed on the outer surface of the metal hearth, and the length of the tooth-shaped grooves 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 groove width and the groove depth 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 cutting damage to the heating wire or the second high-temperature-resistant insulating fiber sleeve by sharp corners in the aerospace launching and running processes, the tooth-shaped grooves are formed into a rectangle. Preferably, corners of the tooth-shaped grooves are rounded. The initial part of the tooth-shaped groove for arranging the iron-chromium-aluminum heating wire to start winding and the tail end part of the tooth-shaped groove after winding are respectively called a wire inlet position and a wire outlet position. At the wire feeding position and the wire discharging position of the iron-chromium-aluminum heating wire, because the free moving spaces of the two positions are larger, the heating wire is easy to rub or cut with surrounding metal in the transmitting process, so that the insulating sleeve is broken, and the insulativity is poor. Therefore, it is preferable to flatten the tooth grooves at the wire feeding and discharging positions and round the corners.
And on the surface of the metal hearth, the iron-chromium-aluminum heating wire spirals around the tooth-shaped groove and is fixed in the tooth-shaped groove, and then the third high-temperature-resistant insulating fiber sleeve is tightly wound on the surface of the metal hearth for 1-5 circles. The diameter of the third high temperature resistant insulating fiber sleeve can be 4-8mm, and the material can be alumina or quartz. By tightly winding the third high-temperature-resistant insulating fiber sleeve, the iron-chromium-aluminum heating wire is tightly fixed in the tooth-shaped groove, so that the spring is avoided. Meanwhile, the combination of the iron-chromium-aluminum heating wire and the metal hearth is increased, so that heat is conveniently and efficiently transferred from the heating wire to the metal hearth, and the energy utilization efficiency is improved. And finally, winding and gluing the fixed fiber sleeve by using polyimide adhesive tape, so that the tightness of the heating assembly is enhanced, meanwhile, polyimide has certain high temperature resistance, and the damage of the heating assembly caused by scratches and the like on the surface in the subsequent processing process can be avoided.
And (3) sleeving two layers of high-temperature-resistant insulating fiber sleeves (the materials can be alumina or quartz) at the wire outlet position of the heating wire of the heating assembly, tightly winding by using polyimide rubberized fabric, and sleeving a ceramic tube. The friction and cutting between the heating wire and surrounding metal parts are avoided, the insulation performance is ensured, and the mechanical resistance is improved. And polishing the exposed part of the iron-chromium-aluminum heating wire by using a file, and polishing the surface insulating oxide film until the surface insulating oxide film is conducted. Bending and hooking the exposed part of the iron-chromium-aluminum heating wire, connecting with 1-6 wires, and brazing by using a silver-plated copper tube.
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 polyimide adhesive tape. The thermocouple wire sleeve 4 layers of high-temperature resistant insulating fiber sleeves can be made of alumina or quartz.
At least 1 hole is symmetrically arranged on the circumference of the starting or stopping part of the wire winding on the outer surface of the metal hearth for fixing the thermocouple. The depth of the hole is 5-10mm, the diameter is 4-7mm, and the bottom of the hole is filled with high temperature resistant insulating fiber cloth. Inserting the insulating and sealed thermocouple head into the hole, and binding and fixing by using a fiber sleeve.
Finally, metal half is arranged outside the heating component, and 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 fixedly connected through screws, a layer of platinum reflecting screen is covered on the side of the metal half, and the reflecting screen is fixed by binding 1-5 circles of iron-chromium-aluminum heating wires.
The present utility model will be further illustrated by the following examples. It is also to be understood that the following examples are given solely for the purpose of illustration and are not to be construed as limitations upon the scope of the utility model, since numerous insubstantial modifications and variations will now occur to those skilled in the art in light of the foregoing disclosure. The specific time, temperature, pressure, power, etc. of the process parameters in the examples below are also only one example of suitable ranges, i.e., one skilled in the art can select from the description herein within the suitable ranges and are not intended to be limited to the specific values of the examples below.
Based on the requirements, the novel heating component is innovatively designed and is specially used for heating the space metal hearth. The heating element can be closely attached to the metal hearth, high-efficiency heat conduction is maintained, and the volume is reduced. Through the design and processing of the insulating material, the high-temperature-resistant composite material can bear high temperature, can keep the safety and reliability of spaceflight, resists the mechanical impact of the spaceflight, and can work with long service life. 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 performance with the metal hearth and the metal heating wire.
On the outer surface of a metal cylinder with the outer diameter of 60mm, spiral tooth-shaped grooves are processed, the groove depth and the groove width are 2.5mm, rectangular grooves are formed, and the number of turns of the grooves is 12. Meanwhile, at the wire feeding position, two holes are symmetrically formed along the circumference of the metal cylinder, the diameter of each hole is 6mm, and the depth of each hole is 8mm. And (3) at the wire inlet and outlet positions, the teeth are flattened to protect the wire inlet and outlet positions. Selecting a FeCrAl heating wire with the diameter of 0.9mm, heating to 750 ℃ at 10 ℃/min, and preserving heat for 6 hours, and completing presintering in air atmosphere. After the heating wire is presintered, the insulation conductivity of the surface of the heating wire is measured by using a universal meter, and the surface insulation is good and can be used. An alumina fiber sleeve with the diameter of 1mm is sleeved in the inner sleeve, and a quartz fiber sleeve with the diameter of 2mm is sleeved outside the inner sleeve. Then winding in the tooth-shaped groove on the surface of the metal hearth until 12 circles are wound. And winding an alumina fiber sleeve with the diameter of 7mm on the outer surface of the metal hearth for 2 circles, and winding and protecting by using polyimide rubberized fabric.
And sleeving 2 layers of quartz fiber sleeves at the positions of the heating wires, and tightly winding the quartz fiber sleeves by polyimide rubberized fabric. Then sleeving an alumina ceramic tube. And polishing the wire outlet position by using a file until the wire outlet position is communicated. Bending and hooking the wire outlet of the heating wire, connecting the wire outlet with 4 wires, and carrying out silver brazing by using a silver-plated copper tube.
The thermocouple head is sleeved into a double-hole alumina ceramic head, the diameter of the ceramic head is 5 multiplied by 9mm, and polyimide rubberized fabric is pasted on the ceramic, so that the thermocouple head is prevented from being jumped 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 the thermocouple hole on the surface of the metal hearth. The heads of the 2 thermocouples are respectively inserted into the holes, and then are bound and fixed by using an insulating fiber pipe.
Two metal half are arranged outside the heating component, 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 to avoid cutting or friction with the wires to cause insulation reduction. The two metal half are connected and fixed through screws. A platinum reflecting screen is coated on the metal half side, 2 circles of FeCrAl heating wires are used for binding, and the reflecting screen and the heating component are fixed.
Claims (10)
1. A heating assembly for a metal hearth for aerospace comprising: the metal hearth, the heating layer, the insulating sleeve layer and the polyimide adhesive layer which are formed by spirally winding iron-chromium-aluminum heating wires and are sequentially arranged on the outer surface of the metal hearth from inside to outside.
2. The heating assembly of a metal hearth for aerospace according to claim 1, wherein the iron-chromium-aluminum heating wire has an insulating protective film on the surface.
3. The heating assembly of the metal hearth for aerospace according to claim 1, wherein the iron-chromium-aluminum heating wire is sleeved with a first high-temperature-resistant insulating fiber sleeve outside, and sleeved with a second high-temperature-resistant insulating fiber sleeve outside the first high-temperature-resistant insulating fiber sleeve;
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 fiber sleeve is 1.8-2.5 mm.
4. The heating assembly of a metal hearth for aerospace according to claim 1, wherein a spiral-shaped tooth-shaped groove for filling and fixing a ferrochrome aluminum heating wire is arranged on the surface of the metal hearth; the section of the tooth-shaped groove is rectangular; the width and depth of the tooth-shaped groove exceed the diameter of the iron-chromium-aluminum heating wire by 1-2mm.
5. The heating assembly for a metal hearth for aerospace according to claim 4, wherein the tooth grooves are flattened at the locations of the entry and exit of the iron-chromium-aluminum heating wire in the tooth grooves.
6. The heating assembly of a metal hearth for aerospace 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 4-8 mm;
the total thickness of the polyimide adhesive cloth layer is 0.1 mm-1 mm.
7. The heating assembly of the metal hearth for aerospace according to claim 1, wherein a first high-temperature-resistant insulating fiber sleeve and a second high-temperature-resistant insulating fiber sleeve are sleeved at the wire outlet of the iron-chromium-aluminum heating wire, the outside of the second high-temperature-resistant insulating fiber sleeve is tightly wound by a polyimide rubberized fabric, and a ceramic tube is sleeved outside the polyimide rubberized fabric;
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 fiber sleeve is 1.8-2.5 mm;
the inner diameter of the ceramic tube is 4-8mm, and the thickness is 2-4 mm.
8. The heating assembly of a metal hearth for aerospace according to claim 1, further comprising a metal half layer and a platinum reflecting screen sequentially distributed on the surface of the polyimide rubberized fabric layer; the thickness of the metal half layer is 0.5-3 mm; punching holes on the metal half layer, and leading out an iron-chromium-aluminum heating wire connected with the lead;
the thickness of the platinum reflecting screen is 0.02-0.06 mm.
9. The heating assembly of a metal hearth for aerospace according to claim 1, further comprising at least 1 temperature thermocouple provided at the start or/and end of the iron-chromium-aluminum heating wire; the head of the temperature thermocouple is sleeved with a double-hole ceramic sleeve, and the thermocouple wire part is sleeved with 4 layers of high-temperature-resistant insulating fiber sleeves.
10. The heating assembly of a metal hearth for aerospace according to claim 9, wherein at least 1 hole is formed on the circumference of the starting or/and ending part of the chromium-aluminum heating wire for fixing a temperature thermocouple; the depth of the hole is 5-10mm, and the diameter is 4-7 mm; and the bottom of the hole is filled with high temperature resistant insulating fiber cloth.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202222337263.4U CN218998311U (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 |
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| CN202222337263.4U CN218998311U (en) | 2022-09-02 | 2022-09-02 | Heating assembly of metal hearth for spaceflight |
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| CN218998311U true CN218998311U (en) | 2023-05-09 |
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| CN202222337263.4U Active CN218998311U (en) | 2022-09-02 | 2022-09-02 | Heating assembly of metal hearth for spaceflight |
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