CN213755014U - Spiral high-temperature armored heater of high-energy propulsion system for satellite - Google Patents
Spiral high-temperature armored heater of high-energy propulsion system for satellite Download PDFInfo
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- CN213755014U CN213755014U CN202023071479.8U CN202023071479U CN213755014U CN 213755014 U CN213755014 U CN 213755014U CN 202023071479 U CN202023071479 U CN 202023071479U CN 213755014 U CN213755014 U CN 213755014U
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Abstract
The utility model discloses a star is with high energy propulsion system's screw-tupe high temperature armor heater belongs to armor heating device technical field. The sheathed heater comprises a working part, a transition part and a leading-out part; the working part is tightly attached to the outer side wall surface of a catalytic bed of the propulsion system and wound spirally along the circumferential direction of the catalytic bed, and comprises an armor protection shell, a heating wire, a compact ceramic framework and ceramic powder; the transition part and the leading-out direction of the working part form an angle of 90 degrees and comprises an armor protective shell, a compact ceramic framework, ceramic powder and a transition line; the leading-out part is composed of an outer sleeve and a plurality of leading-out partsThe outer strand lead wire and the high-temperature-resistant insulating glue. The utility model adopts the transition extraction process, so that the power is concentrated and the heating efficiency is higher; the platinum-rhodium alloy is used as a heating wire and an armored shell, and the heater works and has high temperature resistance; using alpha-Al2O3The ceramic is used as a supporting and protecting framework, so that the device has better insulating property and longer service life.
Description
Technical Field
The utility model relates to an armor heating device technical field, concretely relates to star is with high energy propulsion system's screw-tupe high temperature armor heater.
Background
After the spacecraft departs from the carrier rocket and enters the orbit, the maneuverability of the spacecraft is realized by completely depending on a self-matched space propulsion system in order to complete various flight tasks (such as spacecraft orbit change, orbit transfer and maintenance, self attitude adjustment and maintenance, spacecraft docking, rendezvous and separation, take-off and reentry of a lander and the like). The armored heater of the satellite propulsion system is one of important active thermal control facilities in the aerospace propulsion system, and has key effects on maintaining hot start of a catalytic bed and an injection chamber, reducing propellant consumption, prolonging the service life of a catalyst, preventing the propellant from icing and blocking a nozzle, ensuring sensitive ignition of the propulsion system according to instructions, safe operation and the like.
Liquid single-component thrusters are commonly used in spacecraft as their primary propulsion units. Hydrazines (N)2H4) The single-component propellant is the main propellant used in the existing attitude and orbit control propulsion system, and due to the safety problems of high toxicity, high ice point, flammability, explosiveness and the like of the hydrazine propellant, special protective measures are required to be taken in the installation process of the propulsion system, so that the launching cost, the use and maintenance costs and other related expenses of the satellite are greatly increased. With the development of the aerospace propulsion technology, high energy and green development become the main development directions of liquid propellant for the attitude and orbit control propulsion system of the spacecraft gradually. Currently, two more widely studied green propellants include HAN (hydroxylamine nitrate) and ADN (ammonium dinitramide) based propellantsBoth of them are safe, non-toxic, high energy and low freezing point. However, the preheating and ignition temperature required by the high-energy green thruster in the ignition process is higher, for example, the preheating temperature required by the catalyst of the high-energy ADN-based non-toxic thruster generally needs to reach more than 300 ℃, meanwhile, the combustion temperature of the propellant is as high as more than 1600 ℃, and the temperature transferred to the heater through the catalytic bed is also more than 1500 ℃, which puts higher requirements on the temperature bearing capacity of the sheathed heater.
At present, the armored heater of the satellite propulsion system developed in China mainly serves a single-unit hydrazine thruster, and since the heating device mainly adopts NiGr or NiGrAl as a heating body or an armored protective shell, the service temperature of the armored heater is only 1100 ℃ at most, the using requirement of a high-energy propellant at more than 1500 ℃ in the using process cannot be met, and meanwhile, the traditional armored heater is large in resistance value and low in power and cannot meet the high-temperature heating requirement. Some patents also propose the development of high power high temperature heaters, but there are some problems, such as: patent No. 201510153525.3 relates to a hall propeller's neutralizer heating device is a high power heating device, its armor heating element only constitute by heating core silk, ceramic powder, armor shell three, because ceramic powder intensity and density are not high, in heater bending or working process, the eccentric problem appears easily in the heating core silk for the heater appears the short circuit easily in the working process and burns the condition of silk. On the other hand, the heating device disclosed in the above patent has no design in the transition leading-out aspect, so that the power of the heater cannot be completely concentrated on the working section part during working, and the heating efficiency of the device is reduced to a certain extent. The aforementioned disadvantages are also present in the sheathed heater for a thermal conductivity level sensor for high temperature lava according to patent 201420798031.1.
SUMMERY OF THE UTILITY MODEL
In order to overcome the above-mentioned weak point that exists among the prior art, the utility model aims to provide a star is with high energy propulsion system's screw-tupe high temperature armor heater, this armor heater power is concentrated, and heating efficiency is higher, and the heater work is with tolerating the temperature height.
In order to achieve the above object, the utility model adopts the following technical scheme:
a spiral high-temperature armored heater of a high-energy propulsion system for a satellite comprises a working part, a transition part and a leading-out part, wherein: the working part comprises an armored protective shell I, a heating wire, a compact ceramic framework and ceramic powder; the transition part comprises an armor protection shell II, a compact ceramic framework, ceramic powder and a transition line; the leading-out part comprises an outer sleeve, a plurality of strands of outer leads and high-temperature-resistant insulating glue.
The working part of the armored heater is tightly attached to the wall surface of a catalytic bed of the propulsion system and is wound in a spiral shape along the circumferential direction of the catalytic bed, and the working part can be tightly attached to the catalytic bed of the thruster, so that the heating efficiency of the armored heater is guaranteed.
In the working part, the armored protection shell I is of a spiral tubular structure, the compact ceramic framework is a ceramic tube, the heating wire is arranged in the ceramic tube in a penetrating mode, the ceramic tube is arranged in the armored protection shell, and the ceramic powder is filled in a gap between the ceramic tube and the armored protection shell.
The transition part extends from the working part and forms an angle of 90 degrees with the leading-out direction of the working part; in the transition portion: the compact ceramic framework is a ceramic tube, the transition line is arranged in the ceramic tube in a penetrating mode, the ceramic tube is arranged in the armored protection shell II, and the ceramic powder is filled in a gap between the ceramic tube and the armored protection shell II.
The leading-out parts (two leading-out ends) of the heating wire loop are connected with the transition line in a spot welding mode, and the welding spot is located on the transition section part of the device.
The armored protection shell I and the armored protection shell II are thin-walled tube structures made of platinum-rhodium alloy, the outer diameter is 2mm, and the wall thickness is 0.15 mm; the compact ceramic skeleton is alumina ceramic, the alumina content is higher than 99%, and the density is higher than 90%; the heating wire is made of platinum-rhodium alloy, and the transition wire is made of metal platinum; the wire diameter of the transition line is about 1.5 times of the diameter of the heating wire, so that the heating power is ensured to be concentrated on the outer wall surface of the catalytic bed.
In the leading-out part, the multi-strand outer leads are separated by high-temperature-resistant insulating glue, and the outer sleeve is coated outside the multi-strand outer leads and the high-temperature-resistant insulating glue.
The multi-strand outer lead is connected to a transition line in the transition portion.
When the satellite is in a low-temperature environment (-250 ℃ to-100 ℃), the rated voltage of the armored heater can preheat a catalytic bed of the thruster to more than 400 ℃ under the condition of no coating. In a thermal vacuum flight simulation test, the device can withstand 1500 ℃ ignition high temperature after undergoing a plurality of ignition processes, and still operates well at present.
The design mechanism of the utility model is as follows:
compared with the prior high-temperature heater, the spiral high-temperature armored heater developed by the utility model uses the ceramic framework to position and protect the heating wire, and the main component in the ceramic framework is alpha-Al2O3And the content and the density of the alumina are higher than 90%, so that the ceramic skeleton is superior to ceramic powder in strength, toughness, temperature resistance, temperature impact resistance and other performances, can provide better protection and support for the heating wire at high temperature, and reduces the risk of short circuit of devices.
The utility model uses SiO2And Al2O3The mixed fine powder fills gaps in the device, the former has better bonding performance, the latter has higher dielectric constant, and the high-temperature and vibration performance of the device can be improved after the mixed fine powder and the dielectric constant are mixed according to the weight ratio of 1: 1. In order to concentrate the power of heater on the work portion, the utility model discloses the heater has used the transition to draw forth the design, uses the lower pure metal of conductivity as the transition line, improves the effective power of heater, improves the heating power of device.
Compared with the prior art, the utility model, following beneficial effect has:
(1) the transition leading-out process is adopted, so that the power is concentrated, and the heating efficiency is higher;
(2) the platinum-rhodium alloy is used as a heating wire and an armored shell, and the working temperature of the heater is high;
(3) SiO by vacuum infusion process2With Al2O3The powder is filled in the device, and the high-temperature anti-seismic performance of the heater is better;
(4) using alpha-Al2O3The ceramic is used as a supporting and protecting framework, so that the device has better insulating property, longer service life and higher reliability.
Drawings
FIG. 1 is a schematic structural view of a spiral high temperature armored heater of the high energy propulsion system for a satellite according to the present invention;
fig. 2 shows the preferred dimensions of each part of the spiral high-temperature armored heater of the present invention (the dimensions are in cm in the figure).
Fig. 3 is a schematic cross-sectional view taken at location "i" in fig. 2.
Fig. 4 is a schematic sectional view taken along line a-a in fig. 2.
Fig. 5 is an assembly schematic diagram of the spiral high-temperature armored heater and the catalytic bed of the present invention.
In the figure: 100-a working part; 101-armor shell i; 102-a ceramic skeleton; 103-ceramic powder; 104-a heating wire; 200-a transition portion; 201-armor shell II; 202-welding points; 300-a lead-out portion; 301-outer sleeve; 302-multi-strand lead; 303-high temperature resistant insulating glue; 4-catalytic bed.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings.
The utility model provides a spiral high-temperature armored heater of a high-energy propulsion system for a satellite, which comprises a working part, a transition part and a leading-out part, as shown in figures 1-4; the working part comprises an armored shell I101, a ceramic framework 102, ceramic powder 103 and a heating wire 104; the heating wire loop independently exists and is located inside the armored shell I101, the heating wire is externally installed in the ceramic framework 102 in a penetrating mode, ceramic powder 103 is filled in a device gap, and the heating wire loop is insulated from the armored shell. The ceramic framework is two parallel single-hole alumina ceramic tubes, and the main component is alpha-Al2O3The content of the aluminum oxide is higher than 99%, the density is higher than 90%, and the ceramic framework is utilized to position the heating wire. The ceramic powder is mainly composed of SiO2And Al2O3Mixing the fine powder according to the weight ratio of 1:1In a blend of SiO2Can improve the bonding performance of the ceramic powder layer, Al2O3The heat conduction efficiency and the insulating property of the heater can be improved. The armored shell I and the heating wire are both made of platinum-rhodium 30 alloy, and the wire diameter of the heating wire is 0.15 mm.
The transition part comprises an armored shell II 201, a ceramic framework, ceramic powder and a transition line, and the armored shell II 201, the ceramic framework and the ceramic powder are made of the same material or the same composition as the working part; the transition line is made of pure platinum metal, the wire diameter is 0.25mm, and the wire diameter of the transition line is thicker than that of the heating wire, so that the heating power is mainly concentrated on the working part. Leading-out parts (two leading-out ends) of the heating wire loop are connected with a transition line, the connection process is a spot welding process, and a welding spot is positioned on the transition section part of the device; the leading-out ends of the two heating wires are respectively connected with a transition line, and the formed two welding spots 202 are effectively protected by using a ceramic framework sleeve. (the ceramic framework used in the transition section part is a double-hole alumina ceramic pipe, and each hole of the ceramic pipe is protected by a welding spot)
The armored shell I and the armored shell II are of thin-wall tubular structures, the outer diameter of the armored shell I and the outer diameter of the armored shell II are 2mm, and the wall thickness of the armored shell I and the armored shell II is smaller than 0.15mm, so that heat conduction to the rear end is reduced.
The utility model discloses armor heater work portion is heliciform circumference and distributes in propulsion system catalysis bed 4 outer walls, and work portion can closely laminate with the thruster catalysis bed, guarantees the heating efficiency (fig. 5) of armor heater. The armored shell I is bent by 90 degrees after the working part is led out, so that the transition part structure at the rear end is protected.
The leading-out part comprises an outer sleeve 301, a plurality of leads 302 and high-temperature-resistant insulating glue 303, the leads and the transition wire are welded together through an argon protection micro-arc welding process, and the leads are connected with a power supply for the satellite. Fig. 5 shows two multi-strand lead wires, which are respectively connected to the positive and negative poles of a power supply. The high temperature resistant glue needs to have enough strength and can resist the high temperature of 250 ℃, such as silazane high temperature resistant glue.
The utility model discloses spiral high temperature armor heater has been installed on the green thrustor of high energy, has accomplished hot vacuum flight analogue test along with the thrustor at present, and the device can preheat the catalysis bed in the short time to more than 400 ℃ under the no cladding condition, and device surface temperature exceeds more than 600 ℃ this moment. The armored heater completes a plurality of preheating tasks in the test and also undergoes a plurality of ignition processes, and after the test is finished, the electrical performance of the device is good. Experiments prove that the device can not only endure the high-temperature ignition process of 1500 ℃, but also has higher heating efficiency and longer service life, and can ensure the normal work of the green high-energy thruster.
The above-mentioned embodiment is only the preferred embodiment of the present invention, and is not a limitation to the protection scope of the present invention, but all the changes made by adopting the design principle of the present invention and performing non-creative work on this basis should belong to the protection scope of the present invention.
Claims (8)
1. The utility model provides a star is with high energy propulsion system's screw-tupe high temperature armor heater which characterized in that: the sheathed heater comprises a working part, a transition part and an extraction part, wherein: the working part comprises an armored protective shell I, a heating wire, a compact ceramic framework and ceramic powder; the transition part comprises an armor protection shell II, a compact ceramic framework, ceramic powder and a transition line; the leading-out part comprises an outer sleeve, a plurality of strands of outer leads and high-temperature-resistant insulating glue.
2. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 1, wherein: the working part of the armored heater is tightly attached to the wall surface of a catalytic bed of the propulsion system and is wound in a spiral shape along the circumferential direction of the catalytic bed, and the working part can be tightly attached to the catalytic bed of the thruster, so that the heating efficiency of the armored heater is guaranteed.
3. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 2, wherein: in the working part, the armored protection shell I is of a spiral tubular structure, the compact ceramic framework is a ceramic tube, the heating wire is arranged in the ceramic tube in a penetrating mode, the ceramic tube is arranged in the armored protection shell, and the ceramic powder is filled in a gap between the ceramic tube and the armored protection shell.
4. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 3, wherein: the transition part extends from the working part and forms an angle of 90 degrees with the leading-out direction of the working part; in the transition portion: the compact ceramic framework is a ceramic tube, the transition line is arranged in the ceramic tube in a penetrating mode, the ceramic tube is arranged in the armored protection shell II, and the ceramic powder is filled in a gap between the ceramic tube and the armored protection shell II.
5. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 4, wherein: the leading-out part of the heating wire loop is connected with a transition line in a spot welding mode, and a welding spot is located on the transition section part of the device.
6. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 1, wherein: the armored protection shell I and the armored protection shell II are thin-walled tube structures made of platinum-rhodium alloy, the outer diameter is 2mm, and the wall thickness is 0.15 mm; the compact ceramic skeleton is alumina ceramic, and the main component is alpha-Al2O3The content of alumina is higher than 99 percent, and the density is higher than 90 percent; the heating wire is made of platinum-rhodium alloy, and the transition line is made of metal platinum; the wire diameter of the transition line is 1.5 times of the diameter of the heating wire, so that the heating power is ensured to be concentrated on the outer wall surface of the catalytic bed.
7. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 1, wherein: in the leading-out part, the multi-strand outer leads are separated by high-temperature-resistant insulating glue, and the outer sleeve is coated outside the multi-strand outer leads and the high-temperature-resistant insulating glue.
8. The helical high temperature sheathed heater of a high energy star propulsion system as claimed in claim 7, wherein: the multi-strand outer lead is connected with the transition line in the transition part in a row.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023071479.8U CN213755014U (en) | 2020-12-18 | 2020-12-18 | Spiral high-temperature armored heater of high-energy propulsion system for satellite |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202023071479.8U CN213755014U (en) | 2020-12-18 | 2020-12-18 | Spiral high-temperature armored heater of high-energy propulsion system for satellite |
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| CN213755014U true CN213755014U (en) | 2021-07-20 |
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| CN202023071479.8U Active CN213755014U (en) | 2020-12-18 | 2020-12-18 | Spiral high-temperature armored heater of high-energy propulsion system for satellite |
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