CN109332132A - A kind of electric propulsion device insulating protection method - Google Patents
A kind of electric propulsion device insulating protection method Download PDFInfo
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- CN109332132A CN109332132A CN201811107019.0A CN201811107019A CN109332132A CN 109332132 A CN109332132 A CN 109332132A CN 201811107019 A CN201811107019 A CN 201811107019A CN 109332132 A CN109332132 A CN 109332132A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
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- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
- B05D5/12—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain a coating with specific electrical properties
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
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Abstract
The present invention relates to a kind of electric propulsion device insulating protection methods, belong to space High-Voltage Insulation protection technology field, solve existing insulating protection method there are insulation effects it is bad, and the problem of lead to electric propulsion device structure is complicated to change, increase electric propulsion device volume and weight.Electric propulsion device insulating protection method of the invention coats coatings on non-electrode conductive parts surface；The coatings be nano composite ceramic coating, comprising the following steps: (1) nano composite ceramic coating is shaken up, filter it is spare；(2) filtered nano composite ceramic coating is coated in the surface of non-electrode conductive parts, obtains ceramic coating；(3) it after ceramic coating surface drying, is baked to and does solid work, continue to roast and keep the temperature, close oven.The present invention does not increase the volume and weight of electric propulsion device by realizing more structurally sound insulation in all non-electrode conductive parts surface coated with nano composite ceramics coating, improves the service life of electric propulsion device.
Description
Technical field
The present invention relates to space High-Voltage Insulation protection technology field more particularly to a kind of electric propulsion device insulating protection sides
Method.
Background technique
It will be the following manned deep space exploration aircraft by the high-power electric propulsion device of representative of magnetopasma electric propulsion device
The first choice of propulsion system outside satisfaction on the basis of high-power condition of power supply, is easier to realize the propulsion of high thrust, high specific impulse
Performance.Since high-power magnetopasma electric propulsion device is to realize that propellant ionizes by electrode discharge, arc rank is opened in electric discharge
Section voltage can achieve 6000V or more, even the voltage between electrode also has several hundred after electric propulsion device steady operation
Volt, because there is the continuous injection of propellant, is also easily led electric propulsion device is non-electrode although working under vacuum conditions
It discharges between electric parts, this is absolutely not allowed in the electric propulsion device course of work.
The insulating properties improved between the high-power non-electrode conductive parts of magnetopasma electric propulsion device can effectively prevent electricity
Unnecessary electric discharge in the propeller course of work.There are mainly two types of present existing technical solutions: one is by structure
It is designed, increases the spacing between non-electrode conductive parts, its insulating properties is improved by the method, it must but increase spacing
It so will increase the volume of electric propulsion device, and the reliability of the method is not high；Another kind is by non-electrode what is be closer
Increase ceramic structures between conductive parts, its insulating properties is improved using simple physically-isolated mode, but increases pottery
Porcelain structural member increases the complexity of electric propulsion device assembly indirectly, reduces its whole reliability, increases electric propulsion device
Volume and weight, and this method can not prevent completely the electric discharge between all conductive parts.
In conclusion that there are insulation effects is undesirable for existing insulating protection method, and lead to electric propulsion device structure is complicated to change,
The problem of increasing electric propulsion device volume and weight.
Summary of the invention
In view of above-mentioned analysis, the present invention is intended to provide a kind of electric propulsion device insulating protection method, existing exhausted to solve
Edge means of defence insulation effect is bad, and leads to electric propulsion device structure is complicated to change, and increases asking for electric propulsion device volume and weight
Topic.
The purpose of the present invention is mainly achieved through the following technical solutions:
The present invention provides a kind of electric propulsion device insulating protection methods, coat insulation on non-electrode conductive parts surface and apply
Material, the coatings are nano composite ceramic coating；The insulating protection method the following steps are included:
(1) nano composite ceramic coating is shaken up, filter it is spare；
(2) filtered nano composite ceramic coating is coated in the surface of non-electrode conductive parts, obtains ceramic painting
Layer；
(3) it after ceramic coating surface drying, is baked to and does solid work, continue to roast and keep the temperature, close oven.
On the basis of above scheme, the present invention has also done following improvement:
Further, further include step (4): also coating intensive after having coated ceramic coating, strengthened agent coating, to be added
After strong agent coating surface drying, it is baked to intensive coating and does solid work.
Further, step (2) is coated using the first coating die, and step (4) is coated using the second coating die；Described
One coating die and the second coating die complementary structure.
Further, baking temperature is 100~130 DEG C in step (3), and baking time is 20~30 minutes；Maturing temperature is
550~650 DEG C, soaking time is 0.5~2 hour.
Further, maturing temperature is 600 DEG C in step (3), and soaking time is 1 hour.
Further, baking temperature is 400~600 DEG C in step (4), and baking time is 30~60 minutes.
Further, in step (4), intensive is triethylene tetramine, m-phenylene diamine (MPD) or diethylentriamine.
Further, before coated with nano composite ceramics coating, determination needs to carry out the non-electrode of dielectric ceramic layer coating
Conductive parts.
It further, further include to the non-electrode conductive parts for needing to carry out dielectric ceramic layer coating before step (1)
Surface is pre-processed, and is specifically comprised the following steps: first to treat coating surface oil removing, derusting, is roughened sandblasting later.
Further, spreading implement used in coating first uses washes of absolute alcohol, then is cleaned up with clear water, dries up.
In the step of insulating protection method of the present invention (2), the first coating die coated ceramic coating, including following step are used
It is rapid: the first coating die being placed in non-electrode conductive parts surface to be coated, is coated.
In the step of insulating protection method of the present invention (4), intensive coating is coated using the second coating die, including following
Step: the second coating die is placed on the ceramic coating on non-electrode conductive parts surface to be coated, is coated.
First coating die and the second coating die all have occlusion area and coating zone, and the complementary structure of the two makes
The region that can be coated to the first coating die will not be coated to using the second coating die；Use the second coating die energy
The region being enough coated to will not be coated to using the first coating die.Coated with nano composite ceramics coating and intensive 1 time or more
Secondary, after the completion of coating, orthographic projection of the ceramic coating on component is continuously that orthographic projection of the intensive coating on component is also
Continuously.The ceramic coating and intensive coating obtained using above-mentioned coating method is staggered, and staggered structure can
The problems such as keeping ceramic coating stronger, change more resistant against ambient temperature, avoiding the occurrence of ceramic coating decortication, peeling,
So that non-electrode conductive parts insulating properties is more preferable, insulation performance is more stable.
The present invention has the beneficial effect that:
(1) by compound in all non-electrode conductive parts surface coated with nano of high-power magnetopasma electric propulsion device
Ceramic coating, the characteristic to insulate using nano composite ceramic coating high temperature resistant, by force, enhances high-power magnetopasma electric propulsion
The insulating properties of device key components and parts, insulation stability is stronger, improves the service life of electric propulsion device.
(2) present invention is by the arrangement mode of optimization ceramic coating and intensive coating, i.e., by using the in coating
One coating die and the second coating die so that ceramic coating and intensive coating are staggered, rather than are provided separately, in turn
Increase the insulation performance between non-electrode conductive parts.
(3) electric propulsion device insulating protection method of the invention improves the insulating properties between components by coating coating,
Therefore the volume and weight of electric propulsion device is not will increase without changing the spacing between electric propulsion device inner components, to have
Effect reduces the development cost of high-power magnetopasma electric propulsion device.
(4) insulation between components can be realized by coating coatings in component surface in the present invention, without changing
The internal structure of power transformation propeller, therefore, insulating protection method of the invention are easy to operate and realize.
It in the present invention, can also be combined with each other between above-mentioned each technical solution, to realize more preferred assembled schemes.This
Other feature and advantage of invention will illustrate in the following description, also, certain advantages can become from specification it is aobvious and
It is clear to, or understand through the implementation of the invention.The objectives and other advantages of the invention can be by specification, claims
It is achieved and obtained in specifically noted content.
Detailed description of the invention
Attached drawing is only used for showing the purpose of specific embodiment, and is not to be construed as limiting the invention, in entire attached drawing
In, identical reference symbol indicates identical component.
Fig. 1 is the insulating protection method and process flow chart of the embodiment of the present invention；
Fig. 2 is the top view of the first coating die of the embodiment of the present invention；
Fig. 3 is the top view of the second coating die of the embodiment of the present invention.
Appended drawing reference:
1- occlusion area；2- coating zone.
Specific embodiment
Specifically describing the preferred embodiment of the present invention with reference to the accompanying drawing, wherein attached drawing constitutes the application a part, and
Together with embodiments of the present invention for illustrating the principle of the present invention, it is not intended to limit the scope of the present invention.
Technical solution set forth in the present invention is in the high-power non-electrode conductive parts of magnetopasma electric propulsion device
Outer surface coated with nano composite ceramics coating, but need to guarantee the necessary internal current transport properties of these conductive parts simultaneously.
The composition of nano composite ceramic coating used in the present invention are as follows: alumina powder, mass percentage 92%,
Boron nitride powder, mass percentage 6%, organic solvent, mass percentage 2%.
Before coating, it is necessary first to which one is done to the trend of electric current in the high-power magnetopasma electric propulsion device course of work
A preliminary judgement, identifies the non-electrode conductive parts for being wherein easy to produce electric discharge, and determination needs to carry out dielectric ceramic layer
The non-electrode conductive parts surface of coating.
In the present invention, surface drying refers to dry tack free, i.e. coating surface forms meagre film；It does solid work and refers to that entity is dry, is i.e. coating
It has been completely converted into solid film, there is certain degree of hardness.
According to the difference of insulating requirements, coating number can be for twice or more than twice, to reach under actual condition most
The stabilization effect matched.
A specific embodiment of the invention discloses a kind of electric propulsion device insulating protection method, at non-electrode conductive zero
Part surface coats coatings, and coatings are nano composite ceramic coating；The insulating protection method the following steps are included:
(1) nano composite ceramic coating is shaken up, filter it is spare；
(2) filtered nano composite ceramic coating is coated in the surface of non-electrode conductive parts, obtains ceramic painting
Layer；
(3) it after ceramic coating surface drying, is baked to and does solid work, continue to roast and keep the temperature, close oven.
When implementation, nano composite ceramic coating is coated in non-electrode conductive zero for needing to carry out dielectric ceramic layer coating
The surface of part, obtains ceramic coating, after ceramic coating surface drying, is baked to and does solid work, and continues to roast and keep the temperature, and closes oven.
Compared with prior art, the present embodiment has the beneficial effect that:
(1) by compound in all non-electrode conductive parts surface coated with nano of high-power magnetopasma electric propulsion device
Ceramic coating, the characteristic to insulate using nano composite ceramic coating high temperature resistant, by force, enhances high-power magnetopasma electric propulsion
The insulating properties of device key components and parts, insulation stability is stronger, improves the service life of electric propulsion device.
(2) electric propulsion device insulating protection method of the invention improves the insulating properties between components by coating coating,
Therefore the volume and weight of electric propulsion device is not will increase without changing the spacing between electric propulsion device inner components, to have
Effect reduces the development cost of high-power magnetopasma electric propulsion device.
(3) insulation between components can be realized by coating coatings in component surface in the present invention, without changing
The internal structure of power transformation propeller, therefore, insulating protection method of the invention are easy to operate and realize.
In view of the operating temperature of electric propulsion device is higher, violent cold and hot temperature change can make non-electrode conductive parts table
The ceramic coating peeling in face, decortication, therefore, the present embodiment also coats intensive after having coated ceramic coating, and strengthened agent
Coating after to be strengthened dose of coating surface drying, is baked to intensive coating and does solid work.After coating intensive coating, so that ceramic coating is more
Step up to cause, it is not easily to fall off, to further increase the insulation performance of coating.
In view of the purpose toasted after coated with nano composite ceramics coating is removed in nano composite ceramic coating
Moisture.Because what is removed is moisture, and the boiling point that normal pressure is lauched is 100 DEG C, so baking temperature is selected as 100~130 DEG C.
When baking time was less than 20 minutes under the conditions of baking temperature is 100 DEG C, the water in nano composite ceramic coating is gone
Except incomplete, ceramic coating is not done solid work, and hardness is inadequate；When baking time is 30 minutes, moisture be can remove completely, and the time extends again
It will increase energy consumption.When baking time is 20 minutes under the conditions of baking temperature is 130 DEG C, moisture be can remove completely, ceramic coating
Hardness can satisfy requirement.So baking time of the invention is selected as 20~30 minutes.
In order to enable ceramic coating to resist thermal shock, ceramic coating is baked to by the present embodiment do solid work after carry out heating roasting
It burns, so that ceramic coating be made to can adapt to larger range of temperature change, makes ceramic coating and metallic matrix thermal expansion matching.
By analysis, it was found that, maturing temperature is 550~650 DEG C, and soaking time is 0.5~2 hour, is preferably roasted
Temperature is 600 DEG C, and soaking time is 1 hour, and the good insulating of obtained ceramic coating, bond strength is high, excellent combination property.
In order to make intensive play the role of protecting ceramic coating well, the present embodiment is 400~600 DEG C in temperature,
Time is to toast under conditions of 30~60 minutes to intensive coating, and the intensive curing of coatings after baking is complete, intensity
Greatly, ceramic coating uses also do not peel for a long time, stable insulation.
Further, in the step (4), intensive is triethylene tetramine, m-phenylene diamine (MPD) or diethylentriamine.
In order to reduce labor intensity, the present embodiment is not all coated all components in electric propulsion device,
Trend before coated with nano composite ceramics coating, first to electric current in the high-power magnetopasma electric propulsion device course of work
A preliminary judgement is done, the non-electrode conductive parts for being wherein easy to produce electric discharge are identified, what determination was coated
Non-electrode conductive parts surface, to can not only reduce labor intensity, but also can be improved efficiency, save material cost.
The influence to coating insulation performance such as greasy dirt, iron rust in order to prevent, the present embodiment are applied in coated with nano composite ceramics
Coating surface oil removing, derusting are treated before material, are roughened sandblasting later.Specific steps are as follows: treat coating surface with organic solvent
Greasy dirt is wiped, and is then cleaned with clean cotton, if any metal oxide, concentrated hydrochloric acid be can be used to spray oxide layer, is stood
It is cleaned after a few minutes using clean cotton.Roughening sandblasting procedures select the diamond dust that granularity is 40 mesh and the Buddha's warrior attendant that granularity is 60 mesh
Sand is that the ratio of 1:1 uses after mixing in mass ratio.Sandblasting grade is more than or equal to 2.5 grades.
Used spreading implement first uses washes of absolute alcohol when the present embodiment coating, then is cleaned with clear water, dries up.To painting
The purpose that cloth tool carries out above-mentioned processing is: first is that washing the impurity on spreading implement, preventing conductive impurity coated
It is adhered in coating in journey, influences the insulation performance of coating；Second is that the presence of impurity can make coating coating uneven, band impurity portion
The coating of position is easy to fall off, can not play insulating effect；Third is that drying spreading implement can prevent moisture from entering nano composite ceramic
Its performance is influenced in coating.
In order to further increase the booster action of intensive, the ceramic coating and intensive coating of the present embodiment are not to separate
Setting, but be staggered, staggered ceramic coating and intensive coating are by using the first coating die and second
What coating die was realized, the specific steps are as follows:
In step (2), the first coating die is placed in non-electrode conductive parts surface to be coated, is coated.
In step (4), the second coating die is placed on the ceramic coating on non-electrode conductive parts surface to be coated, into
Row coating.
First coating die and the second coating die all have occlusion area 1 and coating zone 2, the complementary structure of the two,
The region that can be coated to using the first coating die will not be coated to using the second coating die；Use the second coating die
The region that can be coated to will not be coated to using the first coating die.
Staggered structure can make ceramic coating stronger, change more resistant against ambient temperature, avoid out
The problems such as existing ceramic coating decortication, peeling, so that non-electrode conductive parts insulating properties is more preferable, insulation performance is more stable.
Embodiment 1
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) by liquid nano composite ceramics coating on aging machine sealed rolling to bucket bottom without precipitating, with 80 mesh filter screens
It is spare after filtering；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, using spreading implement by nano composite ceramic
Coating is coated uniformly on the outer surface of non-electrode conductive parts；
(5) under room temperature after surface drying to be coated, oven door is closed, oven is run, is toasted 30 minutes at 100 DEG C；Exist later
It is roasted 2 hours at 550 DEG C, closes oven；
(6) oven door is opened, is cooled to room temperature non-electrode conductive parts, then in its external coating intensive triethylene
Tetramine after to be strengthened dose of coating surface drying, closes oven door, runs oven, toast 60 minutes at 400 DEG C, that is, completes once
Coating.
Embodiment 2
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) sealing of liquid nano composite ceramics coating is stirred evenly into no precipitating, with spare after 120 mesh filter screen filtrations；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, the first coating die are placed in be coated non-
Nano composite ceramic coating is coated uniformly on non-electrode conductive parts using spreading implement by electrodes conduct component surface
Outer surface；
(5) under room temperature after surface drying to be coated, oven door is closed, oven is run, is toasted 20 minutes at 130 DEG C；Exist later
It is roasted 0.5 hour at 650 DEG C, closes oven；
(6) oven door is opened, non-electrode conductive parts is cooled to room temperature, the second coating die is placed in be coated non-
On the ceramic coating of electrodes conduct component surface, intensive m-phenylene diamine (MPD) is coated, after to be strengthened dose of coating surface drying, closes oven
Door runs oven, toasts 30 minutes at 600 DEG C, that is, complete primary coating.
Embodiment 3
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) by liquid nano composite ceramics coating on aging machine sealed rolling to bucket bottom without precipitating, with 100 mesh filter screens
It is spare after filtering；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, the first coating die are placed in be coated non-
Nano composite ceramic coating is coated uniformly on non-electrode conductive parts using spreading implement by electrodes conduct component surface
Outer surface；
(5) it is toasted 25 minutes at 115 DEG C after surface drying to be coated under room temperature；It roasts 1 hour, closes at 600 DEG C later
Oven；
(6) oven door is opened, non-electrode conductive parts is cooled to room temperature, the second coating die is placed in be coated non-
On the ceramic coating of electrodes conduct component surface, intensive diethylentriamine is coated, after to be strengthened dose of coating surface drying, is closed roasting
Fire door runs oven, toasts 50 minutes at 500 DEG C, that is, complete primary coating.
Embodiment 4
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) by liquid nano composite ceramics coating on aging machine sealed rolling to bucket bottom without precipitating, with 80 mesh filter screens
It is spare after filtering；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, using spreading implement by nano composite ceramic
Coating is coated uniformly on the outer surface of non-electrode conductive parts；
(5) under room temperature after surface drying to be coated, oven door is closed, oven is run, is toasted 30 minutes at 100 DEG C；Exist later
It is roasted 2 hours at 550 DEG C, closes oven；
(6) oven door is opened, is cooled to room temperature non-electrode conductive parts, then in its external coating intensive triethylene
Tetramine after to be strengthened dose of coating surface drying, closes oven door, runs oven, toast 60 minutes at 400 DEG C, that is, completes once
Coating；
The step of repeating the present embodiment (4) to (6) is primary.
Embodiment 5
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) sealing of liquid nano composite ceramics coating is stirred evenly into no precipitating, with spare after 120 mesh filter screen filtrations；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, the first coating die are placed in be coated non-
Nano composite ceramic coating is coated uniformly on non-electrode conductive parts using spreading implement by electrodes conduct component surface
Outer surface；
(5) under room temperature after surface drying to be coated, oven door is closed, oven is run, is toasted 20 minutes at 130 DEG C；Exist later
It is roasted 0.5 hour at 650 DEG C, closes oven；
(6) oven door is opened, non-electrode conductive parts is cooled to room temperature, the second coating die is placed in be coated non-
On the ceramic coating of electrodes conduct component surface, intensive m-phenylene diamine (MPD) is coated, after to be strengthened dose of coating surface drying, closes oven
Door runs oven, toasts 30 minutes at 600 DEG C, that is, complete primary coating；
(7) the first coating die is changed to the step of the second coating die repeats the present embodiment (4)；
(8) the step of repeating the present embodiment (5)；
(9) the second coating die is changed to the step of the first coating die repeats the present embodiment (6).
Embodiment 6
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) by liquid nano composite ceramics coating on aging machine sealed rolling to bucket bottom without precipitating, with 100 mesh filter screens
It is spare after filtering；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, the first coating die are placed in be coated non-
Nano composite ceramic coating is coated uniformly on non-electrode conductive parts using spreading implement by electrodes conduct component surface
Outer surface；
(5) it is toasted 25 minutes at 115 DEG C after surface drying to be coated under room temperature；It roasts 1 hour, closes at 600 DEG C later
Oven；
(6) oven door is opened, non-electrode conductive parts is cooled to room temperature, the second coating die is placed in be coated non-
On the ceramic coating of electrodes conduct component surface, intensive diethylentriamine is coated, after to be strengthened dose of coating surface drying, is closed roasting
Fire door runs oven, toasts 50 minutes at 500 DEG C, that is, complete primary coating；
(7) the first coating die is changed to the step of the second coating die repeats the present embodiment (4)；
(8) the step of repeating the present embodiment (5)；
(9) the second coating die is changed to the step of the first coating die repeats the present embodiment (6).
Embodiment 7
(1) surfaces of non-electrode conductive parts is subjected to degreasing and rust removal processing, and is roughened sandblasting, Sa2.5 grades of sandblasting or
More than, it is in mass ratio the proportion sandblasting of 1:1 with the diamond dust that granularity is 40 mesh and 60 mesh；
(2) by liquid nano composite ceramics coating on aging machine sealed rolling to bucket bottom without precipitating, with 80 mesh filter screens
It is spare after filtering；
(3) spreading implement is first cleaned up with clear water with after washes of absolute alcohol again, dries up standby with compressed air later
With；
(4) non-electrode conductive parts to be coated are placed in oven, using spreading implement by nano composite ceramic
Coating is coated uniformly on the outer surface of non-electrode conductive parts；
(5) under room temperature after surface drying to be coated, oven door is closed, oven is run, is toasted 30 minutes at 100 DEG C；Exist later
It is roasted 2 hours at 550 DEG C, closes oven；
(6) oven door is opened, is cooled to room temperature non-electrode conductive parts, then in its external coating intensive triethylene
Tetramine after to be strengthened dose of coating surface drying, closes oven door, runs oven, toast 60 minutes at 400 DEG C, that is, completes once
Coating；
The step of repeating the present embodiment (4) to (6) is twice.
Test method:
For the actual working environment demand of high-power magnetopasma electric propulsion device, 10-3Pa grades of vacuum degrees, starting the arc electricity
Press 6000V, operating current 150A, under conditions of 1200 DEG C of temperature, to high-power magnetic for using different technical parameters to coat etc. from
Daughter electric propulsion device carries out vacuum firing test.Test show that each embodiment takes place the conductive time and is shown in Table 1.
The conductive time occurs for the different embodiments of table 1
Note: " insulation " indicates conductive not yet after test starts 500 hours in table.
As can be seen from Table 1, the product of embodiment 1-3 is equally all nano composite ceramic coating of coating and once adds
Strong agent, but the product of embodiment 1 starts to start conduction in 115 hours in test, and the product of embodiment 2 and 3 is being surveyed respectively
Runin just starts conduction after beginning 172 hours and 180 hours.The product insulation performance of embodiment 2 and 3 is significantly better than embodiment 1, former
Because being: the ceramic coating and intensive coating of embodiment 1 are provided separately, and the ceramic coating of embodiment 2 and 3 and reinforcement
Agent coating is staggered.
By table 1 it can also be seen that coating nano composite ceramic coating and twice after intensive twice, the product of embodiment 4
Start conduction after test starts 330 hours, and staggered ceramic coating and the coating of intensive coating reach afterwards twice
Just reach insulation after insulation (embodiment 5 and 6), the ceramic coating being provided separately and the coating three times of intensive coating.It can be seen that
The insulation performance of staggered ceramic coating and intensive coating is significantly better than the ceramic coating being provided separately and intensive applies
The insulation performance of layer.
In conclusion the present invention by selecting suitable insulating protection material, passes through the tool of optimization coating method and coating
Body technology parameter, by optimizing the arrangement mode of ceramic coating and intensive coating, so that non-electrode conductive the zero of electric propulsion device
Insulating properties is more preferable between component, insulation stability is stronger, and can make the volume of high-power magnetopasma electric propulsion device it is minimum,
More compact structure, weight are most light, so that the development cost of high-power magnetopasma electric propulsion device be effectively reduced, improve its use
Service life.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.
Claims (10)
1. a kind of electric propulsion device insulating protection method, which is characterized in that coatings are coated on non-electrode conductive parts surface,
The coatings are nano composite ceramic coating；The insulating protection method the following steps are included:
(1) nano composite ceramic coating is shaken up, filter it is spare；
(2) filtered nano composite ceramic coating is coated in the surface of non-electrode conductive parts, obtains ceramic coating；
(3) it after ceramic coating surface drying, is baked to and does solid work, continue to roast and keep the temperature, close oven.
2. electric propulsion device insulating protection method according to claim 1, which is characterized in that the electric propulsion device insulating protection
Method further includes step (4): also coating intensive after having coated ceramic coating, strengthened agent coating, to be strengthened dose of coating table
After dry, it is baked to intensive coating and does solid work.
3. electric propulsion device insulating protection method according to claim 2, which is characterized in that step (2) uses the first coating
Mold coating, step (4) are coated using the second coating die；First coating die and the second coating die structure are mutual
It mends.
4. electric propulsion device insulating protection method according to claim 1, which is characterized in that baking temperature is in step (3)
100~130 DEG C, baking time is 20~30 minutes；Maturing temperature is 550~650 DEG C, and soaking time is 0.5~2 hour.
5. electric propulsion device insulating protection method according to claim 4, which is characterized in that roasting temperature in the step (3)
Degree is 600 DEG C, and soaking time is 1 hour.
6. electric propulsion device insulating protection method according to claim 2, which is characterized in that baking temperature in the step (4)
Degree is 400~600 DEG C, and baking time is 30~60 minutes.
7. electric propulsion device insulating protection method according to claim 2, which is characterized in that in step (4), intensive three
Ethylene tetramine, m-phenylene diamine (MPD) or diethylentriamine.
8. according to claim 1 to electric propulsion device insulating protection method described in 7, which is characterized in that in coated with nano composite ceramic
Before porcelain coating, the non-electrode conductive parts for needing to carry out dielectric ceramic layer coating are determined.
9. electric propulsion device insulating protection method according to claim 8, which is characterized in that further include pair before step (1)
The surface for needing to carry out the non-electrode conductive parts of dielectric ceramic layer coating is pre-processed, and specifically comprises the following steps: elder generation
Coating surface oil removing, derusting are treated, is roughened sandblasting later.
10. electric propulsion device insulating protection method according to claim 9, which is characterized in that be coated with work used in coating
Tool first uses washes of absolute alcohol, then is cleaned up with clear water, dries up.
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| CN201811107019.0A CN109332132A (en) | 2018-09-21 | 2018-09-21 | A kind of electric propulsion device insulating protection method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113981445A (en) * | 2021-10-25 | 2022-01-28 | 魏育军 | Calcium carbide furnace protection insulating material, preparation method and application thereof |
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| CN113981445A (en) * | 2021-10-25 | 2022-01-28 | 魏育军 | Calcium carbide furnace protection insulating material, preparation method and application thereof |
| CN113981445B (en) * | 2021-10-25 | 2023-09-19 | 魏育军 | Calcium carbide furnace protective insulating material, preparation method and application thereof |
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