CN103241391B - For the insulating assembly and preparation method thereof of Mars landing device heat control - Google Patents
For the insulating assembly and preparation method thereof of Mars landing device heat control Download PDFInfo
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- CN103241391B CN103241391B CN201310148829.1A CN201310148829A CN103241391B CN 103241391 B CN103241391 B CN 103241391B CN 201310148829 A CN201310148829 A CN 201310148829A CN 103241391 B CN103241391 B CN 103241391B
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- aerogel
- block body
- honeycomb
- landing device
- insulating assembly
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- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 239000004964 aerogel Substances 0.000 claims abstract description 82
- 238000005452 bending Methods 0.000 claims abstract description 28
- 239000000463 material Substances 0.000 claims abstract description 27
- 229910004298 SiO 2 Inorganic materials 0.000 claims abstract description 10
- 239000002131 composite material Substances 0.000 claims abstract description 8
- 239000000853 adhesive Substances 0.000 claims description 17
- 230000001070 adhesive effect Effects 0.000 claims description 17
- 239000000835 fiber Substances 0.000 claims description 11
- 239000004642 Polyimide Substances 0.000 claims description 7
- 239000003365 glass fiber Substances 0.000 claims description 7
- 239000012774 insulation material Substances 0.000 claims description 7
- 239000011104 metalized film Substances 0.000 claims description 7
- 229920001721 polyimide Polymers 0.000 claims description 7
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 238000000352 supercritical drying Methods 0.000 claims description 3
- 238000009413 insulation Methods 0.000 abstract description 10
- 230000000694 effects Effects 0.000 abstract description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 4
- 239000004917 carbon fiber Substances 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 230000005855 radiation Effects 0.000 description 3
- 230000002787 reinforcement Effects 0.000 description 3
- 239000008280 blood Substances 0.000 description 1
- 210000004369 blood Anatomy 0.000 description 1
- 239000006059 cover glass Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000011343 solid material Substances 0.000 description 1
- 239000007790 solid phase Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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- Laminated Bodies (AREA)
- Thermal Insulation (AREA)
Abstract
The invention discloses a kind of insulating assembly for the heat control of Mars landing device; comprise laminate structure, structural support, the first aerogel block body, the second aerogel block body, honeycomb and covering; the second aerogel block body is filled in the inside of honeycomb; and be sandwiched between upper and lower two-layer covering; form bending block; the first surface of bending block is provided with the first aerogel block body and structural support, the first aerogel block body outside face covers laminate structure; First aerogel block body and the second aerogel block body are SiO
2aerogel composite.The present invention also provides corresponding preparation method.The present invention adopts based on SiO
2the insulating assembly of aerogel, solves the problem that aerogel material is difficult to because of poor mechanical property apply, has excellent heat-proof quality, effectively meet the insulation requirement under Mars surface condition, and possess significant light weight effect, alleviate the weight of Mars landing device, economize on resources.
Description
Technical field
The present invention relates to a kind of insulating assembly, specifically a kind of insulating assembly for the heat control of Mars landing device and preparation method thereof.
Background technology
There is CO in martian surface
2the wind speed of air, severe sandstorm, 2 ~ 20m/s, range of temperature-130 DEG C ~+30 DEG C, by the impact of martian surface thermal environment, exist between Mars landing device and external environment condition convection current, radiation and with the multiple heat exchange modes such as the heat conduction on Mars ground.For the martian surface thermal environment that reply temperature traverse is violent, there is multiple heat exchange mode, its heat-proof device is very crucial.But under the thermal environment having gaseous exchange, the effect of heat insulation of conventional aerospace device multilayer insulation assembly obviously declines, and multilayer can not be satisfied with the insulation requirement of Mars landing device; In addition, the resources such as the weight of Mars landing device and the energy are most valuable, need heat-proof device to try one's best while meeting performance requriements expendable weight.
Aerogel is formed nanoporous network architecture a kind of mutually gathering with nanometer scale colloidal particle, and in hole, be full of the high dispersive solid-state material of gaseous state dispersed medium.SiO
2low (0.003 ~ the 0.5g/cm of aerogel density
3), pore-solids ratio high (80% ~ 99.8%), the thermal conductivity under normal temperature and pressure, lower than 0.02W/mK, even lowly reaches 0.012W/mK, and can adapt to the high/low temperature vacuum environment of-200 ~ 800 DEG C, is a kind of material that in solid material, thermal conductivity is minimum.But the feature that aerogel intensity is low, fragility is large makes it be difficult to be used alone as block thermal insulation material in engineering.Although introduce in aerogel reinforcement carry out strengthening, toughness reinforcing, the mechanical property of aerogel can be improved to a certain extent, but if enough mechanical properties will be ensured, just need introduce more reinforcement, the thermal conductivity that reinforcement itself is higher adds the solid-phase thermal conduction of material, causes effect of heat insulation to reduce.And insulating assembly of the present invention can realize SiO
2the application of aerogel material on Mars landing device, meets the insulation requirement under Mars surface condition.
Summary of the invention
For defect of the prior art, the object of this invention is to provide a kind of insulating assembly for the heat control of Mars landing device and preparation method thereof, this insulating assembly solve that Mars landing device is violent in temperature traverse, heat-insulating problem under the thermal environment that there is air-flow and the resource exception such as the energy, weight limited conditions.
The present invention is achieved by the following technical solutions.
A kind of insulating assembly for the heat control of Mars landing device; comprise laminate structure, structural support, the first aerogel block body, the second aerogel block body, honeycomb and covering; wherein; the second aerogel block body is filled in the inside of described honeycomb; and be sandwiched between upper and lower two-layer covering; form bending block, the first surface of described bending block is provided with the first aerogel block body and structural support, described first aerogel block body outside face covers laminate structure;
Described first aerogel block body and the second aerogel block body are SiO
2aerogel composite.
Described SiO
2aerogel composite has nano-porous structure and has low fibre content.
Described structural support is the epoxy resin material with lower thermal conductivity.
Described honeycomb is polyimide material, and the thickness of honeycomb is 10mm.
Described covering is carbon fibre materials, and the thickness of covering is lmm.
Described laminate structure is glass fibre material, and the thickness of laminate structure is 0.5mm.
Described first aerogel block body is bonding by high temperature resistant adhesive with between bending block, structural support and laminate structure; Described second aerogel block body is bonding by high temperature resistant adhesive with between covering.
The outside face of described laminate structure and the second face of bending block are covered with the metallized film layer with low-launch-rate.
For a preparation method for the insulating assembly of Mars landing device heat control, comprise the following steps:
Step 1, selects the SiO containing a small amount of fiber
2aerogel composite, and adopt the method for supercritical drying to prepare the first aerogel block body and the second aerogel block body, then carry out machine up, reach required size;
Step 2, inserts the inside of honeycomb by the second aerogel block body;
Step 3, at the upper and lower surface tiling covering of honeycomb, bonding by high temperature resistant adhesive between covering with honeycomb, form bending block;
Step 4, carries out bonding by the first aerogel block body with structural support by high temperature resistant adhesive, then by the first aerogel block body and structural support integral adhesive on the first surface of the bending block of step 3 gained;
Step 5, uses high temperature resistant adhesive album leave Rotating fields in the outside of the first aerogel block body.
For a preparation method for the insulating assembly of Mars landing device heat control, further comprising the steps of:
Step 6, has the metallized film of low-launch-rate at the outside face of laminate structure and second stickup of bending block.
Described honeycomb is polyimide material, and the thickness of honeycomb is 10mm;
Described covering is carbon fibre materials, and the thickness of covering is lmm;
Described laminate structure is glass fibre material, and the thickness of laminate structure is 0.5mm;
Described structural support is the epoxy resin material with lower thermal conductivity.
The honeycomb of above-mentioned carbon fiber skin and polyimide material, as structural slab load, is filled in the second aerogel block body of honeycomb core as thermal insulation material; Thermal insulation layer between instrument and equipment and bending block adopts structural support load, and the first aerogel block body is as thermal insulation material.
Insulating assembly for the heat control of Mars landing device provided by the invention and preparation method thereof, adopts nanoporous SiO
2aerogel, as thermal insulation material, by the aerogel that the structural defence intensity such as covering, honeycomb and structural support are low, is formed based on SiO
2the insulating assembly of aerogel, solves the problem that aerogel material is difficult to because of poor mechanical property apply, has excellent heat-proof quality, effectively meet the insulation requirement under Mars surface condition, and possess significant light weight effect, alleviate the weight of Mars landing device, economize on resources.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the insulating assembly structural representation for the heat control of Mars landing device of the present invention;
In figure, 1 is laminate structure, and 2 is structural support, and 3 is the first aerogel block body, and 4 is the second aerogel block body, and 5 is honeycomb, and 6 is covering.
Detailed description of the invention
Below embodiments of the invention are elaborated: the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement, these all belong to protection scope of the present invention.
As shown in Figure 1, the present embodiment provide firstly a kind of insulating assembly for the heat control of Mars landing device, comprises laminate structure 1, structural support 2, first aerogel block body 3, second aerogel block body 4, honeycomb 5, covering 6; Fill the second aerogel block body 4 in the honeycomb core of honeycomb, honeycomb 5 is sandwiched between upper and lower two-layer covering 6, forms bending block, and the second aerogel block body 4 is bonding by high temperature resistant adhesive with covering 6, and the thickness of honeycomb is 10mm; It is bonding to be equipped with above bending block that the first aerogel block body 3 and structural support 2, first aerogel block body 3 outside face cover laminate structure 1, first aerogel block body 3 and bending block, structural support 2, glass fibre thin layer 1 passes through high temperature resistant adhesive.Described first aerogel block body 3 and the second aerogel block body 4 are containing a small amount of fiber and have the SiO of nano-porous structure
2aerogel composite, density is 0.05 ~ 0.1g/cm
3, coefficient of thermal conductivity is lower than 0.016w/mK; Described structural support 2 is the epoxide resin material of lower thermal conductivity; Described laminate structure 1 is glass fibre material, and the thickness of laminate structure is 0.5mm, and described covering 6 is carbon fibre materials, and the thickness of covering is lmm, and laminate structure and covering outside face paste low-launch-rate metallized film.
The present embodiment additionally provides the preparation method of the insulating assembly for the heat control of Mars landing device, comprises the following steps:
Step 1, selects the SiO containing a small amount of fiber
2aerogel composite, and adopt the method for supercritical drying to prepare the first aerogel block body and the second aerogel block body, then carry out machine up, reach required size;
Step 2, inserts the inside of honeycomb by the second aerogel block body;
Step 3, at the upper and lower surface tiling covering of honeycomb, bonding by high temperature resistant adhesive between covering with honeycomb, form bending block;
Step 4, carries out bonding by the first aerogel block body with structural support by high temperature resistant adhesive, then by the first aerogel block body and structural support integral adhesive on the first surface of the bending block of step 3 gained;
Step 5, uses high temperature resistant adhesive album leave Rotating fields in the outside of the first aerogel block body.
Above-mentioned preparation method is further comprising the steps of:
Step 6, has the metallized film of low-launch-rate at the outside face of laminate structure and second stickup of bending block.
The principle of work of the present embodiment is: insulating assembly adopts carbon fiber skin polyimide bending block as structural slab load, and SiO filled by the honeycomb core of honeycomb
2aerogel block body is as thermal insulation material, and carbon fiber and polyimide are low thermal conductivity material, reduces the heat exchange of bending block both sides.Thermal insulation layer between instrument and equipment and bending block adopts the epoxy resin structural strut member load of lower thermal conductivity, SiO
2aerogel block body is heat insulation, and aerogel outside face cover glass fibre thin layer is worn and torn, due to SiO to prevent aerogel
2aerogel all has outstanding heat-proof quality in conduction, convection current, radiation three, has the advantage that density is little simultaneously, significantly can reduce the heat exchange of insulating assembly both sides.Glass fibre thin layer and carbon fiber skin outside face paste low-launch-rate metallized film, reduce the radiation heat transfer with lander internal unit and external environment condition, thus make described insulating assembly have excellent heat-proof quality under Mars surface condition.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. the insulating assembly for the heat control of Mars landing device, it is characterized in that, comprise laminate structure, structural support, the first aerogel block body, the second aerogel block body, honeycomb and covering, wherein, the second aerogel block body is filled in the inside of described honeycomb, and is sandwiched between upper and lower two-layer covering, forms bending block, the first surface of described bending block is provided with the first aerogel block body and structural support, described first aerogel block body outside face covers laminate structure;
Described first aerogel block body and the second aerogel block body are SiO
2aerogel composite;
The bending block that described covering and honeycomb are formed is as structural slab load; Be filled in the second aerogel block body in honeycomb as the first thermal insulation material; By structural support load between Mars landing device and described bending block; First aerogel block body is as the second thermal insulation material.
2. the insulating assembly for the heat control of Mars landing device according to claim 1, is characterized in that, described structural support is the epoxy resin material with lower thermal conductivity.
3. the insulating assembly for the heat control of Mars landing device according to claim 1, is characterized in that, described honeycomb is polyimide material, and the thickness of honeycomb is 10mm.
4. the insulating assembly for the heat control of Mars landing device according to claim 1, is characterized in that, described covering is carbon fibre materials, and the thickness of covering is 1mm.
5. the insulating assembly for the heat control of Mars landing device according to claim 1, is characterized in that, described laminate structure is glass fibre material, and the thickness of laminate structure is 0.5mm.
6. the insulating assembly for the heat control of Mars landing device according to claim 1, is characterized in that, described first aerogel block body is bonding by high temperature resistant adhesive with between bending block, structural support and laminate structure.
7. the insulating assembly for the heat control of Mars landing device according to any one of claim 1 to 6, is characterized in that, the outside face of described laminate structure and the second face of bending block are covered with the metallized film layer with low-launch-rate.
8., for a preparation method for the insulating assembly of Mars landing device heat control, it is characterized in that, comprise the following steps:
Step 1, selects the SiO containing a small amount of fiber
2aerogel composite, and adopt the method for supercritical drying to prepare the first aerogel block body and the second aerogel block body, then carry out machine up, reach required size;
Step 2, inserts the inside of honeycomb by the second aerogel block body;
Step 3, at the upper and lower surface tiling covering of honeycomb, bonding by high temperature resistant adhesive between covering with honeycomb, form bending block;
Step 4, carries out bonding by the first aerogel block body with structural support by high temperature resistant adhesive, then by the first aerogel block body and structural support integral adhesive on the first surface of the bending block of step 3 gained;
Step 5, uses high temperature resistant adhesive album leave Rotating fields in the outside of the first aerogel block body.
9. the preparation method of the insulating assembly for the heat control of Mars landing device according to claim 8, is characterized in that, further comprising the steps of:
Step 6, has the metallized film of low-launch-rate at the outside face of laminate structure and second stickup of bending block.
10. the preparation method of the insulating assembly for the heat control of Mars landing device according to claim 8 or claim 9, it is characterized in that, described honeycomb is polyimide material, and the thickness of honeycomb is 10mm;
Described covering is carbon fibre materials, and the thickness of covering is 1mm;
Described laminate structure is glass fibre material, and the thickness of laminate structure is 0.5mm;
Described structural support is the epoxy resin material with lower thermal conductivity.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310148829.1A CN103241391B (en) | 2013-04-25 | 2013-04-25 | For the insulating assembly and preparation method thereof of Mars landing device heat control |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310148829.1A CN103241391B (en) | 2013-04-25 | 2013-04-25 | For the insulating assembly and preparation method thereof of Mars landing device heat control |
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| CN103241391B true CN103241391B (en) | 2016-03-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3135451A1 (en) * | 2022-05-16 | 2023-11-17 | Airbus Defence And Space Sas | Thermoregulated space equipment with thermally insulating mechanical support |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494225B (en) * | 2014-12-16 | 2017-03-08 | 山东工业陶瓷研究设计院有限公司 | Silica aerogel combined rigidity thermal insulation tile and preparation method thereof can be processed |
| CN105083591B (en) * | 2015-07-31 | 2017-05-03 | 上海卫星工程研究所 | Integrated machine heat insulation device based on nanometer aerogel |
| CN105371058B (en) * | 2015-08-04 | 2018-10-23 | 上海卫星工程研究所 | Applied to aerogel heat-proof case of high-altitude when long on unmanned vehicle |
| CN109665862A (en) * | 2019-01-02 | 2019-04-23 | 中材科技（苏州）有限公司 | A kind of heat insulating construction plate and preparation method thereof |
| WO2022160174A1 (en) * | 2021-01-28 | 2022-08-04 | 华豹（天津）新材料科技发展股份有限公司 | Thermal-insulation aerogel vacuum composite board and preparation process therefor |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201599533U (en) * | 2009-06-02 | 2010-10-06 | 成都思摩纳米技术有限公司 | High temperature heat-perseveration thermal-insulation composite material |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7635411B2 (en) * | 2004-12-15 | 2009-12-22 | Cabot Corporation | Aerogel containing blanket |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201599533U (en) * | 2009-06-02 | 2010-10-06 | 成都思摩纳米技术有限公司 | High temperature heat-perseveration thermal-insulation composite material |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3135451A1 (en) * | 2022-05-16 | 2023-11-17 | Airbus Defence And Space Sas | Thermoregulated space equipment with thermally insulating mechanical support |
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| CN103241391A (en) | 2013-08-14 |
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