CN206885331U - A kind of compound heat shield of spacecraft - Google Patents
A kind of compound heat shield of spacecraft Download PDFInfo
- Publication number
- CN206885331U CN206885331U CN201720491315.XU CN201720491315U CN206885331U CN 206885331 U CN206885331 U CN 206885331U CN 201720491315 U CN201720491315 U CN 201720491315U CN 206885331 U CN206885331 U CN 206885331U
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- heat shield
- coat
- heat
- ceramic block
- foam ceramic
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Abstract
The utility model discloses a kind of compound heat shield of spacecraft, including load metal shell, light foam ceramic block, coat of metal film, polypropylene resin layer and airway tube processed, the load metal shell upper surface is covered with inorganic fibrous mats thermal insulation layer, the light foam ceramic block processed is uniformly fastened in heat shield, the coat of metal film is covered in heat shield outer surface, the polypropylene resin layer is connected to gently between foam ceramic block and cellular cushion interlayer processed, and the airway tube is arranged on cavity side.The utility model in load metal shell periphery by setting column, and it is provided with reinforcement in coat of metal film surface, improve the overall impact resistance of heat shield, heat conduction is reduced by the solar heat protection gauze pad between film, light foam ceramic block processed plays a supportive role between heat-insulated pure inert gas, polypropylene resin layer and the impact of cellular cushion interlayer heatproof heat-resistant, it is rational in infrastructure, it is adapted to be widely popularized.
Description
Technical field
Space equipment technical field is the utility model is related to, more particularly to a kind of compound heat shield of spacecraft.
Background technology
The thermal protection structure that spacecraft outer surface uses at present uses the plastic sheeting stepped construction with the coat of metal more,
Its basic characteristics is to be coated with the coat of metal in Plastic film surface, and the interval of plastic sheeting is divided with heat-insulated gauze pad on film
It is furnished with passage.The basic ideas of the structure design are to reduce radiant heat transfer by the coat of metal of film, allow between film layer and reduce
Heat transfer, interlayer gas flow is discharged to reduce convection heat transfer' heat-transfer by convection.But in actual applications, because pleat be present in coat of metal film
Wrinkle, and influenceed by punching and being bonded the technological factors such as heat-insulated gauze pad, the surface emissivity characteristic of coat of metal film changes
Become, the barrier property of heat radiation is decreased, for the heat-insulated gauze pad between plural layers, if mesh is too loose not
Direct contact that can be effectively between thin separation film, makes the barriering effect variation to heat transfer, and mesh can reduce as so dense
Buffer action of the heat-shielding net advance capital for body to heat transfer.Therefore we make improvement to this, propose a kind of compound heat shield of spacecraft.
Utility model content
Main purpose of the present utility model is to provide a kind of spacecraft compound heat shield can effectively solve background technology
The problem of middle.
To achieve the above object, the technical scheme that the utility model is taken is：
A kind of compound heat shield of spacecraft, including load metal shell, light foam ceramic block processed, coat of metal film,
Polypropylene resin layer and airway tube, the load metal shell upper surface is covered with inorganic fibrous mats thermal insulation layer, and load metal
Closure periphery is equipped with column, and the light foam ceramic block processed is uniformly fastened in heat shield, and the heat shield bottom is set
There is cavity, be filled with pure inert gas in the cavity, the coat of metal film is covered in heat shield outer surface, and metal
Be provided with reinforcement on plating layer film, the polypropylene resin layer be connected to light foam ceramic block processed and cellular cushion interlayer it
Between, solar heat protection gauze pad is fixedly connected with the cellular cushion interlayer, the solar heat protection gauze pad is set with coat of metal film contacts face
There is passage, the airway tube is arranged on cavity side.
Further, the airway tube is provided with sealing ring with the intraoral side of column contact jaw.
Further, it is fixedly connected by welding between the column bottom and load metal shell.
Further, described airway tube one end is provided with valve cock.
Further, the valve cock is made up of alloy material.
Further, the reinforcement and coat of metal film are formed in one structure.
Compared with prior art, the utility model has the advantages that：The compound heat shield of this kind of spacecraft, by
Load metal shell periphery sets column, and is provided with reinforcement in coat of metal film surface, improves the anti-of heat shield entirety
Impact capacity, the coat of metal reduce radiant heat transfer, and reducing heat by the solar heat protection gauze pad between film conducts, and solar heat protection gauze pad and metal
The passage in coating film contacts face is then to speed up the deflation between multilayer material, discharges interlayer gas flow to reduce to spreading
Heat, gently foam ceramic block processed played a supportive role between heat-insulated pure inert gas, polypropylene resin layer and cellular cushion
Interlayer heatproof heat-resistant impacts, and rational in infrastructure, function is easy to use, is adapted to be widely popularized.
Brief description of the drawings
Fig. 1 is a kind of global sections structural representation of the compound heat shield of spacecraft of the utility model.
In figure：1st, load metal shell；2nd, inorganic fibrous mats thermal insulation layer；3rd, heat shield；4th, cavity；5th, pure inert gas
Body；6th, light foam ceramic block processed；7th, column；8th, solar heat protection gauze pad；9th, reinforcement；10th, coat of metal film；11st, passage；
12nd, polypropylene resin layer；13rd, cellular cushion interlayer；14th, airway tube；15th, valve cock；16th, sealing ring.
Embodiment
Technological means, creation characteristic, reached purpose and effect to realize the utility model are easy to understand, below
With reference to embodiment, the utility model is expanded on further.
As shown in figure 1, a kind of compound heat shield of spacecraft, including load metal shell 1, light foam ceramic block 6 processed, gold
Category plating layer film 10, polypropylene resin layer 12 and airway tube 14, the upper surface of load metal shell 1 is covered with inorganic fibrous mats
Thermal insulation layer 2, and load metal shell 1 has been peripherally installed with column 7, the light foam ceramic block 6 processed is uniformly fastened on heat shield 3
Interior, the bottom of heat shield 3 is provided with cavity 4, and pure inert gas 5, the coat of metal film are filled with the cavity 4
10 are covered in the outer surface of heat shield 3, and reinforcement 9 is provided with coat of metal film 10, and the polypropylene resin layer 12 connects
Between foam ceramic block 6 and cellular cushion interlayer 13 processed, anti-heat supply network is fixedly connected with the cellular cushion interlayer 13 light
Pad 8, the solar heat protection gauze pad 8 are provided with passage 11 with the contact surface of coat of metal film 10, and the airway tube 14 is arranged on cavity 4
Side.
Wherein, the airway tube 14 is provided with sealing ring 16 with the intraoral side of the contact jaw of column 7, is easy to improve pure inert gas
5 sealings.
Wherein, it is fixedly connected by welding between the bottom of column 7 and load metal shell 1, is easy to keep load gold
Belong to the resistance to overturning of housing 1.
Wherein, described one end of airway tube 14 is provided with valve cock 15, is easy to fill pure inert gas 5.
Wherein, the valve cock 15 is made up of alloy material, conveniently adapts to adverse circumstances.
Wherein, the reinforcement 9 and coat of metal film 10 are formed in one structure, are easy to improve load-bearing dynamics.
It should be noted that the utility model is a kind of compound heat shield of spacecraft, during work, by load metal-back
The periphery of body 1 sets column, and reinforcement 9 is provided with the surface of coat of metal film 10, improves the overall shock resistance energy of heat shield
Power, the coat of metal reduce radiant heat transfer, and reducing heat by the solar heat protection gauze pad 8 between film conducts, and solar heat protection gauze pad 8 and the coat of metal
The passage 11 of the contact surface of film 10 is then to speed up the deflation between multilayer material, discharges interlayer gas flow to reduce to spreading
Heat, gently foam ceramic block 6 processed played a supportive role between heat-insulated pure inert gas 5, polypropylene resin layer 12 and honeycomb
The heatproof heat-resistant of buffer interlayer 13 impacts, and valve cock 15 is made up of alloy material, conveniently adapts to adverse circumstances, this kind of heat shield has
Effect improves anti-thermal effect.
The advantages of general principle and principal character of the present utility model and the utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of the spirit and scope of the utility model is not departed from, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within claimed the scope of the utility model.The utility model
Claimed scope is by appended claims and its equivalent thereof.
Claims (6)
1. a kind of compound heat shield of spacecraft, including load metal shell（1）, light foam ceramic block processed（6）, the coat of metal it is thin
Film（10）, polypropylene resin layer（12）And airway tube（14）, it is characterised in that：The load metal shell（1）Upper surface covers
There is inorganic fibrous mats thermal insulation layer（2）, and load metal shell（1）It has been peripherally installed with column（7）, the light foam ceramic block processed
（6）Uniformly it is fastened on heat shield（3）It is interior, the heat shield（3）Bottom is provided with cavity（4）, the cavity（4）It is interior filled with pure
Net inert gas（5）, the coat of metal film（10）It is covered in heat shield（3）Outer surface, and coat of metal film（10）On
It is provided with reinforcement（9）, the polypropylene resin layer（12）It is connected to light foam ceramic block processed（6）With cellular cushion interlayer
（13）Between, the cellular cushion interlayer（13）On be fixedly connected with solar heat protection gauze pad（8）, the solar heat protection gauze pad（8）With metal-plated
Layer film（10）Contact surface is provided with passage（11）, the airway tube（14）Installed in cavity（4）Side.
A kind of 2. compound heat shield of spacecraft according to claim 1, it is characterised in that：The airway tube（14）With column
（7）The intraoral side of contact jaw is provided with sealing ring（16）.
A kind of 3. compound heat shield of spacecraft according to claim 1, it is characterised in that：The column（7）Bottom is with holding
Power metal shell（1）Between be fixedly connected by welding.
A kind of 4. compound heat shield of spacecraft according to claim 1, it is characterised in that：The airway tube（14）Pacify one end
Equipped with valve cock（15）.
A kind of 5. compound heat shield of spacecraft according to claim 4, it is characterised in that：The valve cock（15）For alloy
Material is made.
A kind of 6. compound heat shield of spacecraft according to claim 4, it is characterised in that：The reinforcement（9）With metal
Plate layer film（10）Be formed in one structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720491315.XU CN206885331U (en) | 2017-05-05 | 2017-05-05 | A kind of compound heat shield of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720491315.XU CN206885331U (en) | 2017-05-05 | 2017-05-05 | A kind of compound heat shield of spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206885331U true CN206885331U (en) | 2018-01-16 |
Family
ID=61341501
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720491315.XU Active CN206885331U (en) | 2017-05-05 | 2017-05-05 | A kind of compound heat shield of spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206885331U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
-
2017
- 2017-05-05 CN CN201720491315.XU patent/CN206885331U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
| CN113978696B (en) * | 2021-11-08 | 2024-04-09 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210429 Address after: 330000 north of Yingxiong Avenue, Nanchang Economic and Technological Development Zone, Nanchang City, Jiangxi Province (office building) (628, 6th floor) Patentee after: NANCHANG HANTIAN SCIENCE & TECHNOLOGY GROUP Co.,Ltd. Address before: 526060, 14 floor, Huijin center, Xinyuan West Road, Duanzhou District, Zhaoqing, Guangdong, Zhaoqing Patentee before: ZHAOQING GUANGYINGKE GENERAL AVIATION Research Institute |