CN111892882A - Graphite film whole-satellite large-area application structure for satellite and satellite - Google Patents
Graphite film whole-satellite large-area application structure for satellite and satellite Download PDFInfo
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- CN111892882A CN111892882A CN202010779084.9A CN202010779084A CN111892882A CN 111892882 A CN111892882 A CN 111892882A CN 202010779084 A CN202010779084 A CN 202010779084A CN 111892882 A CN111892882 A CN 111892882A
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- Prior art keywords
- satellite
- application structure
- graphite film
- film
- graphite
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
- C09J7/00—Adhesives in the form of films or foils
- C09J7/20—Adhesives in the form of films or foils characterised by their carriers
- C09J7/29—Laminated material
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/506—Heat pipes
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
- C09J2400/00—Presence of inorganic and organic materials
- C09J2400/10—Presence of inorganic materials
-
- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
- C09J2479/00—Presence of polyamine or polyimide
- C09J2479/08—Presence of polyamine or polyimide polyimide
- C09J2479/086—Presence of polyamine or polyimide polyimide in the substrate
Abstract
The invention provides a graphite film whole satellite large-area application structure for a satellite and the satellite, comprising: a first polyimide film 1, a graphite film 2, and a second polyimide film 3; the graphite film 2 is disposed between the first polyimide film 1 and the second polyimide film 3, and is vacuum-sealed by the first polyimide film 1 and the second polyimide film 3. The invention solves the problem of large-area application of the graphite film on the satellite, and has the advantages of strong adaptability, simple implementation, high reliability and the like.
Description
Technical Field
The invention relates to a temperature control system of a space vehicle, in particular to a light high-heat-conductivity graphite film whole satellite large-area application structure for a satellite and the satellite.
Background
In recent years, the satellite is developed towards miniaturization, light weight and batch, the function of the load is increasingly complicated, the heat consumption of a single machine is increasingly large, and the traditional thermal control design scheme cannot meet the thermal control requirement of the satellite. The present satellites are various in types, shapes and uses, wide in distribution orbit range, and large in illumination condition and external heat flow change. The thermal control design needs to meet the temperature requirements of the satellite and the load under different working modes under the conditions of illumination on each orbit surface and external heat flow.
The illumination condition of part of satellites is complex, the change of external heat flow is large, all side surfaces are illuminated in turn, fixed radiating surfaces are not provided, and all radiating surfaces need to be thermally coupled to prevent the single machine on the cabin plate from being overhigh in temperature when a single radiating surface is directly illuminated by the sun. At present, the requirement for light weight of a satellite is higher and higher, the traditional thermal control products are often overlarge in quality (such as heat pipes, radiation plates and heat spreading plates), and the traditional heat spreading plates cannot realize reliable flexible connection between cabin plates and far cannot meet the requirements for quality and reliability of the thermal control system by the satellite.
The graphite film is a novel heat dissipation material, and has high thermal conductivity (more than 900W/(m.K)) and low density (0.2 kg/m)2) And the super-flexibility characteristic, the heat dissipation film has been applied to the heat dissipation field of civil electronic products, and has a huge application prospect in the field of spacecrafts. But the graphite film has poor mechanical property, is easy to remove slag, has difficulty in large-area adhesion, and greatly limits the application of the graphite film in the aerospace field. Therefore, a method for implementing a process for solving the problem of large-area application of graphite films on satellites is needed.
The prior patent document CN107311661A discloses a composite graphite film, and a preparation method and an application thereof, and the technical research direction is mainly the preparation method of the graphite film, but the prior documents of practical application and using methods relate to a small amount.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a graphite film whole satellite large-area application structure for a satellite and the satellite.
The invention provides a graphite film whole satellite large-area application structure for a satellite, which comprises: a first polyimide film 1, a graphite film 2, and a second polyimide film 3;
the graphite film 2 is disposed between the first polyimide film 1 and the second polyimide film 3, and is vacuum-sealed by the first polyimide film 1 and the second polyimide film 3.
Preferably, the second polyimide film 3 is used as a mounting surface, and a silicone back adhesive 4 is arranged on the surface.
Preferably, the whole satellite large-area application structure of the graphite film for the satellite is provided with openings in any shapes, and edges of the openings are sealed.
Preferably, the second polyimide film 3 is fixed on the surface to be bonded with the aid of a paper tape or a glass fiber pressure sensitive tape.
Preferably, the number of the bubbles between the whole satellite large-area application structure and the veneered surface of the graphite film for the satellite is not more than 5, and the size of the bubbles is less than 5mm multiplied by 5 mm.
Preferably, the plurality of bubbles are not connected to each other in a sheet.
Preferably, the number of the graphite films 2 is one or more, and the graphite films 2 are mutually lapped and spliced.
The satellite provided by the invention comprises the graphite film whole satellite large-area application structure for the satellite.
Preferably, the graphite film whole satellite large-area application structure for the satellite is adhered to an adjacent structural plate, a heat pipe area or a single machine installation surface of the satellite.
Preferably, the heat pipe area comprises an embedded or externally attached heat pipe area.
Compared with the prior art, the invention has the following beneficial effects:
(1) the graphite film is vacuum-packaged by the polyimide film, so that the graphite film is slag-dropping-proof, bubble-free, adaptive to space environment and high in reliability.
(2) The organic silicon back adhesive is arranged on the mounting surface, so that reliable and rapid pasting in a large temperature area can be realized, the organic silicon pressure sensitive adhesive can be used for a long time at the temperature of-73-296 ℃, the bonding strength and flexibility of the organic silicon pressure sensitive adhesive are still kept at high temperature and low temperature, the organic silicon pressure sensitive adhesive has good chemical inertia, long service life, outstanding moisture resistance and electrical property, acid-base corrosion resistance and ageing resistance, the defects of insufficient temperature resistance range and on-orbit reliability of the traditional pressure sensitive adhesive can be overcome, the organic silicon back adhesive can be reliably and rapidly pasted in the large temperature area, and the quick development requirement of small satellites is met.
(3) The graphite films are reliably overlapped and spliced in the large-area sticking area, and flexible and efficient thermal coupling between the cabin plates is realized.
(4) The surface of the graphite film can be perforated in any shape in advance and then is subjected to vacuum packaging, so that single machine mounting holes, cabin plate holes, operation windows and the like can be completely avoided, and interference is avoided.
(5) Compared with the traditional heat spreading plate, the heat spreading plate can meet the light weight requirement of a small satellite.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural diagram of a graphite film whole satellite large-area application structure for a satellite;
fig. 2 is a schematic diagram of a graphite film pasting structure for a satellite with a large area.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the graphite thin film whole satellite large-area application structure for a satellite provided by the invention comprises: a first polyimide film 1, a graphite film 2, and a second polyimide film 3. The graphite film 2 is arranged between the first polyimide film 1 and the second polyimide film 3, and is vacuum-packaged by the first polyimide film 1 and the second polyimide film 3. The second polyimide film 3 is used as a mounting surface, and the surface is provided with an organic silicon back adhesive 4.
In order to ensure the pasting quality, the auxiliary fixing on the pasted surface is allowed to be carried out by using a paper tape or a glass fiber pressure sensitive adhesive tape. The number of the bubbles between the whole satellite large-area application structure and the veneered surface of the graphite film for the satellite is not more than 5, the size of the bubbles is less than 5mm multiplied by 5mm, and a plurality of bubbles are not connected into a piece. When the area of the veneered area exceeds the maximum width of the graphite film, the multiple graphite films can be mutually lapped and spliced. The whole satellite large-area application structure of the graphite film for the satellite is provided with openings in any shape, and the edges of the openings are sealed.
As shown in fig. 2, the whole satellite large-area application structure of the graphite film for the satellite can be adhered to a satellite structure plate and a single-machine installation surface in a large area, and the oblique line area in the figure is the whole satellite large-area application structure of the graphite film for the satellite. The graphite film is adhered to the adjacent structural plates of the satellite, so that the thermal coupling between the cabin plates can be enhanced; the graphite film is adhered to the pre-embedded or externally-adhered heat pipe area 5, so that a whole star heat pipe network can be formed, and the heat exchange effect is enhanced; the graphite film is pasted on the single machine mounting surface, so that heat can be dispersed, heat dissipation is assisted, the temperature of the single machine is reduced, attention is paid to the fact that single machine mounting holes need to be reserved before packaging, and the edges of the holes are sealed during packaging.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A graphite film whole-satellite large-area application structure for a satellite is characterized by comprising: a first polyimide film (1), a graphite film (2) and a second polyimide film (3);
the graphite film (2) is arranged between the first polyimide film (1) and the second polyimide film (3) and is packaged in a vacuum mode through the first polyimide film (1) and the second polyimide film (3).
2. The graphite film whole satellite large-area application structure for the satellite according to claim 1, wherein the second polyimide film (3) is used as a mounting surface, and a silicone back adhesive (4) is arranged on the surface.
3. The whole satellite large-area application structure of graphite film for satellite according to claim 1, wherein the whole satellite large-area application structure of graphite film for satellite is provided with openings of any shape, and edges of the openings are sealed.
4. The graphite film whole satellite large-area application structure for the satellite according to claim 1, wherein the second polyimide film (3) is fixed on the adhered surface by paper tape or glass fiber pressure sensitive tape.
5. The whole satellite large-area application structure of graphite film for satellite according to claim 1, wherein the number of air bubbles between the whole satellite large-area application structure of graphite film for satellite and the veneered surface is not more than 5, and the size of the air bubbles is less than 5mm x 5 mm.
6. The satellite graphite film whole satellite large area application structure of claim 5, wherein the plurality of air bubbles are not connected to each other.
7. The whole satellite large-area application structure of graphite thin films for satellites as claimed in claim 1 is characterized in that the number of the graphite thin films (2) is one or more, and the graphite thin films (2) are spliced with each other.
8. A satellite comprising the graphite film whole satellite large-area application structure for a satellite according to any one of claims 1 to 7.
9. The satellite of claim 8, wherein the graphite film whole satellite large area application structure for the satellite is adhered to an adjacent structural plate, a heat pipe area or a single machine installation surface of the satellite.
10. The satellite of claim 9, wherein the heat pipe region comprises a pre-buried or externally attached heat pipe region.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010779084.9A CN111892882A (en) | 2020-08-05 | 2020-08-05 | Graphite film whole-satellite large-area application structure for satellite and satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010779084.9A CN111892882A (en) | 2020-08-05 | 2020-08-05 | Graphite film whole-satellite large-area application structure for satellite and satellite |
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| Publication Number | Publication Date |
|---|---|
| CN111892882A true CN111892882A (en) | 2020-11-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010779084.9A Pending CN111892882A (en) | 2020-08-05 | 2020-08-05 | Graphite film whole-satellite large-area application structure for satellite and satellite |
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| CN (1) | CN111892882A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114537719A (en) * | 2022-01-14 | 2022-05-27 | 上海卫星工程研究所 | Multifunctional flexible satellite structure and processing method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103193222A (en) * | 2007-05-17 | 2013-07-10 | 株式会社钟化 | Graphite film and graphite composite film |
| CN107031137A (en) * | 2017-04-01 | 2017-08-11 | 北京空间飞行器总体设计部 | A kind of high heat conduction device and preparation method thereof |
-
2020
- 2020-08-05 CN CN202010779084.9A patent/CN111892882A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103193222A (en) * | 2007-05-17 | 2013-07-10 | 株式会社钟化 | Graphite film and graphite composite film |
| CN107031137A (en) * | 2017-04-01 | 2017-08-11 | 北京空间飞行器总体设计部 | A kind of high heat conduction device and preparation method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 吕百龄 等主编: "《实用橡胶手册》", 31 July 2001, 化学工业出版社 * |
| 方汉中 主编: "《世界建筑材料 发展水平和趋势》", 30 April 1989, 科学普及出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114537719A (en) * | 2022-01-14 | 2022-05-27 | 上海卫星工程研究所 | Multifunctional flexible satellite structure and processing method thereof |
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Application publication date: 20201106 |