CN114084380A - Inflatable expansion type flexible heat radiator for spacecraft - Google Patents
Inflatable expansion type flexible heat radiator for spacecraft Download PDFInfo
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- CN114084380A CN114084380A CN202111051969.8A CN202111051969A CN114084380A CN 114084380 A CN114084380 A CN 114084380A CN 202111051969 A CN202111051969 A CN 202111051969A CN 114084380 A CN114084380 A CN 114084380A
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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
- B64G1/503—Radiator panels
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- Aviation & Aerospace Engineering (AREA)
- Rigid Pipes And Flexible Pipes (AREA)
Abstract
An inflatable unfolding type flexible heat radiator for a spacecraft belongs to the technical field of thermal control of the spacecraft. The invention comprises an inflatable frame, two flexible radiation films, a rigid-flexible combined pipeline or a fully flexible serial pipeline and a rigid connecting piece; the flexible radiation device comprises two flexible radiation films, a rigid-flexible combined pipeline or a fully-flexible serial pipeline is arranged between the two flexible radiation films in a stacked mode, the two flexible radiation films are bonded with the rigid-flexible combined pipeline or the fully-flexible serial pipeline through a heat conduction adhesive, a rigid connecting piece is fixedly connected with one end of each flexible radiation film and the rigid-flexible combined pipeline or the fully-flexible serial pipeline, and the inflatable frame is bonded with the edges of the two flexible radiation films except the one end of each flexible radiation film. The invention is made of flexible composite material, is in a folded state before launching, is inflated and unfolded into a large-area radiator after being put into orbit, and has the characteristics of light weight, high folding efficiency, small launching volume, low launching cost, easiness in launching, high rigidity, large heat dissipation area, high heat dissipation power and the like.
Description
Technical Field
The invention belongs to the technical field of thermal control of spacecrafts, and particularly relates to an inflatable expanded flexible heat radiator for a spacecraft.
Background
The heat radiator is an important component of a heat removal system of the spacecraft, and most of the current spacecrafts adopt a self-covering or a rigid heat dissipation plate as the radiator so as to realize heat exchange with the space environment. With the development of space technology such as manned spacecraft and space station, the spacecraft has more and more functions and larger scale, which inevitably leads to the continuous increase of thermal power, and brings great challenge to the heat radiation performance of the heat radiator. Because of the limitation of the size, the launching load and the launching envelope of the spacecraft, the radiator which is made of the skin or the rigid radiating plate has the defects of heavy mass, small radiating area, high launching cost, high launching difficulty and the like, and the requirement of high-power heat extraction of the future spacecraft is difficult to meet.
Disclosure of Invention
The invention aims to provide an inflatable expansion type flexible heat radiator for a spacecraft aiming at the requirement of high-power heat extraction of the spacecraft, which has the characteristics of obviously increased radiation area, flexibility, folding property, light weight, small emission volume, low emission cost, high rigidity, high vibration fundamental frequency, space environment resistance, high heat radiation power and the like compared with the traditional heat radiator.
In order to achieve the purpose, the invention adopts the following technical scheme:
an inflatable unfolding type flexible heat radiator for a spacecraft comprises an inflatable frame, two flexible radiation films, a rigid-flexible combined pipeline or a fully-flexible serial pipeline and a rigid connecting piece; the flexible radiation device comprises two flexible radiation films, a rigid-flexible combined pipeline or a fully-flexible serial pipeline, wherein the two flexible radiation films are stacked, the rigid-flexible combined pipeline or the fully-flexible serial pipeline is arranged between the two flexible radiation films, the two flexible radiation films are bonded with the rigid-flexible combined pipeline or the fully-flexible serial pipeline through a heat conduction adhesive, a rigid connecting piece is fixedly connected with one end of each flexible radiation film and the rigid-flexible combined pipeline or the fully-flexible serial pipeline, and the inflatable frame is bonded with the edges of the two flexible radiation films except the one end.
Compared with the prior art, the invention has the beneficial effects that:
1. the inflatable expansion type flexible heat radiator for the spacecraft is made of flexible composite materials, is in a folded state before launching, is inflated and expanded into a large-area radiator after being in orbit, and has the characteristics of light weight, high folding efficiency, small launching volume, low launching cost, easiness in launching, high rigidity, large heat dissipation area, high heat dissipation power and the like.
2. The inflatable frame is made of inflatable unfolding support pipes, the pipe walls are made of multiple layers of flexible composite materials, and the support pipe airtight layer, the support pipe electric heating layer and the support pipe rigidizing layer are sequentially arranged from inside to outside, so that the inflatable frame can be flexibly folded and launched, and the launching volume is small.
3. The inflatable frame can be inflated and expanded, and drives the flexible heat radiator to be expanded and formed. The inflatable frame is formed in a rigidized mode after being unfolded, the rigidity of the structure is high after the rigidization, support is provided for the unfolded flexible radiator, and the structural rigidity and the vibration fundamental frequency of the radiator are improved.
4. The inflatable unfolding type flexible heat radiator is driven to unfold in an inflatable mode, and the unfolding mode is simple, reliable and easy to realize.
5. The control of the unfolding process of the radiator can be realized by controlling the flow velocity and the flow of the inflation gas of the inflation frame, and the control mode is simple and reliable.
6. The supporting tube air-tight layer is made of a gas barrier film, has good gas barrier performance and can ensure that the inflatable frame is smoothly unfolded and molded.
7. The electric heating layer of the supporting tube is formed by electric heating wires, and can electrically heat the inflatable expanding supporting tube to enable the inflatable expanding supporting tube to be rigid. The rigidization mode is simple, controllable and reliable.
8. The inflatable supporting tube is of a thin-wall round tube structure, can be inflated, unfolded, formed and rigidized, and has a large sectional area, high rigidity after rigidization and light weight.
9. The flexible radiation film comprises two flexible radiation films which are bonded through a heat-conducting adhesive, and a plurality of U-shaped flexible pipelines or full-flexible serial pipelines which are arranged in parallel are wrapped between the two flexible radiation films through the heat-conducting adhesive, so that the U-shaped flexible pipelines or the full-flexible serial pipelines can be fully contacted with the flexible radiation films, and a good heat transfer effect is achieved.
10. The U-shaped flexible pipeline or the full-flexible serial pipeline is made of multiple layers of flexible composite materials, and sequentially comprises a flexible pipeline air-tight layer and a flexible pipeline bearing layer from inside to outside, so that the U-shaped flexible pipeline or the full-flexible serial pipeline has the advantages of flexibility, folding property, good liquid barrier property, corrosion resistance, high pressure bearing, high heat conduction and the like, can be kept at 50 ℃ for a long time, is kept stable under the condition of contacting with working fluid, and is impermeable to steam generated by the working fluid.
11. The flexible pipeline airtight layer is made of silicon rubber, and the silicon rubber can be subjected to material modification by adding carbon black or graphite, so that the flexible pipeline airtight layer has the advantages of flexibility, folding resistance, corrosion resistance, good heat-conducting property and the like.
12. The bearing layer of the flexible pipeline is woven by fiber materials, has the characteristics of high modulus, high strength and the like, and can adopt resin adhesive with high heat transfer performance to carry out gum dipping heat transfer modification on the fibers so as to improve the heat transfer performance of the fibers.
13. The rigid-flexible combined pipeline comprises a plurality of U-shaped flexible pipelines, a plurality of T-shaped pipes and two main pipelines, the U-shaped flexible pipelines are sleeved from inside to outside to form a parallel structure, and the rigid-flexible combined pipeline has the advantages of simple structure, few joints, high structural reliability, easiness in processing, light weight, easiness in folding, short flow, low pipeline pressure head, high average temperature, high heat exchange efficiency and the like.
14. The rigid connection is located at the end of the flexible radiator to facilitate folding and packaging of the flexible radiator in the length direction.
Drawings
Fig. 1 is a front view of an inflatable deployment flexible heat radiator for a spacecraft of the present invention;
FIG. 2 is a schematic view of the structure of the inflatable deployment support tube;
FIG. 3 is a schematic structural view of a flexible pipe;
FIG. 4 is a schematic structural view of a rigid-flexible composite pipe;
FIG. 5 is a schematic diagram of the construction of a fully flexible looped tandem conduit;
fig. 6 is a schematic structural diagram of a fully flexible rectangular tandem pipeline.
The names and reference numbers of the components referred to in the above figures are as follows:
the flexible radiation type pipeline comprises an inflatable frame 1, two flexible radiation films 2, a rigid-flexible combined pipeline 3, a rigid connecting piece 4, a main pipeline 5, an inflatable expansion supporting pipe 6, a supporting pipe airtight layer 7, a supporting pipe electric heating layer 8, a supporting pipe rigidizing layer 9, a flexible pipeline 10, a flexible pipeline airtight layer 11, a flexible pipeline bearing layer 12, a fluid inlet 13, a fluid outlet 14, a T-shaped pipe 15, a fully flexible rectangular serial pipeline 16 and a fully flexible annular serial pipeline 17.
Detailed Description
The first embodiment is as follows: as shown in fig. 1 to 6, the present embodiment discloses an inflatable unfolding flexible heat radiator for spacecraft, which comprises an inflatable frame 1, two flexible radiation films 2, a rigid-flexible combined pipeline 3 or a fully flexible serial pipeline, and a rigid connecting piece 4; the two flexible radiation films 2 are stacked, a rigid-flexible combined pipeline 3 or a full-flexible series pipeline is arranged between the two flexible radiation films 2, the two flexible radiation films 2 are bonded with the rigid-flexible combined pipeline 3 or the full-flexible series pipeline through a heat conduction adhesive, the rigid connecting piece 4 is fixedly connected with one end of each flexible radiation film 2 and the rigid-flexible combined pipeline 3 or the full-flexible series pipeline (the flexible heat radiator can be conveniently folded in the length direction, the two flexible radiation films 2 are preferably rectangular in shape), and the inflatable frame 1 (adopting the adhesive) is bonded with the edges of the two flexible radiation films 2 except for one end.
The rigid-flexible combined pipeline 3 or the fully-flexible serial pipeline has the advantages of simple structure, few joints, high structural reliability, easiness in processing, light weight, easiness in folding, short flow, low pipeline pressure head, high average temperature, high heat exchange efficiency and the like.
The second embodiment is as follows: as shown in fig. 1, fig. 3 and fig. 4, the present embodiment is further described with respect to a first embodiment, in which the rigid-flexible combined pipe 3 includes a plurality of U-shaped flexible pipes 10, two main pipes 5 and a plurality of T-shaped pipes 15; the U-shaped flexible pipelines 10 are sequentially sleeved from inside to outside to form a parallel structure, two ends of each U-shaped flexible pipeline 10 are communicated with the corresponding main pipeline 5 through T-shaped pipes 15 (the U-shaped flexible pipelines 10 are wrapped, the U-shaped flexible pipelines 10 are fully contacted with the flexible radiation film 2, so that the U-shaped flexible pipelines have a good heat transfer effect), the two main pipelines 5 are arranged in the two flexible radiation films 2 in a 'I' shape, one main pipeline 5 is provided with a fluid inlet 13, and the other main pipeline 5 is provided with a fluid outlet 14.
The third concrete implementation mode: as shown in fig. 5 and fig. 6, this embodiment is further described as a first embodiment, the fully flexible serial pipeline is a fully flexible rectangular serial pipeline 16 or a fully flexible annular serial pipeline 17, and the two ends of the fully flexible serial pipeline are respectively a fluid inlet 13 and a fluid outlet 14.
The fourth concrete implementation mode: as shown in fig. 1 and fig. 2, in this embodiment, a first embodiment, a second embodiment, or a third embodiment is further described, the inflatable frame 1 is U-shaped, the inflatable frame 1 is formed by an inflatable expanding support tube 6 (which can assist the flexible heat radiator to expand and form), a tube wall of the inflatable expanding support tube 6 is made of multiple layers of flexible composite materials, and a support tube airtight layer 7, a support tube electric heating layer 8, and a support tube rigid layer 9 are sequentially arranged on the tube wall of the inflatable expanding support tube 6 from inside to outside.
The fifth concrete implementation mode: as shown in fig. 2, this embodiment is further described with respect to the fourth embodiment, in which the support tube air-tight layer 7 is made of a (good gas barrier) film material (such as polyimide, EVOH (ethylene vinyl alcohol copolymer) or PVDC (polyvinylidene chloride) for maintaining the air-tightness of the inflatable expansion support tube 6 and ensuring smooth expansion molding thereof); the support tube electric heating layer 8 is made of electric heating wires (can electrically heat the inflatable expansion support tube 6 to enable the inflatable expansion support tube to be rigid); the supporting tube rigidizing layer 9 is made of a rigidizable thermosetting resin material (can be heated and rigidized by an electric heating wire after being inflated and unfolded for molding).
The sixth specific implementation mode: as shown in fig. 1, this embodiment is further explained with respect to the first embodiment, the flexible radiation film 2 (which is the main heat dissipation area of the radiator) is made of a (high-radiation, low-absorption, flexible, folding-resistant) film material (such as a polyimide film), and the surface of the film is coated with a high-radiation performance coating (such as a ceramic radiation coating) resistant to the space environment.
The seventh embodiment: as shown in fig. 3, this embodiment is a further description of a second embodiment, a pipe wall material of the U-shaped flexible pipe 10 is made of multiple layers of flexible composite materials, and a flexible pipe airtight layer 11 and a flexible pipe force-bearing layer 12 are sequentially arranged on the pipe wall of the U-shaped flexible pipe 10 from inside to outside; the flexible pipeline air-tight layer 11 is made of silicon rubber, and the flexible pipeline bearing layer 12 is woven by fiber materials.
The flexible pipeline air-tight layer 11 is used for blocking fluid in a pipeline, maintaining the sealing of the U-shaped flexible pipeline 10, preventing fluid permeation and the like, is made of flexible, folding-resistant and corrosion-resistant silicon rubber, and can be subjected to material modification (the volume fraction of the carbon black or graphite filler is 15% -25%) by adding the carbon black or graphite filler, so that the heat-conducting property of the flexible pipeline air-tight layer is improved.
The flexible pipeline bearing layer 12 is a key part of the U-shaped flexible pipeline 10 for bearing fluid pressure, is woven by high-modulus and high-strength fiber materials such as aramid fibers, and can be modified by dipping the aramid fibers by high-heat-transfer-performance resin adhesive to improve the heat transfer performance of the fibers.
The specific implementation mode is eight: as shown in fig. 3, fig. 5 and fig. 6, the third embodiment is further described, wherein the pipe wall material of the fully flexible rectangular serial pipe 16 or the fully flexible annular serial pipe 17 is made of multiple layers of flexible composite materials, and the flexible pipe airtight layer 11 and the flexible pipe force-bearing layer 12 are sequentially arranged from inside to outside; the flexible pipeline air-tight layer 11 is made of silicon rubber, and the flexible pipeline bearing layer 12 is woven by fiber materials.
The specific implementation method nine: as shown in fig. 1 and 4, in this embodiment, a first embodiment is further described, in which the main pipe 5 and the T-shaped pipe 15 of the rigid-flexible combined pipe 3 are both rigid pipes and are made of carbon fiber composite materials or metal materials.
The invention is mainly used for radiating the spacecraft in the space environment, the spacecraft is launched after being folded and packaged, the flexible radiation film 2 and the U-shaped flexible pipeline 10 or the fully flexible serial pipeline are driven to be unfolded and formed by the inflatable frame 1 after the spacecraft enters the orbit and is inflated into the inflatable frame 1 by the gas cylinder. After the expansion forming, the support tube electric heating layer in the side wall of the inflatable frame 1 is used for heating the inflatable frame, so that the inflatable frame 1 is stiffened, the flexible heat radiator can be supported without inflation pressure, and the structural rigidity is improved. At this time, working fluid is input to the fluid inlet of the U-shaped flexible pipeline 10 or the fully flexible serial pipeline, and heat on the spacecraft is transferred to the flexible radiation film 2 through the U-shaped flexible pipeline 10 of the parallel structure or the fully flexible serial pipeline connected in series and radiated to the space environment, so that heat exchange with the space environment is realized, and a good heat dissipation effect is achieved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention, and the present invention is not limited thereto, and any person skilled in the art can substitute or change the technical solution of the present invention and its inventive concept within the technical scope of the present invention.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111051969.8A CN114084380B (en) | 2021-09-08 | 2021-09-08 | Inflatable expansion type flexible heat radiator for spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111051969.8A CN114084380B (en) | 2021-09-08 | 2021-09-08 | Inflatable expansion type flexible heat radiator for spacecraft |
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| Publication Number | Publication Date |
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| CN114084380A true CN114084380A (en) | 2022-02-25 |
| CN114084380B CN114084380B (en) | 2024-08-13 |
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| CN202111051969.8A Active CN114084380B (en) | 2021-09-08 | 2021-09-08 | Inflatable expansion type flexible heat radiator for spacecraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114852378A (en) * | 2022-03-31 | 2022-08-05 | 北京空间飞行器总体设计部 | Deployable heat radiator based on single-phase fluid circuit |
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| CN207360608U (en) * | 2017-09-21 | 2018-05-15 | 上海卫星工程研究所 | Spacecraft folding multilayer heat screen |
| CN109279051A (en) * | 2017-07-23 | 2019-01-29 | 北京遥感设备研究所 | An adaptive variable radiation area thermal control device |
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2021
- 2021-09-08 CN CN202111051969.8A patent/CN114084380B/en active Active
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|---|---|---|---|---|
| US4813476A (en) * | 1987-10-21 | 1989-03-21 | The United States Of America As Represented By The Secretary Of The Air Force | Expandable pulse power spacecraft radiator |
| US4842045A (en) * | 1988-10-11 | 1989-06-27 | The United States Of America As Represented By The Secretary Of The Air Force | Expandable radiator |
| US6439297B1 (en) * | 1996-07-31 | 2002-08-27 | Matra Marconi Space Uk Limited | Deployable radiators for spacecraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114852378A (en) * | 2022-03-31 | 2022-08-05 | 北京空间飞行器总体设计部 | Deployable heat radiator based on single-phase fluid circuit |
| CN114852378B (en) * | 2022-03-31 | 2024-05-24 | 北京空间飞行器总体设计部 | Deployable heat radiator based on single-phase fluid circuit |
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| CN114084380B (en) | 2024-08-13 |
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