CN205366109U - Control outer thermal current barn door device - Google Patents
Control outer thermal current barn door device Download PDFInfo
- Publication number
- CN205366109U CN205366109U CN201520786691.2U CN201520786691U CN205366109U CN 205366109 U CN205366109 U CN 205366109U CN 201520786691 U CN201520786691 U CN 201520786691U CN 205366109 U CN205366109 U CN 205366109U
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- column
- lock body
- connector
- multilayer insulation
- join domain
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Abstract
The utility model provides a control outer thermal current barn door device, including first stand, second stand and multi -layer insulation component, wherein, multi -layer insulation component's one end is connected first stand, the other end is connected the second stand, a connection zone, multi -layer insulation component main part and the 2nd connection zone that multi -layer insulation component links to each other including the order, a connection zone is provided with first connecting piece and detains the body and first connecting piece lock body, first connecting piece is detained the body and is wound connect after the rotatory a week of first stand first connection lock body, the 2nd connection zone is provided with the second connecting piece and detains the body and second connecting piece lock body, the second connecting piece is detained the body and is wound connect after the rotatory a week of second stand the lock body is connected to the second. The utility model discloses the structure is simple and easy, and is with low costs, only needs multilayer multi -layer insulation component and carbon fiber material stand, polyamide fibre line and hasp just can reach the effect that reduces outer thermal current.
Description
Technical field
This utility model relates to Space Facilities, reduces, in particular it relates to a kind of, the device that Orbital heat flux affects for space unit temperature.
Background technology
Due to the needs of design in spacecraft development process, part system is arranged on satellite towards terrace, and major part parts are directly exposed to outside celestial body, and thermal environment is extremely complex.Need the thermal design of space unit parts is taked Optimized Measures, improve temperature distribution state, it is ensured that normal operation in-orbit.For space unit thermal design, the factor affecting its temperature levels is mainly made up of Orbital heat flux and unit self heat consumption.In track running, it is subject to the cold black heat sink alternately heating of solar radiation, earth infra-red radiation and the earth sunlight reflection of light and space and cooling.Unit surface, space each several part accepts the inhomogeneities and over time of radiations heat energy, will result in the uneven of its surface temperature distribution and fluctuation.When operating attitude changes, the part towards the sun can produce the huge temperature difference with the part being in sun shade；The change of temperature is very big to the performance impact of space unit, and meanwhile, thermal agitation produced by the thermal source within the unit of space also influences whether the performance of space unit.The performance of space unit is produced different impacts by various forms of Temperature Distribution.Homogeneous temperature field is changed, material Proper Match can be passed through and without thermalized design, reduce its impact on performance as far as possible；Thermograde is on the impact of performance not only complexity but also is difficult to control to, it is necessary to carries out correlation analysis for concrete temperature environment, and adopts effective temperature control means.
Present space unit development trend is that volume is big, configuration is complicated, heat consumption is big.In order to meet the performance requirement of space unit, anti-increasing does not drop in the heat consumption of important unit, it is necessary to the optimization design that takes appropriate measures reduces the Orbital heat flux impact for space unit.Meet the demand reducing Orbital heat flux now by general method and be difficult to meet the needs of design, it is necessary to find new approach to solve the Orbital heat flux problem of space unit.
The mode being presently used for reducing Orbital heat flux mainly has:
1, cell surface spraying S781 white paint thermal control coating.Which thermal control measure is simple, but when surface is irradiated by sunlight, performance degradation is fast.Thus be only applicable to be sprayed at the cell surface being in opaco.
2, cell surface pastes OSR thermal control coating.Which thermal control measure is complicated, and the planarity requirements for adhesive surface is high, and self is brittle and fragile, need to perform safeguard procedures.Thus it is only applicable to the cell surface of surfacing.
3, cell surface cladding multilamellar.Which thermal control measure is simple, but has also completely cut off the passage of heat radiation while having completely cut off Orbital heat flux.Thus it is only applicable to the cell surface of sunlight long-term irradiation.
Utility model content
For defect of the prior art, the purpose of this utility model is to provide a kind of control Orbital heat flux light barrier device.
According to the control Orbital heat flux light barrier device that this utility model provides, including the first column, the second column and multilayer insulation assembly；
Wherein, one end of described multilayer insulation assembly connects described first column, and the other end connects described second column；
Described multilayer insulation assembly includes the first join domain, multilayer insulation module body and the second join domain that order is connected；
Described first join domain is provided with the first connector button and the first connector lock body；Described first connector button connects described first after described first column rotates a circle and connects lock body；
Described second join domain is provided with the second connector button and the second connector lock body；Described second connector button connects described second after described second column rotates a circle and connects lock body.
Preferably, the first connecting line and the second connecting line are also included；Described first join domain is provided with multiple first string holes；Described first string holes is arranged between described first connector button and the first connector lock body；
It is connected by the first connecting line between multiple first string holes, thus the first join domain connects the cylinder of described first column；
Described second join domain is provided with multiple second string holes；Described second string holes is arranged between described second connector button and the second connector lock body；
It is connected by the second connecting line between multiple second string holes, thus the second join domain connects the cylinder of described second column.
Preferably, described multilayer insulation assembly includes the multilayer insulation unit that multilamellar is fitted successively；
Described multilayer insulation unit includes two-sided aluminized mylar and terylene mesh；Described two-sided aluminized mylar is fitted and connected described terylene mesh.
Preferably, described first column and described second column adopt carbon fibre material to make；
Described first connecting line and described second connecting line adopt chinlon line.
Preferably, thermal control coating is also included；The both side surface of described multilayer insulation assembly is provided with thermal control coating.
Preferably, described thermal control coating adopts the silver-plated second surface mirror thermal control coating of conductivity type F46 thin film of 50 μm.
Preferably, described first connector button and described second connector button adopt soft hasp；Described first connector lock body and described second connector lock body adopt hard hasp.
Compared with prior art, this utility model has following beneficial effect:
1, this utility model simple structure, cost is low, it is only necessary to multilamellar multilayer insulation assembly and carbon fibre material column, chinlon line and hasp just can reach to reduce the effect of Orbital heat flux；
2, this utility model reliability is high, is absent from starting, terminating and Problem of Failure；
3, this utility model light blocking is effective, adopts multilamellar multilayer insulation assembly isolation sunlight for the impact of space unit, meets the needs of thermal control design.
Accompanying drawing explanation
By reading detailed description non-limiting example made with reference to the following drawings, other features, objects and advantages of the present utility model will become more apparent upon:
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the structural representation of multilayer insulation assembly in this utility model.
In figure:
1 is the first column；
2 is multilayer insulation assembly；
3 is the second string holes；
4 is the second column；
5 is hard hasp；
6 is the first string holes；
7 is soft hasp.
Detailed description of the invention
Below in conjunction with specific embodiment, this utility model is described in detail.Following example will assist in those skilled in the art and are further appreciated by this utility model, but do not limit this utility model in any form.It should be pointed out that, to those skilled in the art, without departing from the concept of the premise utility, it is also possible to make some deformation and improvement.These broadly fall into protection domain of the present utility model.
In the present embodiment, the control Orbital heat flux light barrier device that this utility model provides, including the first column the 1, second column 4 and multilayer insulation assembly 2；Wherein, one end of described multilayer insulation assembly 2 connects described first column 1, and the other end connects described second column 4；Described multilayer insulation assembly 2 includes the first join domain, multilayer insulation module body and the second join domain that order is connected；Described first join domain is provided with the first connector button and the first connector lock body；Described first connector button connects described first after described first column 1 rotates a circle and connects lock body；Described second join domain is provided with the second connector button and the second connector lock body；Described second connector button connects described second after described second column 4 rotates a circle and connects lock body.In the present embodiment, described first connector button and described second connector button adopt soft hasp 5；Described first connector lock body and described second connector lock body adopt hard hasp 7.Described first join domain is provided with multiple first string holes 6；Described first string holes 6 is arranged between described first connector button and the first connector lock body；It is connected by the first connecting line between multiple first string holes 6, thus the first join domain connects the cylinder of described first column 1；Described second join domain is provided with multiple second string holes 3；Described second string holes 3 is arranged between described second connector button and the second connector lock body；It is connected by the second connecting line between multiple second string holes 3, thus the second join domain connects the cylinder of described second column 4.Described first column 1 and described second column 4 adopt carbon fibre material to make；Described first connecting line and described second connecting line adopt chinlon line.In the present embodiment, specifically, described multilayer insulation assembly 2 is fixed on the outer surface of carbon fibre material column by hasp and chinlon line by chinlon string holes.First soft hasp is around left side the first column 1 and the first hard hasp lap, and chinlon line is fastened by the first string holes 6 on the first column 1；Second soft hasp is around right side the second column 4 and the second hard hasp lap, and chinlon line is fastened by the second string holes 3 on the second column 1.
Described multilayer insulation assembly 2 includes the multilayer insulation unit that multilamellar is fitted successively；In the present embodiment, described multilayer insulation assembly 2 includes 20 layers of multilayer insulation unit fitted successively.Described multilayer insulation unit includes two-sided aluminized mylar and the terylene mesh of 6 μ m-thick；Described two-sided aluminized mylar is fitted and connected described terylene mesh, and namely each multilayer insulation unit is made up of separately one layer of 6 μm of two-sided aluminized mylar and one layer of terylene mesh.
The control Orbital heat flux light barrier device that this utility model provides, also includes thermal control coating；The both side surface of described multilayer insulation assembly 2 is provided with thermal control coating.Described thermal control coating adopts the silver-plated second surface mirror thermal control coating of conductivity type F46 thin film of 50 μm.F46 is the copolymer of tetrafluoroethene and hexafluoropropene, for perfluoroethylene-propylene (FEP).
As it is shown in figure 1, the control Orbital heat flux light barrier device operation principle that this utility model provides is that multilayer insulation assembly 2 is fixed on the outer surface of carbon fibre material column by hasp and chinlon line by string holes, define control Orbital heat flux light barrier device.Thus reducing the sunlight irradiation for space unit, reducing the Orbital heat flux affecting space unit temperature levels, effectively meeting the temperature requirement of space unit.When the control Orbital heat flux light barrier device using this utility model to provide, it is only necessary to the first column 1 and the second column 4 being connected with space unit, multilayer insulation assembly is arranged on the outer surface of space unit.
Proved by upper embodiment, control Orbital heat flux light barrier device of the present utility model have control Orbital heat flux effective, adaptability is good, thermal control measure also allow for implement feature.
Above specific embodiment of the utility model is described.It is to be appreciated that this utility model is not limited to above-mentioned particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims, and this has no effect on flesh and blood of the present utility model.
Claims (7)
1. one kind controls Orbital heat flux light barrier device, it is characterised in that include the first column, the second column and multilayer insulation assembly；
Wherein, one end of described multilayer insulation assembly connects described first column, and the other end connects described second column；
Described multilayer insulation assembly includes the first join domain, multilayer insulation module body and the second join domain that order is connected；
Described first join domain is provided with the first connector button and the first connector lock body；Described first connector button connects described first after described first column rotates a circle and connects lock body；
Described second join domain is provided with the second connector button and the second connector lock body；Described second connector button connects described second after described second column rotates a circle and connects lock body.
2. control Orbital heat flux light barrier device according to claim 1, it is characterised in that also include the first connecting line and the second connecting line；Described first join domain is provided with multiple first string holes；Described first string holes is arranged between described first connector button and the first connector lock body；
It is connected by the first connecting line between multiple first string holes, thus the first join domain connects the cylinder of described first column；
Described second join domain is provided with multiple second string holes；Described second string holes is arranged between described second connector button and the second connector lock body；
It is connected by the second connecting line between multiple second string holes, thus the second join domain connects the cylinder of described second column.
3. control Orbital heat flux light barrier device according to claim 1, it is characterised in that described multilayer insulation assembly includes the multilayer insulation unit that multilamellar is fitted successively；
Described multilayer insulation unit includes two-sided aluminized mylar and terylene mesh；Described two-sided aluminized mylar is fitted and connected described terylene mesh.
4. control Orbital heat flux light barrier device according to claim 2, it is characterised in that described first column and described second column adopt carbon fibre material to make；
Described first connecting line and described second connecting line adopt chinlon line.
5. control Orbital heat flux light barrier device according to claim 1, it is characterised in that also include thermal control coating；The both side surface of described multilayer insulation assembly is provided with thermal control coating.
6. control Orbital heat flux light barrier device according to claim 5, it is characterised in that described thermal control coating adopts the silver-plated second surface mirror thermal control coating of conductivity type F46 thin film of 50 μm.
7. control Orbital heat flux light barrier device according to claim 1, it is characterised in that described first connector button and described second connector button adopt soft hasp；Described first connector lock body and described second connector lock body adopt hard hasp.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520579356 | 2015-08-04 | ||
| CN2015205793565 | 2015-08-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205366109U true CN205366109U (en) | 2016-07-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520786691.2U Expired - Fee Related CN205366109U (en) | 2015-08-04 | 2015-10-12 | Control outer thermal current barn door device |
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| CN (1) | CN205366109U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428643A (en) * | 2016-09-08 | 2017-02-22 | 上海卫星工程研究所 | External heat flux weakening device and use method thereof as well as a spacecraft |
| CN107628275A (en) * | 2017-07-27 | 2018-01-26 | 上海卫星工程研究所 | A kind of outer rotating mechanism relative motion face thermal controls apparatus of star |
| CN109927940A (en) * | 2019-02-19 | 2019-06-25 | 上海卫星工程研究所 | Solar array driving mechanism temperature barrier |
-
2015
- 2015-10-12 CN CN201520786691.2U patent/CN205366109U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428643A (en) * | 2016-09-08 | 2017-02-22 | 上海卫星工程研究所 | External heat flux weakening device and use method thereof as well as a spacecraft |
| CN107628275A (en) * | 2017-07-27 | 2018-01-26 | 上海卫星工程研究所 | A kind of outer rotating mechanism relative motion face thermal controls apparatus of star |
| CN107628275B (en) * | 2017-07-27 | 2020-11-10 | 上海卫星工程研究所 | Relative motion surface thermal control device of extraterrestrial rotating mechanism |
| CN109927940A (en) * | 2019-02-19 | 2019-06-25 | 上海卫星工程研究所 | Solar array driving mechanism temperature barrier |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160706 Termination date: 20211012 |
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| CF01 | Termination of patent right due to non-payment of annual fee |