CN204223186U - A kind of light thin-wall composite structure fairing - Google Patents
A kind of light thin-wall composite structure fairing Download PDFInfo
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- CN204223186U CN204223186U CN201420617540.XU CN201420617540U CN204223186U CN 204223186 U CN204223186 U CN 204223186U CN 201420617540 U CN201420617540 U CN 201420617540U CN 204223186 U CN204223186 U CN 204223186U
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Abstract
The utility model belongs to spacecraft structure technical field, is specifically related to a kind of light thin-wall composite structure fairing.This fairing is laminar texture, meet to pneumatic come flow path direction be streamline contour, each layer is respectively carbon fiber A, glass fibre, carbon fiber B, resin matrix, thermal protection coating from inside to outside.2.5 dimension braidings are adopted between described carbon fiber A, glass fibre, carbon fiber B, form composite material preformed body, two groups of fibers are had in 2.5 dimension braided materials, distribute along X to Y-direction in preform, warp thread bends through adjacent weft layers in Z-direction, and adjacent weft layers is linked together, form integral fabric.Described carbon fiber A, carbon fiber B adopt T300 carbon fiber, layer thickness 0.2mm.Described glass fibre adopts 4 layers of SW280 high-strength glass fibre, layer thickness 0.2mm.Described resin matrix adopts bismaleimide resin.Described thermal protection coating adopts silicone rubber based thermal protection coating.It is light that the utility model has architecture quality, the advantages such as thermal protective performance is good.
Description
Technical field
The utility model belongs to spacecraft structure technical field, is specifically related to a kind of light thin-wall composite structure fairing.
Background technology
In space launch vehicle, cable and pipeline etc. lay along outer wall, cause local protuberance, affect aerodynamic configuration.And space launch vehicle is in high-speed flight, oncoming gas shock, on local protuberance thing, can cause structure temperature to rise sharply, can cause structural failure time serious.General solution is at local protuberance beyond the region of objective existence side design path type fairing, maintains spacecraft aerodynamic configuration, bears Aerodynamic Heating, to protect the facility such as inside cable and pipeline simultaneously.Conventional rectifier cover is different according to Aerodynamic Heating environment, uses the metallic material such as steel, aluminium more.But metallic material density is large, thermal conductivity is high, cause final finished scantling of structure large, Heavy Weight.Although can content with funtion requirement, have influence on the carrying capacity of spacecraft.Space launch vehicle requires that outer fairing is lightweight, anti-nuclear electromagnetic pulse is effective, high-temperature resistant result good, causes cowling design difficulty large.
Summary of the invention
The purpose of this utility model is to provide a kind of light thin-wall composite structure fairing, and it is light that this fairing has architecture quality, the advantages such as thermal protective performance is good.
For achieving the above object, technical solution adopted in the utility model is:
A kind of light thin-wall composite structure fairing is laminar texture, meet to pneumatic come flow path direction be streamline contour, each layer is respectively carbon fiber A, glass fibre, carbon fiber B, resin matrix, thermal protection coating from inside to outside.
2.5 dimension braidings are adopted between described carbon fiber A, glass fibre, carbon fiber B, form composite material preformed body, two groups of fibers are had in 2.5 dimension braided materials, distribute along X to Y-direction in preform, warp thread bends through adjacent weft layers in Z-direction, and adjacent weft layers is linked together, form integral fabric.
Described carbon fiber A, carbon fiber B adopt T300 carbon fiber, layer thickness 0.2mm.
Described glass fibre adopts 4 layers of SW280 high-strength glass fibre, layer thickness 0.2mm.
Described resin matrix adopts bismaleimide resin.
Described thermal protection coating adopts silicone rubber based thermal protection coating.
Described fairing uses the finished product after mold pressing or injection mo(u)lding, and gross thickness is 1.6mm ± 0.2mm, when being incubated 10min at 300 DEG C, pulling strengrth is not less than 330MPa, compression strength is not less than 326MPa, and bending strength is not less than 548MPa, and shearing strength value is not less than 27.2MPa.
Described fairing, after selecting the thermal protection coating of 3mm, can bear 35kw/m
2aerodynamic Heating hot-fluid, is reduced to 250 DEG C by cable hood body temperature from 800 DEG C.
Described fairing surface density reaches 16.03kg/mm
2.
Beneficial effect acquired by the utility model is:
The utility model thickness can be accomplished very thin, 1.5mm, in identical high Aerodynamic Heating environment, compares traditional steel fairing loss of weight 48.3%.Use carbon fiber, can ensure that dome structure is electrically continuous.Electrical continuity can be the important performance of spacecraft safety.Use glass fibre, the resistance to heat of fairing finished product can be promoted.Use 2.5 dimension braidings, while raising fiber lay down layer interlaminar strength, the advantage that anufacturability is good can be had.Outermost layer and innermost layer two-layer use carbon fiber symmetrical, internal stress when can balance composite formed, avoids warpage.The glass temperature of bismaleimide resin is 350 DEG C, uses bismaleimide resin, significantly can promote the resistance to heat of fairing.If serviceability temperature is more than 350 DEG C, at the thermal protection coating of fairing outermost layer according to actual conditions spraying different-thickness, promote its resistance to heat further.The density of thermal protection coating is 0.52g/cm
3, much smaller than the density of metallic material.The object of loss of weight can be reached.
Accompanying drawing explanation
Fig. 1 is light thin-wall composite structure dome structure figure described in the utility model;
Fig. 2 is the partial enlarged drawing of Fig. 1;
In figure: 1, carbon fiber A; 2, glass fibre; 3, resin matrix; 4, thermal protection coating; 5, fairing; 6, carbon fiber B.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail..
As shown in Figure 1 and Figure 2, light thin-wall composite structure fairing 5 described in the utility model is laminar texture, meet to pneumatic come flow path direction be streamline contour, each layer is respectively carbon fiber A1, glass fibre 2, carbon fiber B6, resin matrix 3, thermal protection coating 4 from inside to outside; Wherein adopt 2.5 dimension braidings between carbon fiber and glass fibre 2, form composite material preformed body, two groups of fibers are had in 2.5 dimension braided materials, along warp-wise (X to) and broadwise (Y-direction) distribution in preform, warp thread bends through adjacent weft layers in Z-direction, and adjacent weft layers is linked together, form integral fabric.Its interlayer mechanical property is better than laminated material, and manufacturability is better than full 3 D weaving.
Described carbon fiber A1, carbon fiber B6 adopt T300 carbon fiber.Can strengthen resin matrix 3, simultaneously because electric conduction of carbon fiber is functional, can ensure that cubic performance is continuous.Tie up braiding with other interlayer 2.5 to form.Every layer thickness 0.2mm.
Described glass fibre 2 adopts 4 layers of SW280 high-strength glass fibre.Can strengthen resin-based, there is good resistance to heat simultaneously.Can lay multilayer according to service condition, interlayer 2.5 is tieed up braiding and is formed.Every layer thickness 0.2mm.
Described resin matrix 3 adopts bismaleimide resin.Have the glass temperature up to 350 DEG C, resistance to heat is good.
Described thermal protection coating 4 adopts silicone rubber based thermal protection coating.The thickness different according to Aerodynamic Heating environmental selection, protection bismaleimide resin matrix 3 temperature is not higher than serviceability temperature.
Shaping rear overall performance is as follows.
Use the finished product after mold pressing or injection mo(u)lding, gross thickness is 1.6mm ± 0.2mm, and when being incubated 10min at 300 DEG C, pulling strengrth is not less than 330MPa, and compression strength is not less than 326MPa, and bending strength is not less than 548MPa, and shearing strength value is not less than 27.2MPa.
After selecting the thermal protection coating of 3mm, 35kw/m can be born
2aerodynamic Heating hot-fluid, is reduced to 250 DEG C by cable hood body temperature from 800 DEG C.
Piece electrical performance is continuous.
Surface density reaches 16.03kg/mm
2, and under identical function condition, use the surface density of steel fairing for 31kg/mm
2, therefore can remarkable loss of weight.
Claims (9)
1. a light thin-wall composite structure fairing, it is characterized in that: this fairing (5) is laminar texture, meet to pneumatic come flow path direction be streamline contour, each layer is respectively carbon fiber A (1), glass fibre (2), carbon fiber B (6), resin matrix (3), thermal protection coating (4) from inside to outside.
2. light thin-wall composite structure fairing according to claim 1, it is characterized in that: between described carbon fiber A (1), glass fibre (2), carbon fiber B (6), adopt 2.5 dimension braidings, form composite material preformed body, two groups of fibers are had in 2.5 dimension braided materials, distribute along X to Y-direction in preform, warp thread bends through adjacent weft layers in Z-direction, and adjacent weft layers is linked together, and forms integral fabric.
3. light thin-wall composite structure fairing according to claim 1, is characterized in that: described carbon fiber A (1), carbon fiber B (6) adopt T300 carbon fiber, layer thickness 0.2mm.
4. light thin-wall composite structure fairing according to claim 1, is characterized in that: described glass fibre (2) adopts 4 layers of SW280 high-strength glass fibre, layer thickness 0.2mm.
5. light thin-wall composite structure fairing according to claim 1, is characterized in that: described resin matrix (3) adopts bismaleimide resin.
6. light thin-wall composite structure fairing according to claim 1, is characterized in that: described thermal protection coating (4) adopts silicone rubber based thermal protection coating.
7. light thin-wall composite structure fairing according to claim 1, it is characterized in that: described fairing (5) uses the finished product after mold pressing or injection mo(u)lding, gross thickness is 1.6mm ± 0.2mm, when being incubated 10min at 300 DEG C, pulling strengrth is not less than 330MPa, compression strength is not less than 326MPa, and bending strength is not less than 548MPa, and shearing strength value is not less than 27.2MPa.
8. light thin-wall composite structure fairing according to claim 1, is characterized in that: described fairing (5), after selecting the thermal protection coating (4) of 3mm, can bear 35kw/m
2aerodynamic Heating hot-fluid, is reduced to 250 DEG C by cable hood body temperature from 800 DEG C.
9. light thin-wall composite structure fairing according to claim 1, is characterized in that: described fairing (5) surface density reaches 16.03kg/mm
2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420617540.XU CN204223186U (en) | 2014-10-23 | 2014-10-23 | A kind of light thin-wall composite structure fairing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420617540.XU CN204223186U (en) | 2014-10-23 | 2014-10-23 | A kind of light thin-wall composite structure fairing |
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|---|---|
| CN204223186U true CN204223186U (en) | 2015-03-25 |
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| CN201420617540.XU Active CN204223186U (en) | 2014-10-23 | 2014-10-23 | A kind of light thin-wall composite structure fairing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106253161A (en) * | 2016-09-30 | 2016-12-21 | 西安长峰机电研究所 | A kind of composite material cable cover |
| CN110481058A (en) * | 2019-09-20 | 2019-11-22 | 湖北三江航天江北机械工程有限公司 | Inside it is embedded in the winding intracorporal lightweight cable hood forming method of shell |
| CN114197099A (en) * | 2021-12-17 | 2022-03-18 | 宜兴市新立织造有限公司 | Three-dimensional braided composite material cable cover and preparation method thereof |
| CN115231000A (en) * | 2022-09-20 | 2022-10-25 | 北京宇航系统工程研究所 | Heat insulation method for space carrier |
-
2014
- 2014-10-23 CN CN201420617540.XU patent/CN204223186U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106253161A (en) * | 2016-09-30 | 2016-12-21 | 西安长峰机电研究所 | A kind of composite material cable cover |
| CN110481058A (en) * | 2019-09-20 | 2019-11-22 | 湖北三江航天江北机械工程有限公司 | Inside it is embedded in the winding intracorporal lightweight cable hood forming method of shell |
| CN110481058B (en) * | 2019-09-20 | 2021-08-06 | 湖北三江航天江北机械工程有限公司 | Method for forming light cable cover embedded in winding shell |
| CN114197099A (en) * | 2021-12-17 | 2022-03-18 | 宜兴市新立织造有限公司 | Three-dimensional braided composite material cable cover and preparation method thereof |
| CN115231000A (en) * | 2022-09-20 | 2022-10-25 | 北京宇航系统工程研究所 | Heat insulation method for space carrier |
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