CN204223186U - A kind of light thin-wall composite structure fairing - Google Patents
A kind of light thin-wall composite structure fairing Download PDFInfo
- Publication number
- 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
- Authority
- CN
- China
- Prior art keywords
- carbon fiber
- fairing
- composite structure
- light thin
- glass fibre
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 22
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 32
- 239000004917 carbon fiber Substances 0.000 claims abstract description 32
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 32
- 239000011248 coating agent Substances 0.000 claims abstract description 18
- 238000000576 coating method Methods 0.000 claims abstract description 18
- 239000003365 glass fiber Substances 0.000 claims abstract description 18
- 229920005989 resin Polymers 0.000 claims abstract description 18
- 239000011347 resin Substances 0.000 claims abstract description 18
- 239000011159 matrix material Substances 0.000 claims abstract description 11
- XQUPVDVFXZDTLT-UHFFFAOYSA-N 1-[4-[[4-(2,5-dioxopyrrol-1-yl)phenyl]methyl]phenyl]pyrrole-2,5-dione Chemical compound O=C1C=CC(=O)N1C(C=C1)=CC=C1CC1=CC=C(N2C(C=CC2=O)=O)C=C1 XQUPVDVFXZDTLT-UHFFFAOYSA-N 0.000 claims abstract description 7
- 238000009954 braiding Methods 0.000 claims abstract description 7
- 229920003192 poly(bis maleimide) Polymers 0.000 claims abstract description 7
- 239000000835 fiber Substances 0.000 claims abstract description 5
- 239000004744 fabric Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims abstract description 4
- 229920002379 silicone rubber Polymers 0.000 claims abstract description 4
- 239000004945 silicone rubber Substances 0.000 claims abstract description 4
- 238000010438 heat treatment Methods 0.000 claims description 7
- 238000005452 bending Methods 0.000 claims description 3
- 230000036760 body temperature Effects 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000010008 shearing Methods 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 17
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000011229 interlayer Substances 0.000 description 3
- 208000020442 loss of weight Diseases 0.000 description 3
- 239000007769 metal material Substances 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 239000011521 glass Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000003460 anti-nuclear Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000002648 laminated material Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000009941 weaving Methods 0.000 description 1
Landscapes
- Laminated Bodies (AREA)
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 |
Applications Claiming Priority (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 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204223186U true CN204223186U (en) | 2015-03-25 |
Family
ID=52921307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420617540.XU Expired - Lifetime CN204223186U (en) | 2014-10-23 | 2014-10-23 | A kind of light thin-wall composite structure fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204223186U (en) |
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 not_active Expired - Lifetime
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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204223186U (en) | A kind of light thin-wall composite structure fairing | |
| US10399657B2 (en) | Fibre-reinforced metal component for an aircraft or spacecraft and production methods for fibre-reinforced metal components | |
| CN105500837B (en) | The technique that composite makes high ferro equipment compartment apron board | |
| US9669937B2 (en) | Fiber composite part for an aircraft or spacecraft | |
| US20140168847A1 (en) | Lightning strike protection means and fibre composite component | |
| CN202711808U (en) | Insulation-type carbon fiber composite core wire | |
| CN105082723B (en) | A kind of fiber-reinforced thermoplastic resin aramid aluminiumlaminates part shaping techniques | |
| EP3564184B1 (en) | Structural fibre-reinforced component with lightning strike protection by using carbon nano tube mats and metallic layers | |
| US20130005208A1 (en) | Electrically conductive structure | |
| JP7446735B2 (en) | Integrated surface protection systems, composite structures and methods of protection | |
| US20220411077A1 (en) | Electrothermal heater mat | |
| CN106079474A (en) | A kind of naval vessel composite propeller blade preform and preparation method thereof | |
| JP6615357B2 (en) | Process for manufacturing bottom plate of equipment cabin in high-speed railway vehicle by composite material | |
| CN110654526A (en) | Temperature equalizing method and structure for high-temperature and high-heat part | |
| CN105173056A (en) | Wing fuel tank protective cap and forming process thereof | |
| CN112781443B (en) | Stealth, ablation and bearing integrated light launching box and preparation method thereof | |
| US20190240876A1 (en) | Composite structures | |
| US20230219696A1 (en) | Lightning strike protection layer | |
| CN204249171U (en) | Full-automatic glass steel dismoulding system | |
| CN105313345A (en) | Fabrication technology for thermoplastic composite product for airplane main/auxiliary force-bearing components | |
| CN106584701A (en) | Forming method for sewing body enhanced composite steering engine protection plate | |
| CN211993703U (en) | Ultrathin preforming body for multi-curved-surface shell with continuous non-notch core layer reinforced fabric | |
| CN203770587U (en) | Transmission device | |
| CN205911047U (en) | Light -duty aviation wire of high strength | |
| US20130230390A1 (en) | Leading edge structure, in particular for an air inlet of an aircraft engine nacelle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |