CN207609489U - The all- composite engine jet pipe of Z-direction enhancing - Google Patents
The all- composite engine jet pipe of Z-direction enhancing Download PDFInfo
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- CN207609489U CN207609489U CN201721734657.6U CN201721734657U CN207609489U CN 207609489 U CN207609489 U CN 207609489U CN 201721734657 U CN201721734657 U CN 201721734657U CN 207609489 U CN207609489 U CN 207609489U
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- composite
- carbon fiber
- jet pipe
- band
- strap
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- 239000002131 composite material Substances 0.000 title claims abstract description 67
- 230000002708 enhancing effect Effects 0.000 title claims abstract description 20
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 42
- 239000004917 carbon fiber Substances 0.000 claims abstract description 42
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 40
- 210000000867 larynx Anatomy 0.000 claims abstract description 35
- 238000002679 ablation Methods 0.000 claims abstract description 33
- 238000009413 insulation Methods 0.000 claims abstract description 22
- 238000004804 winding Methods 0.000 claims abstract description 22
- 239000000835 fiber Substances 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 10
- 238000005229 chemical vapour deposition Methods 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims abstract description 8
- 238000000465 moulding Methods 0.000 claims abstract description 7
- 150000001875 compounds Chemical class 0.000 claims abstract description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 230000005494 condensation Effects 0.000 claims description 2
- 238000009833 condensation Methods 0.000 claims description 2
- 238000000151 deposition Methods 0.000 claims 1
- 239000000126 substance Substances 0.000 claims 1
- 230000009471 action Effects 0.000 abstract description 3
- 238000009991 scouring Methods 0.000 abstract description 3
- 239000010410 layer Substances 0.000 description 42
- 239000011203 carbon fibre reinforced carbon Substances 0.000 description 23
- 101000845183 Homo sapiens Tetratricopeptide repeat protein 5 Proteins 0.000 description 17
- 102100031280 Tetratricopeptide repeat protein 5 Human genes 0.000 description 17
- 239000004744 fabric Substances 0.000 description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 5
- 229910052799 carbon Inorganic materials 0.000 description 5
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000377 silicon dioxide Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
- 238000005255 carburizing Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 210000004209 hair Anatomy 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 229920002239 polyacrylonitrile Polymers 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
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- Laminated Bodies (AREA)
Abstract
The utility model discloses a kind of all- composite engine jet pipes of Z-direction enhancing, including C/C composite materials larynx lining, ablation layer, thermal insulation layer and composite material casing, wherein, C/C composite material larynxs lining is to be made through chemical vapor deposition method after carbon fiber is woven into prefabricated component, and the outer edge of C/C composite material larynxs lining is that band twists carbon fiber bundle；It is twisted in the band of C/C composite material larynxs lining and forms ablation layer on carbon fiber bundle after fiber or strap prepreg are wound and are cured, band is twisted carbon fiber bundle and is inserted into inside ablation layer；The side of ablation layer tiltedly twines and is formed by curing thermal insulation layer by fiber or strap prepreg, and band is twisted carbon fiber bundle and is inserted into inside thermal insulation layer；The side of thermal insulation layer is by fiber or strap is laid or winding molding compound material shell.The utility model proposes Z-direction enhancing all- composite engine jet pipe, improve interlaminar action power, reduce the probability that ablation layer is peeled off by airflow scouring.
Description
Technical field
The utility model is related to the composite material hairs that Solid Rocket Motor Technology field more particularly to a kind of Z-direction enhance
Motivation jet pipe.
Background technology
The light weight of solid propellant rocket moulding material and it is high-strength be Solid Rocket Propulsion Technology eternal developing goal.It uses
Composite material, which substitutes traditional metal materials, is the effective ways for the passive quality for reducing rocket engine, for example is twined using carbon fiber
The total quality of solid propellant rocket can be substantially reduced around shell.
SRM Nozzle can also use fiber（Or strap）Material is Wrapping formed to reduce passive quality, so
And the fiber and strap interlaminar action power due to winding be not strong, under the ablation effect of high temperature and high pressure gas, ablation layer is easily
It is peeled off by airflow scouring.
Utility model content
The main purpose of the utility model is to provide a kind of all- composite engine jet pipes of Z-direction enhancing, it is intended to improve
Interlaminar action power.
To achieve the above object, the utility model provides a kind of all- composite engine jet pipe of Z-direction enhancing, including C/C
Composite material larynx lining, ablation layer, thermal insulation layer and composite material casing, wherein
The C/C composite materials larynx lining is to be made through chemical vapor deposition method after carbon fiber is woven into prefabricated component,
The outer edge of C/C composite material larynxs lining is that band twists carbon fiber bundle；
The C/C composite materials larynx lining band twist carbon fiber bundle on after fiber or strap prepreg are wound and are cured shape
At ablation layer, band is twisted carbon fiber bundle and is inserted into inside ablation layer；
The side of the ablation layer tiltedly twines and is formed by curing thermal insulation layer by fiber or strap prepreg, and band twists carbon fiber bundle
It is inserted into inside thermal insulation layer；
The side of the thermal insulation layer is by fiber or strap is laid or winding molding compound material shell.
Preferably, the band outside the C/C composite materials larynx lining twists a diameter of 1.05 ~ 1.15mm of carbon fiber bundle.
Preferably, it is 5 ~ 6 mm that the band outside the C/C composite materials larynx lining, which twists the length of carbon fiber bundle,.
Preferably, the C/C composite materials larynx lining is 5 ~ 20 mm, a diameter of 0.2 ~ 1.5 mm carbon fibers by length in reserve
It is made again through chemical vapor deposition method after the woven formation prefabricated component of beam.
Preferably, the ablation layer is wound by fiber or strap with 5 ° ~ 15 ° of winding angle.
Preferably, the density of the C/C composite materials larynx lining is 1.70 g/cm3To 1.90 g/cm3。
Preferably, the composite material casing is Wrapping formed with 50 ° ~ 70 ° of winding angle by fiber or strap.
Preferably, the side of the composite material casing is provided with flange.
The utility model proposes Z-direction enhancing all- composite engine jet pipe, have the advantages that：
（1）Jet pipe is integrally formed, simple production process, no fault of construction；
（2）Winding method is molded, and is kept its light, can be substantially reduced passive quality；
（3）C/C composite material larynxs are served as a contrast twists carbon fiber bundle progress interlaminar improvement between ablation layer and thermal insulation layer by band, no
It can layer by layer be removed by air-flow, resistance to ablation ability is strong.
Description of the drawings
Fig. 1 is the structural schematic diagram of the all- composite engine jet pipe of the utility model Z-direction enhancing；
Fig. 2 is the structural schematic diagram of prefabricated component in the all- composite engine jet pipe that the utility model Z-direction enhances；
Fig. 3 is that prefabricated component forms C/C after carburizing is fixed in the all- composite engine jet pipe that the utility model Z-direction enhances
The structural schematic diagram of composite material larynx lining.
In figure, 1-C/C composite material larynxs lining, 2- ablation layers, 3- thermal insulation layers, 4- flanges, 5- composite material casings.
The embodiments will be further described with reference to the accompanying drawings for the realization, functional characteristics and advantage of the utility model aim.
Specific implementation mode
It should be appreciated that specific embodiment described herein is only used to explain the utility model, it is not used to limit this
Utility model.
It should be noted that in the description of the present invention, term " transverse direction ", " longitudinal direction ", "upper", "lower", " preceding ",
The orientation or positional relationship of the instructions such as " rear ", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" be based on
Orientation or positional relationship shown in the drawings, is merely for convenience of describing the present invention and simplifying the description, and is not instruction or dark
Show that signified device or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as pair
The limitation of the utility model.
Referring to figs. 1 to Fig. 3, a kind of all- composite engine jet pipe of Z-direction enhancing, including C/C composite material larynxs lining 1, burning
Lose layer 2, thermal insulation layer 3 and composite material casing 5, wherein
C/C composite material larynxs lining 1 is made after being woven into prefabricated component for carbon fiber through chemical vapor deposition method, C/C
The outer edge of composite material larynx lining 1 is that band twists carbon fiber bundle；
It is formed after fiber or strap prepreg are wound and are cured on the band twirl carbon fiber bundle of C/C composite material larynxs lining 1
Ablation layer 2, band are twisted carbon fiber bundle and are inserted into inside ablation layer 2；
The side of ablation layer 2 tiltedly twines by fiber or strap prepreg and is formed by curing thermal insulation layer 3, and band is twisted carbon fiber bundle and inserted
Enter inside thermal insulation layer 3；
The side of thermal insulation layer 3 is by fiber or strap is laid or winding molding compound material shell 5.
Specifically, the band outside C/C composite materials larynx lining 1 twists a diameter of 1.05 ~ 1.15mm of carbon fiber bundle.C/C composite woods
Expect that the length that the band outside larynx lining 1 twists carbon fiber bundle is 5 ~ 6 mm.C/C composite material larynxs lining 1 is 5 ~ 20 mm by length in reserve,
It is made again through chemical vapor deposition method after a diameter of woven formation prefabricated component of 0.2 ~ 1.5 mm carbon fiber bundles.C/C composite woods
Expect that the density of larynx lining 1 is 1.70 g/cm3To 1.90 g/cm3。
Ablation layer 2 passes through fiber or strap（Carbon fiber or carbon cloth can be used）It is wound with 5 ° ~ 15 ° of winding angle.It is multiple
Condensation material shell 5 is Wrapping formed with 50 ° ~ 70 ° of winding angle by fiber or strap.By with certain winding angle molding, shadow
Ring it is each to mechanics distribution, the low longitudinal strength of winding angle is high, and winding angle epipodium is to intensity height.The one of composite material casing 5
Side is provided with flange 4.Thermal insulation layer 3 can be Wrapping formed by high silica cloth.
It is Wrapping formed that ablation layer 2 can be used T300K plain weave carbon cloth prepregs, and it is 30- that Winding pressure is controlled in winding process
50 N/cm2, to ensure that thick beam carbon fiber is inserted into inside carbon cloth without fractureing.
It is Wrapping formed that composite material casing 5 can be used T700 carbon fiber prepregs, using autoclave and vacuum bag in pressure
1.2MPa, 80-170 DEG C of staged curing moldings.
The production method that the present embodiment provides the all- composite engine jet pipe of a specific Z-direction enhancing herein.
（1）It is compiled into shape shown in Fig. 2 using T700 carbon fibers, reserves 1 mm of diameter in tail portion, the band of 5 mm of length is twisted
Carbon fiber bundle forms prefabricated component, and prefabricated component is by CVD three times（Chemical Vapor Deposition, chemical vapor deposition）
It is 1.86g/cm that density is obtained after carburization process3C/C composite material larynxs lining 1.Carbon fiber bundle diameter outside larynx lining becomes
1.05-1.15mm length is still 5 mm.
（2）Ablation layer 2 is wound using the 1K-300 polyacrylonitrile plain weave carbon cloth prepregs of 10mm wide, canoe is adopted
With flat folded winding, the control of strap pressure is 40N/cm2, ensure that reserved carbon fiber bundle is inserted into inside strap, winding obtains corresponding
After shape, using autoclave according to curing cycle at 0.8MPa：85℃ /3h+100℃ /2h+110℃ /1h+125℃ /
1h+160 DEG C/4h heating rates（Curing degree ladder）：The mode of 0.5 DEG C/min is cured, and ablation layer wrap is obtained, and is passed through
Turning finishes to obtain qualified ablation layer wrap.Since 1 reserved carbon fiber of C/C composite material larynxs lining enters ablation layer carbon
The interlayer of cloth and play the role of Z-direction enhancing, ablation layer strap binding force between layers and mechanical strength greatly improve, together
When, reserved carbon fiber can resist washing away for air-flow, thus ablation layer strap will not be removed by airflow scouring and layer by layer, significantly
Improve the ablation resistance of jet pipe.
（3）Tiltedly thermal insulation layer 3, strap pressure control are twined using 10 ° of the high silica cloth ba phenolic resin prepreg that width is 15 mm
System is in 40N/cm2, after winding obtains respective shapes, using autoclave and vacuum bag according to solid under the solidifying pressure of 1.0 MPa
Change system：85 DEG C/3h+100 DEG C/2h+110 DEG C/1h+125 DEG C/1h+160 DEG C/4h heating rates（Curing degree ladder）：0.5
DEG C/mode of min cured, thermal insulation layer wrap is obtained, the next step is entered after turning finishes.
（4）The Wrapping formed of shell is carried out using T700 SC carbon fiber prepregs, winding angle is 60 °, in 1.2 MPa
According to 120 DEG C/2h+150 DEG C/5h heating rates under pressure（Curing degree ladder）：The mode of 0.5 DEG C/min is cured, and is passed through
Turnery processing obtains final jet pipe.
The all- composite engine jet pipe for the Z-direction enhancing that the present embodiment proposes, has the advantages that：
（1）Jet pipe is integrally formed, and is not related to bonding and the splicing of component, simple production process, no fault of construction；
（2）Winding method is molded, and is kept its light, can be substantially reduced passive quality；
（3）Carbon fiber bundle is twisted by band between C/C composite material larynxs lining 1 and ablation layer 2 and thermal insulation layer 3 and carries out interlayer increasing
By force, it will not layer by layer be removed by air-flow, resistance to ablation ability is strong.
It these are only the preferred embodiment of the utility model, it does not limit the scope of the patent of the present invention, every
Equivalent structure transformation made based on the specification and figures of the utility model, it is relevant to be applied directly or indirectly in other
Technical field is equally included in the patent within the scope of the utility model.
Claims (8)
1. a kind of all- composite engine jet pipe of Z-direction enhancing, which is characterized in that including C/C composite materials larynx lining, ablation layer,
Thermal insulation layer and composite material casing, wherein
The C/C composite materials larynx lining is to be made through chemical vapor deposition method after carbon fiber is woven into prefabricated component, and C/C is multiple
The outer edge of condensation material larynx lining is that band twists carbon fiber bundle；
It twists to be formed after fiber or strap prepreg are wound and are cured on carbon fiber bundle in the band of C/C composite materials larynx lining and burn
Layer is lost, band is twisted carbon fiber bundle and is inserted into inside ablation layer；
The side of the ablation layer tiltedly twines and is formed by curing thermal insulation layer by fiber or strap prepreg, and band is twisted carbon fiber bundle and is inserted into
Inside thermal insulation layer；
The side of the thermal insulation layer is by fiber or strap is laid or winding molding compound material shell.
2. the all- composite engine jet pipe of Z-direction enhancing as described in claim 1, which is characterized in that the C/C composite materials
Band outside larynx lining twists a diameter of 1.05 ~ 1.15mm of carbon fiber bundle.
3. the all- composite engine jet pipe of Z-direction enhancing as described in claim 1, which is characterized in that the C/C composite materials
The length that band outside larynx lining twists carbon fiber bundle is 5 ~ 6 mm.
4. the all- composite engine jet pipe of Z-direction enhancing as described in claim 1, which is characterized in that the C/C composite materials
Larynx lining is 5 ~ 20 mm by length in reserve, again through chemical gas after a diameter of woven formation prefabricated component of 0.2 ~ 1.5 mm carbon fiber bundles
Phase depositing operation is made.
5. the all- composite engine jet pipe of Z-direction enhancing as described in claim 1, which is characterized in that the ablation layer passes through
Fiber or strap are wound with 5 ° ~ 15 ° of winding angle.
6. the all- composite engine jet pipe of Z-direction enhancing as described in claim 1, which is characterized in that the C/C composite materials
The density of larynx lining is 1.70 g/cm3To 1.90 g/cm3。
7. the all- composite engine jet pipe of Z-direction enhancing as described in claim 1, which is characterized in that the composite shell
Body is Wrapping formed with 50 ° ~ 70 ° of winding angle by fiber or strap.
8. the all- composite engine jet pipe of Z-direction enhancing as claimed in any of claims 1 to 7 in one of claims, which is characterized in that institute
The side for stating composite material casing is provided with flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721734657.6U CN207609489U (en) | 2017-12-13 | 2017-12-13 | The all- composite engine jet pipe of Z-direction enhancing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721734657.6U CN207609489U (en) | 2017-12-13 | 2017-12-13 | The all- composite engine jet pipe of Z-direction enhancing |
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| Publication Number | Publication Date |
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| CN207609489U true CN207609489U (en) | 2018-07-13 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109882317A (en) * | 2018-11-30 | 2019-06-14 | 西安航天动力技术研究所 | A kind of nozzle-divergence segment structure reducing outer wall temperature |
| CN110529293A (en) * | 2019-05-15 | 2019-12-03 | 内蒙古工业大学 | A kind of solid propellant rocket hot-bulb socket and spigot joint header structure design |
| CN110588014A (en) * | 2019-09-03 | 2019-12-20 | 长春长光宇航复合材料有限公司 | 2.5D composite material spray pipe expansion section and co-curing forming method thereof |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112571829A (en) * | 2020-11-25 | 2021-03-30 | 长春长光宇航复合材料有限公司 | Preparation method of high-performance composite material spray pipe part |
-
2017
- 2017-12-13 CN CN201721734657.6U patent/CN207609489U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109882317A (en) * | 2018-11-30 | 2019-06-14 | 西安航天动力技术研究所 | A kind of nozzle-divergence segment structure reducing outer wall temperature |
| CN110529293A (en) * | 2019-05-15 | 2019-12-03 | 内蒙古工业大学 | A kind of solid propellant rocket hot-bulb socket and spigot joint header structure design |
| CN110529293B (en) * | 2019-05-15 | 2022-06-21 | 内蒙古工业大学 | Solid rocket engine hot ball socket joint structural design |
| CN110588014A (en) * | 2019-09-03 | 2019-12-20 | 长春长光宇航复合材料有限公司 | 2.5D composite material spray pipe expansion section and co-curing forming method thereof |
| CN110588014B (en) * | 2019-09-03 | 2023-01-10 | 长春长光宇航复合材料有限公司 | 2.5D composite material spray pipe expansion section and co-curing forming method thereof |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112571829A (en) * | 2020-11-25 | 2021-03-30 | 长春长光宇航复合材料有限公司 | Preparation method of high-performance composite material spray pipe part |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Z-direction reinforced composite material engine nozzle Effective date of registration: 20220124 Granted publication date: 20180713 Pledgee: Yichang financing guarantee Group Co.,Ltd. Pledgor: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. Registration number: Y2022980001010 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230227 Granted publication date: 20180713 Pledgee: Yichang financing guarantee Group Co.,Ltd. Pledgor: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. Registration number: Y2022980001010 |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Z-direction reinforced composite material engine nozzle Effective date of registration: 20230327 Granted publication date: 20180713 Pledgee: Yichang financing guarantee Group Co.,Ltd. Pledgor: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. Registration number: Y2023980036032 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Granted publication date: 20180713 Pledgee: Yichang financing guarantee Group Co.,Ltd. Pledgor: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. Registration number: Y2023980036032 |