CN208364259U - The all- composite engine jet pipe of protection against erosion - Google Patents
The all- composite engine jet pipe of protection against erosion Download PDFInfo
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- CN208364259U CN208364259U CN201820739442.1U CN201820739442U CN208364259U CN 208364259 U CN208364259 U CN 208364259U CN 201820739442 U CN201820739442 U CN 201820739442U CN 208364259 U CN208364259 U CN 208364259U
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- layer
- jet pipe
- enhancement layer
- thermal insulation
- protection against
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- 239000002131 composite material Substances 0.000 title claims abstract description 41
- 230000003628 erosive effect Effects 0.000 title claims abstract description 19
- 239000010410 layer Substances 0.000 claims abstract description 108
- 210000000867 larynx Anatomy 0.000 claims abstract description 49
- 238000002679 ablation Methods 0.000 claims abstract description 35
- 238000009413 insulation Methods 0.000 claims abstract description 26
- 239000000835 fiber Substances 0.000 claims abstract description 22
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 13
- 239000004917 carbon fiber Substances 0.000 claims abstract description 13
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 11
- 238000005229 chemical vapour deposition Methods 0.000 claims abstract description 6
- 230000008569 process Effects 0.000 claims abstract description 5
- 238000009954 braiding Methods 0.000 claims abstract description 4
- 239000002344 surface layer Substances 0.000 claims abstract description 4
- 238000004804 winding Methods 0.000 claims description 15
- 239000005439 thermosphere Substances 0.000 claims 1
- 239000004744 fabric Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 238000000465 moulding Methods 0.000 description 4
- 230000008901 benefit Effects 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
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 2
- 238000005255 carburizing Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000009940 knitting Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 229920001568 phenolic resin Polymers 0.000 description 2
- 239000005011 phenolic resin Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 238000009941 weaving Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- OBNDGIHQAIXEAO-UHFFFAOYSA-N [O].[Si] Chemical compound [O].[Si] OBNDGIHQAIXEAO-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000000875 corresponding effect Effects 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 239000002905 metal composite material Substances 0.000 description 1
- 229920002239 polyacrylonitrile Polymers 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
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- Nonwoven Fabrics (AREA)
Abstract
The utility model discloses a kind of all- composite engine jet pipes of protection against erosion, including larynx lining, head enhancement layer, ablation layer, thermal insulation layer and composite material casing, as starting surface layer, it is jet pipe that ablation layer, thermal insulation layer and composite material casing are successively rotation-formed from inside to outside for larynx lining and head enhancement layer；Head enhancement layer is formed by the arrival end that one end that larynx serves as a contrast extends to jet pipe, and head enhancement layer is integrally formed with larynx lining, and larynx lining and head enhancement layer form after being prepared into prefabricated component for carbon fiber braiding is integrally formed through chemical vapor deposition process；Ablation layer is twisted on carbon fiber bundle through fiber or strap in the band of larynx lining and head enhancement layer through being entwined；Thermal insulation layer is tiltedly twined and is solidified by fiber or strap prepreg on the outside of ablation layer；Composite material casing passes through fiber or strap laying or Wrapping formed on the outside of thermal insulation layer.The utility model proposes protection against erosion all- composite engine jet pipe, solve the problems, such as larynx lining interior ablation layer between falling off.
Description
Technical field
The utility model relates to Solid Rocket Motor Technology fields more particularly to a kind of composite material of protection against erosion to start
Machine jet pipe.
Background technique
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 substitution traditional metal materials are to reduce the effective ways of the passive quality of rocket engine, for example twine using carbon fiber
The total quality of solid propellant rocket can be substantially reduced around shell.
SRM Nozzle can also use the winding of fiber (or strap) material integrally formed to reduce passive quality,
However, one is since the fiber or strap interlaminar action power of winding be strong, and under the ablation effect of high temperature and high pressure gas, ablation
Layer is easily peeled off by airflow scouring；Secondly traditional CC larynx lining is weaker with the active force of ablation layer, thus it is easy in high speed gas
It falls off under the washing away of stream.
It is currently used to solve the problems, such as that the method washed away mainly is adopted after jet pipe head ablation layer is using compression molding
Interlaminar action power is improved with suture or Z-pin is punctured, the major way of these technologies is to be added to improve layer in strap interlayer
Between intensity fiber, however, the addition of fiber will cause the damage of material plane intensity, in addition, the cost of Z-pin technique compared with
Height, overall stability are also poor.And at present to no very effective solution that falls off between larynx lining and interior ablation layer.
Utility model content
The main purpose of the utility model is to provide a kind of all- composite engine jet pipes of protection against erosion, it is intended to solve larynx
The problem that falls off between lining and interior ablation layer.
To achieve the above object, the utility model provides a kind of all- composite engine jet pipe of protection against erosion, including larynx lining,
Head enhancement layer, ablation layer, thermal insulation layer and composite material casing, larynx lining and head enhancement layer, which are used as, originates surface layer, ablation layer,
Thermal insulation layer and composite material casing are successively rotation-formed for jet pipe from inside to outside；
The head enhancement layer is formed by the arrival end that one end that larynx serves as a contrast extends to jet pipe, head enhancement layer and larynx lining one
Molding, larynx lining and head enhancement layer be integrally formed be prepared into after prefabricated component through chemical vapor deposition process of carbon fiber braiding and
At；
The ablation layer is twisted on carbon fiber bundle through fiber or strap in the band of larynx lining and head enhancement layer through being entwined；
The thermal insulation layer is tiltedly twined and is solidified by fiber or strap prepreg on the outside of ablation layer；
The composite material casing passes through fiber or strap laying or Wrapping formed on the outside of thermal insulation layer.
Preferably, one end of the ablation layer extends in the gap that head enhancement layer and thermal insulation layer surround, and the other end prolongs
Extend to the outlet end of jet pipe；The both ends of the thermal insulation layer and composite material casing extend respectively to arrival end and the outlet of jet pipe
End.
Preferably, the head enhancement layer with a thickness of 10-60mm, the larynx diameter of jet pipe is 5-500mm.
Preferably, the ablation layer is wound by fiber or strap with 5 ° ~ 15 ° of winding angle.
Preferably, the thermal insulation layer is wound by fiber or strap with 5 ° ~ 15 ° of winding angle.
Preferably, the density of the larynx lining is 1.70 g/cm3To 1.90 g/cm3。
Preferably, the composite material casing is provided with flange close to the side at nozzle entry end.
The utility model proposes protection against erosion all- composite engine jet pipe, have the advantages that
(1) jet pipe is integrally formed, simple production process, no fault of construction；
(2) light, passive quality can be substantially reduced；
(3) it washes away after most strong head enhancement layer and larynx lining are formed using 2.5D or 3 D weaving through over carburizing technique
It obtains, interlaminar action power is strong, and there is no the situations removed layer by layer；
(4) larynx lining is integrated knitting forming with the head enhancement layer as ablation layer in head, thus larynx lining adds with head
Strong layer is tightly combined；
(5) head enhancement layer and larynx lining are integrally formed, and since larynx lining does not increase in thickness direction, simply increase length
Degree, thus a little felt body cost is simply increased relative to larynx lining, and reduce Fabric tape winding and Z-pin and puncture work
Skill, whole jet pipe are at low cost.
Detailed description of the invention
Fig. 1 is the axial section structural schematic diagram of the all- composite engine jet pipe of the utility model protection against erosion；
Fig. 2 is the structural representation of larynx lining and head enhancement layer in the all- composite engine jet pipe of the utility model protection against erosion
Figure.
In figure, 1- larynx lining, the head 2- enhancement layer, 3- ablation layer, 4- thermal insulation layer, 5- composite material casing.
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 embodiment
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, be constructed and operated in a specific orientation, therefore should not be understood as pair
The limitation of the utility model.The correlated conditions such as position, the winding angle of flange can according to need corresponding adjustment, should not be understood as
Illustrating flange position, winding angle etc. is limitations of the present invention.
Referring to Figures 1 and 2, in this preferred embodiment, a kind of all- composite engine jet pipe of protection against erosion, including larynx lining 1,
Head enhancement layer 2, ablation layer 3, thermal insulation layer 4 and composite material casing 5, larynx lining 1 and head enhancement layer 2 are used as starting surface layer,
It is jet pipe that ablation layer 3, thermal insulation layer 4 and composite material casing 5 are successively rotation-formed from inside to outside (jet pipe is revolving body)；
Head enhancement layer 2 is formed by the arrival end (left end shown in FIG. 1) that one end of larynx lining 1 extends to jet pipe, and head adds
Strong layer 2 and 1 integrated molding of larynx lining, larynx lining 1 and head enhancement layer 2, which are that carbon fiber braiding is integrally formed, to be prepared into after prefabricated component through changing
Gas-phase deposition is learned to form；
Ablation layer 3 is twisted on carbon fiber bundle through fiber or strap in the band of larynx lining 1 and head enhancement layer 2 through being entwined；
Thermal insulation layer 4 is presoaked 3 outside of ablation layer (outside is close to the side of outside of the nozzle wall) by fiber or strap
Material tiltedly twines and solidifies；
Composite material casing 5 passes through fiber or cloth 4 outside of thermal insulation layer (outside is close to the side of outside of the nozzle wall)
Band laying or Wrapping formed.
Specifically, one end of ablation layer 3 extends in the gap that head enhancement layer 2 and thermal insulation layer 4 surround, and the other end extends
To the outlet end (right end shown in FIG. 1) of jet pipe；The both ends of thermal insulation layer 4 and composite material casing 5 extend respectively to jet pipe
Arrival end and outlet end.
Head enhancement layer 2 with a thickness of 10-60mm, the larynx diameter of jet pipe is 5-500mm.Ablation layer 3 passes through fiber or strap
It is wound with 5 ° ~ 15 ° of winding angle.Thermal insulation layer 4 is wound by fiber or strap with 5 ° ~ 15 ° of winding angle.Larynx lining 1
Density be 1.70 g/cm3To 1.90 g/cm3.Larynx lining 1 and head enhancement layer 2 are compiled by carbon fiber bundle through 2.5D or three-dimensional is whole
It knits and is made again through chemical vapor deposition process after forming prefabricated component, density is 1.70 g/cm3To 1.90 g/cm3。
In addition, composite material casing 5 is provided with flange close to the side at nozzle entry end.Composite material casing 5 can be used
T700 carbon fiber prepreg is Wrapping formed, using autoclave and vacuum bag in pressure 1.2MPa, 80 ~ 170 DEG C it is staged curing at
Type.
The production method that the present embodiment provides a specific all- composite engine jet pipe herein.
(1) it is compiled into shape shown in Fig. 2 using T700 carbon fiber, forms prefabricated component, prefabricated component is by CVD three times
It is 1.86 g/cm that density is obtained after (Chemical Vapor Deposition, chemical vapor deposition) carburization process3Larynx lining 1
With head enhancement layer 2.
(2) on the basis of prepared by (1), using the phenolic resin prepolymer of the 1K-300 polyacrylonitrile plain weave carbon cloth of 10 mm wide
Leaching material is wound ablation layer 3, and canoe is 40 N/cm using flat folded winding, the control of strap pressure2, existed using autoclave
According to curing cycle under 0.8 MPa: 85 DEG C/3h+100 DEG C/2h+110 DEG C/1h+125 DEG C/1h+160 DEG C/4h heating speed
Rate: the mode of 0.5 DEG C/min is solidified, and obtains ablation layer wrap, is twined by the ablation layer that turning finishes to obtain qualification
Around part.
(3) it on the basis of (2), is tiltedly twined using 10 ° of prepreg of high silicon oxygen cloth ba phenolic resin that width is 15 mm heat-insulated
Layer 4, strap pressure are controlled in 40N/cm2, after winding obtains respective shapes, the consolidating in 1.0 MPa using autoclave and vacuum bag
Change under pressure according to curing cycle: 85 DEG C/3h+100 DEG C/2h+110 DEG C/1h+125 DEG C/1h+160 DEG C/4h heating speed
Rate: the mode of 0.5 DEG C/min is solidified, and obtains thermal insulation layer wrap, and the next step is entered after turning finishes.
(4) on the basis of (3), the Wrapping formed of shell is carried out using T700 SC carbon fiber prepreg, winding angle is
60 °, by 120 DEG C/2h+150 DEG C/5h heating rate under 1.2 MPa pressure: solidified in the way of 0.5 DEG C/min,
Final jet pipe is obtained by turnery processing.
The all- composite engine jet pipe for the protection against erosion that the present embodiment proposes, has the advantages that
(1) jet pipe is integrally formed, simple production process, no fault of construction；
(2) light, passive quality can be substantially reduced；
(3) it washes away most strong head enhancement layer 2 and larynx lining 1 can be used after 2.5D or 3 D weaving molding through over carburizing
Technique obtains, and interlaminar action power is strong, and there is no the situations removed layer by layer；
(4) larynx lining 1 is integrated knitting forming with the head enhancement layer 2 as interior ablation layer, thus larynx lining 1 is reinforced with head
Layer 2 is tightly combined；
(5) head enhancement layer 2 and larynx lining 1 are integrally formed, and since larynx lining 1 does not increase in thickness direction, are only increased
Length, thus a little felt body cost is simply increased relative to larynx lining 1, and reduce Fabric tape winding and Z-pin and wear
Thorn technique, whole jet pipe are at low cost.
The above is only the preferred embodiments of the utility model, and therefore it does not limit the scope of the patent of the utility model, all
Equivalent structure transformation made based on the specification and figures of the utility model, the including but not limited to adjustment of flange position,
It is wound on the outside of flange or laying metal material or composite material is reinforced, be applied directly or indirectly in other relevant skills
Art field, is also included in the patent protection scope of the utility model.
Claims (7)
1. a kind of all- composite engine jet pipe of protection against erosion, which is characterized in that including larynx lining, head enhancement layer, ablation layer, every
Thermosphere and composite material casing, larynx lining and head enhancement layer are as starting surface layer, ablation layer, thermal insulation layer and composite shell
It is jet pipe that body is successively rotation-formed from inside to outside；
The head enhancement layer is formed by the arrival end that one end that larynx serves as a contrast extends to jet pipe, head enhancement layer and larynx lining one at
Type, larynx lining and head enhancement layer form after being prepared into prefabricated component for carbon fiber braiding is integrally formed through chemical vapor deposition process；
The ablation layer is twisted on carbon fiber bundle through fiber or strap in the band of larynx lining and head enhancement layer through being entwined；
The thermal insulation layer is tiltedly twined and is solidified by fiber or strap prepreg on the outside of ablation layer；
The composite material casing passes through fiber or strap laying or Wrapping formed on the outside of thermal insulation layer.
2. the all- composite engine jet pipe of protection against erosion as described in claim 1, which is characterized in that one end of the ablation layer
It extends in the gap that head enhancement layer and thermal insulation layer surround, the other end extends to the outlet end of jet pipe；The thermal insulation layer and
The both ends of composite material casing extend respectively to arrival end and the outlet end of jet pipe.
3. the all- composite engine jet pipe of protection against erosion as described in claim 1, which is characterized in that the head enhancement layer
With a thickness of 10-60mm, the larynx diameter of jet pipe is 5-500mm.
4. the all- composite engine jet pipe of protection against erosion as described in claim 1, which is characterized in that the ablation layer passes through fibre
Dimension or strap are wound with 5 ° ~ 15 ° of winding angle.
5. the all- composite engine jet pipe of protection against erosion as described in claim 1, which is characterized in that the thermal insulation layer passes through fibre
Dimension or strap are wound with 5 ° ~ 15 ° of winding angle.
6. the all- composite engine jet pipe of protection against erosion as described in claim 1, which is characterized in that the density of larynx lining is
1.70 g/cm3To 1.90 g/cm3。
7. the all- composite engine jet pipe of the protection against erosion as described in any one of claim 1 to 6, which is characterized in that institute
It states composite material casing and the side at nozzle entry end is provided with flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820739442.1U CN208364259U (en) | 2018-05-18 | 2018-05-18 | The all- composite engine jet pipe of protection against erosion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820739442.1U CN208364259U (en) | 2018-05-18 | 2018-05-18 | The all- composite engine jet pipe of protection against erosion |
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| Publication Number | Publication Date |
|---|---|
| CN208364259U true CN208364259U (en) | 2019-01-11 |
Family
ID=64935510
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| CN201820739442.1U Active CN208364259U (en) | 2018-05-18 | 2018-05-18 | The all- composite engine jet pipe of protection against erosion |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590890A (en) * | 2018-03-30 | 2018-09-28 | 上海空间推进研究所 | Engine jet pipe extended segment and lance system |
| CN110509572A (en) * | 2019-09-03 | 2019-11-29 | 长春长光宇航复合材料有限公司 | A kind of full composite material jet pipe and quick molding method |
| 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 |
| CN114198223A (en) * | 2021-11-29 | 2022-03-18 | 湖北航泰科技有限公司 | One-step curing molding full-composite engine spray pipe |
-
2018
- 2018-05-18 CN CN201820739442.1U patent/CN208364259U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590890A (en) * | 2018-03-30 | 2018-09-28 | 上海空间推进研究所 | Engine jet pipe extended segment and lance system |
| CN108590890B (en) * | 2018-03-30 | 2019-12-06 | 上海空间推进研究所 | Nozzle system |
| CN110509572A (en) * | 2019-09-03 | 2019-11-29 | 长春长光宇航复合材料有限公司 | A kind of full composite material jet pipe and quick molding method |
| 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 |
| CN114198223A (en) * | 2021-11-29 | 2022-03-18 | 湖北航泰科技有限公司 | One-step curing molding full-composite engine spray pipe |
| CN114198223B (en) * | 2021-11-29 | 2023-09-15 | 湖北航泰科技有限公司 | One-step curing formed full composite material engine spray pipe |
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Legal Events
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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 |
Denomination of utility model: Scour resistant composite material engine nozzle Effective date of registration: 20220124 Granted publication date: 20190111 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 |
Date of cancellation: 20230227 Granted publication date: 20190111 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 | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Anti erosion composite material engine nozzle Effective date of registration: 20230327 Granted publication date: 20190111 Pledgee: Yichang financing guarantee Group Co.,Ltd. Pledgor: HUBEI HANGTAI TECHNOLOGY Co.,Ltd. Registration number: Y2023980036032 |
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Granted publication date: 20190111 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 |