CN106762222A - Large-scale segmentation composite shell attachment structure and housing winding method - Google Patents
Large-scale segmentation composite shell attachment structure and housing winding method Download PDFInfo
- Publication number
- CN106762222A CN106762222A CN201611069154.1A CN201611069154A CN106762222A CN 106762222 A CN106762222 A CN 106762222A CN 201611069154 A CN201611069154 A CN 201611069154A CN 106762222 A CN106762222 A CN 106762222A
- Authority
- CN
- China
- Prior art keywords
- section
- winding layer
- winding
- rocket engine
- fiber
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to a kind of large-scale segmentation composite shell attachment structure, its left section of rocket engine cast is fixedly connected by left connector with right section of rocket engine cast with right connector, wind to hang in each first fiber by fiber and carried out between stake and left section of motor body end socket spiral winding the first spiral inclination winding layer of formation, ring is carried out in the first spiral inclination winding layer outer surface by fiber and is wound the first circumferential winding layer, wind to hang in each second fiber by fiber and carried out between stake and right section of motor body end socket spiral winding the second spiral inclination winding layer of formation, ring is carried out in the second spiral inclination winding layer outer surface by fiber and is wound the second circumferential winding layer.The present invention can make large-scale segmentation composite material casing high stability connection, automation high Wrapping formed.
Description
Technical field
The present invention relates to without end socket housing pressure stochastic distribution and interconnection technique, and in particular to a kind of large-scale segmentation composite wood
Material shell attachment structure and housing winding method.
Background technology
Being connected to during composite structure is designed for fiber winding product occupies critical role.It turns out that, reasonably connect
Connect design to be not only able to meet use requirement, mitigate architecture quality, and can be with the service life of extending structure.Fiber winding method
It is the production preferable process of fibre reinforced composites rocket engine cast.Housing is generally two ends with ball, ellipsoid
Or the cylindrical shell of isostension balanced type end socket, it is not only adapted to the looping connection that fiber winding forming is also beneficial to metal joint.
And the fiber without end socket housing winds and is connected, then be the Pinch technology of composite material casing structure design and moulding process.Should
Class component is in the case where the effect of the load such as internal pressure and additional external force moment of flexure is born, it will usually make winding housing and metal joint connecting portion
This weak link produces destruction and fails first.
Domestic segmentation housing interconnection technique is used for metal engine housing, composite segmentation housing technologies research at present
It is rarely reported, the technology belongs to compared with frontier at home.
The content of the invention
It is an object of the invention to provide a kind of large-scale segmentation composite shell attachment structure and housing winding method, should
Structures and methods can make large-scale segmentation composite material casing high stability connection, automation high Wrapping formed.
In order to solve the above technical problems, a kind of large-scale segmentation composite shell attachment structure disclosed by the invention, it is wrapped
Include left section of rocket engine cast, right section of rocket engine cast, installed in left section of left section of hair of rocket engine cast left end
Motivation shell cover, installed in the left section of left connector of rocket engine cast right-hand member, installed in right section of rocket engine cast
Right section of motor body end socket of right-hand member, installed in the right section of right connector of rocket engine cast left end, it is characterised in that：Institute
State left section of rocket engine cast to be fixedly connected with right connector by left connector with right section of rocket engine cast, the left side
The right-hand member of section rocket engine cast lateral wall is circumferentially provided with first fiber of circle winding and hangs stake, right section of rocket motor casing
The left end of body lateral wall is circumferentially also provided with second fiber of circle winding and hangs stake, is wound in each first fiber by fiber and hung
Spiral winding is carried out between stake and left section of motor body end socket and forms the first spiral inclination winding layer, the winding of the first spiral inclination
Layer wraps up left section of rocket engine cast, carries out ring in the first spiral inclination winding layer outer surface by fiber and is wound
First circumferential winding layer, winds to hang and carry out spiral between stake and right section of motor body end socket by fiber in each second fiber
The second spiral inclination winding layer is wound, the second spiral inclination winding layer wraps up right section of rocket engine cast, by fibre
Dimension carries out ring and is wound the second circumferential winding layer in the second spiral inclination winding layer outer surface.
A kind of winding method of above-mentioned large-scale segmentation composite shell attachment structure moderate heat arrow motor body, its feature
It is that it comprises the following steps：
Step 1：Left section of motor body end socket, left section of rocket engine cast and left connector are respectively installed to core
On, left section of motor body end socket and left connector are arranged on left section of rocket engine cast two ends；
Step 2：Wind to hang in each first fiber by fiber and carry out spiral between stake and left section of motor body end socket
The first spiral inclination winding layer is wound, the first spiral inclination winding layer wraps up left section of rocket engine cast, by fibre
Dimension carries out ring and is wound the first circumferential winding layer in the first spiral inclination winding layer outer surface；
Step 3：What step 2 was obtained is wound with left section of rocket of the first spiral inclination winding layer and the first circumferential winding layer
Motor body is heating and curing, and the demoulding is carried out after the completion of solidification and completes left section of composite material casing.
Beneficial effects of the present invention：
The present invention efficiently solves that adhesive bonding of composites connection transmission load is small, and strength decentralization is big, antistripping ability
With the stress concentration of composite machinery connection, the low problem of joint efficiency；Hang that stake is Wrapping formed realizes the small of continuous fiber
Angle wound is molded without slip, and attachment structure effectively can be connected again.This invention ensures that each section of composite is steady
Determine, be reliably connected, the carrying needs of casing rigidity, rigidity are disclosure satisfy that again, while providing bigger axial tightening power, structure is received
Load is more evenly distributed.
Brief description of the drawings
Fig. 1 is left section of rocket engine cast and the right section of attachment structure schematic diagram of rocket engine cast in the present invention；
Fig. 2 is the left section of structural representation of rocket engine cast winding process in the present invention；
Fig. 3 is the right section of structural representation of rocket engine cast winding process in the present invention.
Wherein, 1-core, 2-left section motor body end socket, the 3-the first spiral inclination winding layer, 3.1-the second spiral shell
Rotation inclination winding layer, the winding of the 4-the first fiber hang stake, the winding of the 4.1-the second fiber and hang stake, 5-left connector, 6-right connection
Part, 7-left section rocket engine cast, 8-U-shaped connection ring, 8.1-extension, the 9-the second pin, 10-cover plate, 11-the
One pin, 12-annular connection bump, 12.1-groove, 13-sealing ring, 14-right section rocket engine cast, 15-right section
Motor body end socket, the 16-the first circumferential winding layer, the 16.1-the second circumferential winding layer, 17-pin-and-hole.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail：
Large-scale segmentation composite shell attachment structure designed by the present invention, as shown in Figures 1 to 3, it includes left section of fire
Arrow motor body 7, right section of rocket engine cast 14, installed in left section of left section of engine of the left end of rocket engine cast 7
Shell cover 2, installed in the left section of left connector 5 of the right-hand member of rocket engine cast 7, installed in right section of rocket engine cast 14
Right section of motor body end socket 15 of right-hand member, installed in the right section of right connector 6 of the left end of rocket engine cast 14, described left section
Rocket engine cast 7 is fixedly connected by left connector 5 with right section of rocket engine cast 14 with right connector 6, the left side
The right-hand member of the section lateral wall of rocket engine cast 7 is circumferentially provided with first fiber of circle winding and hangs (two neighboring first fibre of stake 4
The spacing that dimension winding is hung between stake 4 is equal), the left end of the right section of lateral wall of rocket engine cast 14 is circumferentially also provided with a circle
Stake 4.1 (spacing that two neighboring second fiber winding is hung between stake 4.1 is equal) is hung in the winding of second fiber, by fiber at each
The winding of first fiber is hung and carried out between stake 4 and left section of motor body end socket 2 spiral winding the first spiral inclination winding layer of formation
3, the first spiral inclination winding layer 3 wraps up left section of rocket engine cast 7, by fiber in the first spiral inclination winding layer 3
Outer surface carries out ring and is wound the first circumferential winding layer 16, is wound in each second fiber by fiber and hangs stake 4.1 and the right side
Spiral winding is carried out between section motor body end socket 15 and forms the second spiral inclination winding layer 3.1, the winding of the second spiral inclination
Layer 3.1 wraps up right section of rocket engine cast 14, and ring is carried out in the outer surface of the second spiral inclination winding layer 3.1 by fiber
It is wound the second circumferential winding layer 16.1.
In above-mentioned technical proposal, the connection end of the left connector 5 is provided with U-shaped connection ring 8, the connection end of right connector 6
Annular connection bump 12 is provided with, the annular connection bump 12 is embedded in the U-shaped opening of U-shaped connection ring 8, the U-shaped connection ring 8
Two side and annular connection bump 12 on offer corresponding pin-and-hole 17, the two side of U-shaped connection ring 8 and annular connection bump
The first pin 11 is inserted in 12 pin-and-hole 17.The side wall of inner side is provided with extension 8.1 in the U-shaped connection ring 8, and the annular is even
Connect raised 12 and be provided with groove 12.1 corresponding with extension 8.1, in the insertion groove 12.1 of the extension 8.1, the extension
Sealing ring 13 is provided between 8.1 and groove 12.1.Installed for by the first pin by the second pin 9 in the U-shaped connection ring 8
The cover plate 10 that 11 tops cover.Said structure structure can improve the bonding strength of segmentation housing and meet housing seal requirement, carry
The connective stability of housing high.
In above-mentioned technical proposal, the first spiral inclination winding layer 3 and the second spiral inclination winding layer 3.1 have 16 layers
The thickness of spiral wound, the first spiral inclination winding layer 3 and the second spiral inclination winding layer 3.1 is equal and thickness range
In 2.9mm~3.1mm.
In above-mentioned technical proposal, the circumferential winding layer 16.1 of first circumferential winding layer 16 and second has 7 layers, the first ring
It is equal to the thickness of the circumferential winding layer 16.1 of winding layer 16 and second and thickness range is in 4.0~4.5mm.
In above-mentioned technical proposal, tilting section in the first spiral inclination winding layer 3 and the second spiral inclination winding layer 3.1
Fiber is equal relative to the angle of the left section of axis of rocket engine cast 7, and angular range is 16.7 °~17.5 °.
In above-mentioned technical proposal, for winding housing, the present invention is carried out using the canoe of spiral+ring, design master
To be calculated based on netting theory.
1st, winding angle is calculated
To ensure stability of the fiber on end socket in winding process, the winding of cylinder is set using non-measure line winding angle
Meter, but its actual winding angle can not deviate left section of motor body end socket 2 and right section of motor body end socket 15 is surveyed during design
± 8 ° of alignment winding angle, the left section of calculating at the Geodesic winding angle of motor body end socket 2 is carried out by formula (1)：
In formula：r01It is the left section of radius in the pole hole of motor body end socket 2, r01Equal to 176mm；R is rocket engine cast
Radius, the radius of two housings in left and right is 1100mm；
The right section of Geodesic winding angle of motor body end socket 15 calculates and is carried out by formula (2)：
r02It is the right section of radius in the pole hole of motor body end socket 15, r02Equal to 446mm.
To ensure that left section of motor body end socket 2 and right section of motor body end socket 15 will not be slided in winding process
Line, the winding angle of rocket engine cast is generally red using left section of motor body end socket 2 and right section of motor body end socket 15
The average value that line winding angle sum is determined at diatom is carried out, then its actual winding angle is
The winding angle and left section of motor body end socket 2 and the Geodesic winding angular difference value of right section of motor body end socket 15
It is not in slip phenomenon within 8 °, in winding process.Above winding angle is calculated value, according to line style during actual winding
The actual conditions such as slip, reaming, the point of contact of winding allow trickle change, and the actual winding angle value of this cylinder is at 16.7 °
Between~17.5 °.
In above-mentioned technical proposal, the thickness of the first spiral inclination winding layer 3 and the second spiral inclination winding layer 3.1 is according to public affairs
Formula (4) is calculated：
In formula：[σfb] it is fibre bundle yarn intensity, value is 4200MPa；PbIt is housing design burst pressure, value is
11.5MPa；K is fibre strength mobilization factor, and value is 0.75；kαIt is spiral winding stress equilibrium coefficient, value is 0.75.
Can be calculated the thickness t of the first spiral inclination winding layer 3 and the second spiral inclination winding layer 3.1α=2.92mm；
Winding parameter determination is as follows：Winding silvalin plying number is N=10 strands；Spiral winding cotton yarn tape width b=23mm；Ring
To cotton yarn tape width b '=27mm；
Sub-thread yarn sheet sectional area：
2. single layer fibre cotton yarn tape thickness
Plane cotton yarn tape thickness hα=0.4444/2.3=0.193mm
Ring cotton yarn tape thickness hθ=0.4444/2.7=0.164mm
Then the cylinder spiral winding number of plies is calculated
Because each circulation helical is wound up as 2 layers, the number of plies of spiral winding is even number, therefore, the whole even number of the spiral winding number of plies
It it is 16 layers, then the actual (real) thickness of spiral winding is 0.193 × 16=3.1mm.
Ring winding fiber thickness is calculated according to formula (5)：
Can be calculated tβ=3.83mm, the circumferential winding layer number of cylinder is：
In view of safety coefficient, 26 layers are taken, then ring is to the actual (real) thickness of winding
0.164 × 26=4.3mm；
The gross thickness of cylinder cylinder section fibre is 3.1+4.3=7.4mm
Because winding fiber volume fraction is generally between 58%~65%, 60% is taken herein according to conventional experience, then
The gross thickness of winding layer is
Burst pressure is estimated
(1) cylinder spiral burst strength is estimated by formula (6)
(2) cylinder ring burst strength is estimated by formula (7)
Its burst pressure takes both minimum values by force, then the burst pressure of cylinder is 12.1Mpa, meets burst pressure and is more than
The design requirement of 11.5Mpa.
A kind of winding method of above-mentioned large-scale segmentation composite shell attachment structure moderate heat arrow motor body, its feature
It is that it comprises the following steps：
Step 1：Left section of motor body end socket 2, left section of rocket engine cast 7 and left connector 5 are respectively installed to
On core 1, left section of motor body end socket 2 and left connector 5 are arranged on the left section of two ends of rocket engine cast 7；
Step 2：Wind to hang in each first fiber by fiber and carry out spiral shell between stake 4 and left section of motor body end socket 2
Rotation is wound the first spiral inclination winding layer 3, and the first spiral inclination winding layer 3 wraps up left section of rocket engine cast 7, leads to
Cross fiber and carry out ring in the outer surface of the first spiral inclination winding layer 3 and be wound the first circumferential winding layer 16；
Step 3：What step 2 was obtained is wound with left section of the first spiral inclination winding layer 3 and the first circumferential winding layer 16
Rocket engine cast 7 is heating and curing, and the demoulding is carried out after the completion of solidification and completes left section of composite material casing.
Step 4：Method according to step 1~3 is by right section of rocket engine cast 14, the right section of and of motor body end socket 15
Right connector 6 is installed on core 1, and completes the second spiral inclination winding layer 3.1 and the second circumferential winding layer 16.1
Winding, simultaneously the demoulding completes right section of composite material casing for finally heated solidification.
In above-mentioned technical proposal, the heat curing process is Three-section type heating solidification process, wherein, first paragraph is 95 DEG C
At a temperature of be heating and curing 3 hours, second segment is to be heating and curing 2 hours at a temperature of 125 DEG C, and the 3rd section is 150 DEG C of temperature
Under be heating and curing 6 hours.
The content that this specification is not described in detail belongs to prior art known to professional and technical personnel in the field.
Claims (10)
1. a kind of large-scale segmentation composite shell attachment structure, it includes left section of rocket engine cast (7), right section of rocket hair
Motivation housing (14), installed in left section of left section of motor body end socket (2) of rocket engine cast (7) left end, installed in a left side
The left connector (5) of section rocket engine cast (7) right-hand member, the right section of hair installed in right section of rocket engine cast (14) right-hand member
Motivation shell cover (15), installed in the right section of right connector (6) of rocket engine cast (14) left end, it is characterised in that：Institute
State left section of rocket engine cast (7) and right section of rocket engine cast (14) solid by left connector (5) and right connector (6)
Fixed connection, the right-hand member of left section of rocket engine cast (7) lateral wall is circumferentially provided with first fiber of circle winding and hangs stake
(4), the left end of right section of rocket engine cast (14) lateral wall is circumferentially also provided with second fiber of circle winding and hangs stake
(4.1), spiral is carried out between each first fiber winding extension stake (4) and left section of motor body end socket (2) by fiber to twine
Around the first spiral inclination winding layer (3) is formed, the first spiral inclination winding layer (3) wraps up left section of rocket engine cast (7),
Ring is carried out in first spiral inclination winding layer (3) outer surface by fiber and is wound the first circumferential winding layer (16), passed through
Fiber is hung in the winding of each second fiber and carried out between stake (4.1) and right section of motor body end socket (15) spiral winding formation the
Two spiral inclination winding layers (3.1), the second spiral inclination winding layer (3.1) wraps up right section of rocket engine cast (14), leads to
Cross fiber and carry out ring in second spiral inclination winding layer (3.1) outer surface and be wound the second circumferential winding layer (16.1).
2. large-scale segmentation composite shell attachment structure according to claim 1, it is characterised in that：The left connector
(5) connection end is provided with U-shaped connection ring (8), and the connection end of right connector (6) is provided with annular connection bump (12), the annular
In the U-shaped opening of the U-shaped connection ring (8) of connection bump (12) insertion, the two side of the U-shaped connection ring (8) and annular connection are convex
Rise and corresponding pin-and-hole (17) is offered on (12), the pin-and-hole (17) of U-shaped connection ring (8) two side and annular connection bump (12)
The first pin of middle insertion (11).
3. large-scale segmentation composite shell attachment structure according to claim 2, it is characterised in that：The U-shaped connection
The side wall of inner side is provided with extension (8.1) in ring (8), and the annular connection bump (12) is provided with corresponding with extension (8.1)
Groove (12.1), in the embedded groove (12.1) of the extension (8.1), sets between the extension (8.1) and groove (12.1)
There is sealing ring (13).
4. large-scale segmentation composite shell attachment structure according to claim 3, it is characterised in that：The U-shaped connection
The cover plate (10) for the first pin (11) top to be covered is installed by the second pin (9) on ring (8).
5. large-scale segmentation composite shell attachment structure according to claim 1, it is characterised in that：First spiral
Inclining winding layer (3) and the second spiral inclination winding layer (3.1) has 16 helical layer winding layers, the first spiral inclination winding
The thickness of layer (3) and the second spiral inclination winding layer (3.1) is equal and thickness range is in 2.9mm~3.1mm.
6. large-scale segmentation composite shell attachment structure according to claim 1, it is characterised in that：First ring
Winding layer (16) and the second circumferential winding layer (16.1) have 7 layers, the first circumferential winding layer (16) and the second circumferential winding layer
(16.1) thickness is equal and thickness range is in 4.0~4.5mm.
7. large-scale segmentation composite shell attachment structure according to claim 1, it is characterised in that：First spiral
Inclination section fibre is relative to left section of rocket engine cast (7) in inclining winding layer (3) and the second spiral inclination winding layer (3.1)
The angle of axis is equal, and angular range is 16.7 °~17.5 °.
8. the winding side of large-scale segmentation composite shell attachment structure moderate heat arrow motor body described in a kind of claim 1
Method, it is characterised in that it comprises the following steps：
Step 1：Left section of motor body end socket (2), left section of rocket engine cast (7) and left connector (5) are respectively mounted
Onto core (1), by left section of motor body end socket (2) and left connector (5) installed in left section of rocket engine cast (7) two
End；
Step 2：Wind to hang in each first fiber by fiber and carry out spiral shell between stake (4) and left section of motor body end socket (2)
Rotation is wound the first spiral inclination winding layer (3), and the first spiral inclination winding layer (3) is by left section of rocket engine cast (7)
Parcel, carries out ring and is wound the first circumferential winding layer (16) by fiber in first spiral inclination winding layer (3) outer surface；
Step 3：What step 2 was obtained is wound with left section of the first spiral inclination winding layer (3) and the first circumferential winding layer (16)
Rocket engine cast (7) is heating and curing, and the demoulding is carried out after the completion of solidification and completes left section of composite material casing.
9. the winding method of rocket engine cast according to claim 8, it is characterised in that：Also walked after the step 3
Rapid 4, method according to step 1~3 is by right section of rocket engine cast (14), right section of motor body end socket (15) and right connection
Part (6) is installed on core (1), and completes the second spiral inclination winding layer (3.1) and the second circumferential winding layer (16.1)
Winding, finally heated solidification and the demoulding complete right section of composite material casing.
10. the winding method of rocket engine cast according to claim 8 or claim 9, it is characterised in that：It is described to be heating and curing
Process is Three-section type heating solidification process, wherein, to be heating and curing 3 hours at a temperature of 95 DEG C, second segment is 125 DEG C to first paragraph
At a temperature of be heating and curing 2 hours, the 3rd section be 150 DEG C at a temperature of be heating and curing 6 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611069154.1A CN106762222B (en) | 2016-11-29 | 2016-11-29 | Large-scale segmentation composite shell attachment structure and housing winding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611069154.1A CN106762222B (en) | 2016-11-29 | 2016-11-29 | Large-scale segmentation composite shell attachment structure and housing winding method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106762222A true CN106762222A (en) | 2017-05-31 |
| CN106762222B CN106762222B (en) | 2018-03-09 |
Family
ID=58905051
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611069154.1A Active CN106762222B (en) | 2016-11-29 | 2016-11-29 | Large-scale segmentation composite shell attachment structure and housing winding method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106762222B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107127981A (en) * | 2017-06-26 | 2017-09-05 | 江苏恒神股份有限公司 | Carbon fiber composite material casing forming method |
| CN109049763A (en) * | 2018-07-16 | 2018-12-21 | 江苏新扬新材料股份有限公司 | A kind of manufacturing method of high-temperature fibre wound composite shell |
| CN109681345A (en) * | 2018-12-28 | 2019-04-26 | 湖北航天技术研究院总体设计所 | Ultra-large type solid propellant rocket segmented composite material casing and its manufacturing method |
| CN109968686A (en) * | 2019-05-13 | 2019-07-05 | 哈尔滨玻璃钢研究院有限公司 | A kind of Filament Wound Composite device and assembly method |
| CN111959004A (en) * | 2020-07-27 | 2020-11-20 | 江苏新扬新材料股份有限公司 | Carrier rocket engine shell reinforcing method |
| CN112297465A (en) * | 2020-09-02 | 2021-02-02 | 江苏新扬新材料股份有限公司 | Large composite material rocket engine shell winding method |
| CN114043745A (en) * | 2021-11-04 | 2022-02-15 | 合肥工业大学 | Fiber winding method and system applied to combined revolving body with concave curved surface |
| CN115307052A (en) * | 2022-08-15 | 2022-11-08 | 佛山仙湖实验室 | Optimal design method for winding enhancement layer of composite gas cylinder and application thereof |
| CN115416327A (en) * | 2022-07-29 | 2022-12-02 | 上海复合材料科技有限公司 | Composite material shell suitable for large-aperture-ratio solid rocket engine and winding forming method |
| WO2023024394A1 (en) * | 2021-08-25 | 2023-03-02 | 江苏国富氢能技术装备股份有限公司 | Carbon fiber fully-wound gas cylinder and carbon fiber winding method therefor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1052926A (en) * | 1989-12-29 | 1991-07-10 | 赵永青 | Solid propellant rocket fiber winding shell reversal nozzle joint chair filament winding process |
| US20030021974A1 (en) * | 2001-06-01 | 2003-01-30 | Steffen Beyer | Combustion chamber with internal jacket made of a ceramic composite material and process for manufacture |
| RU2320886C1 (en) * | 2006-05-30 | 2008-03-27 | Открытое акционерное общество Научно-производственное объединение "Искра" | Solid-propellant rocket engine |
| CN102632683A (en) * | 2012-03-30 | 2012-08-15 | 湖北三江航天江北机械工程有限公司 | Manufacturing method for manual patch of heat insulating layer of filament winding engine shell |
| CN103328192A (en) * | 2010-10-11 | 2013-09-25 | 吉凯恩航空服务有限公司 | Method of manufacturing a composite structure and composite structure obtained thereby |
| CN104354436A (en) * | 2014-11-07 | 2015-02-18 | 湖北三江航天江北机械工程有限公司 | Manufacturing method of composite material shell wound by high-temperature-resistant fiber |
-
2016
- 2016-11-29 CN CN201611069154.1A patent/CN106762222B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1052926A (en) * | 1989-12-29 | 1991-07-10 | 赵永青 | Solid propellant rocket fiber winding shell reversal nozzle joint chair filament winding process |
| US20030021974A1 (en) * | 2001-06-01 | 2003-01-30 | Steffen Beyer | Combustion chamber with internal jacket made of a ceramic composite material and process for manufacture |
| RU2320886C1 (en) * | 2006-05-30 | 2008-03-27 | Открытое акционерное общество Научно-производственное объединение "Искра" | Solid-propellant rocket engine |
| CN103328192A (en) * | 2010-10-11 | 2013-09-25 | 吉凯恩航空服务有限公司 | Method of manufacturing a composite structure and composite structure obtained thereby |
| CN102632683A (en) * | 2012-03-30 | 2012-08-15 | 湖北三江航天江北机械工程有限公司 | Manufacturing method for manual patch of heat insulating layer of filament winding engine shell |
| CN104354436A (en) * | 2014-11-07 | 2015-02-18 | 湖北三江航天江北机械工程有限公司 | Manufacturing method of composite material shell wound by high-temperature-resistant fiber |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107127981A (en) * | 2017-06-26 | 2017-09-05 | 江苏恒神股份有限公司 | Carbon fiber composite material casing forming method |
| CN109049763A (en) * | 2018-07-16 | 2018-12-21 | 江苏新扬新材料股份有限公司 | A kind of manufacturing method of high-temperature fibre wound composite shell |
| CN109681345A (en) * | 2018-12-28 | 2019-04-26 | 湖北航天技术研究院总体设计所 | Ultra-large type solid propellant rocket segmented composite material casing and its manufacturing method |
| CN109968686A (en) * | 2019-05-13 | 2019-07-05 | 哈尔滨玻璃钢研究院有限公司 | A kind of Filament Wound Composite device and assembly method |
| CN109968686B (en) * | 2019-05-13 | 2024-05-03 | 哈尔滨玻璃钢研究院有限公司 | Composite material winding device and assembly method |
| CN111959004A (en) * | 2020-07-27 | 2020-11-20 | 江苏新扬新材料股份有限公司 | Carrier rocket engine shell reinforcing method |
| CN112297465A (en) * | 2020-09-02 | 2021-02-02 | 江苏新扬新材料股份有限公司 | Large composite material rocket engine shell winding method |
| WO2023024394A1 (en) * | 2021-08-25 | 2023-03-02 | 江苏国富氢能技术装备股份有限公司 | Carbon fiber fully-wound gas cylinder and carbon fiber winding method therefor |
| CN114043745A (en) * | 2021-11-04 | 2022-02-15 | 合肥工业大学 | Fiber winding method and system applied to combined revolving body with concave curved surface |
| CN115416327A (en) * | 2022-07-29 | 2022-12-02 | 上海复合材料科技有限公司 | Composite material shell suitable for large-aperture-ratio solid rocket engine and winding forming method |
| CN115307052A (en) * | 2022-08-15 | 2022-11-08 | 佛山仙湖实验室 | Optimal design method for winding enhancement layer of composite gas cylinder and application thereof |
| CN115307052B (en) * | 2022-08-15 | 2024-05-28 | 佛山仙湖实验室 | Optimal design method for winding reinforcing layer of composite gas cylinder and application thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106762222B (en) | 2018-03-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106762222B (en) | Large-scale segmentation composite shell attachment structure and housing winding method | |
| US10508682B2 (en) | Composite torque tube end fitting attachment method | |
| CN108453969A (en) | Method for manufacturing wind turbine rotor blade root interval and relevant wind turbine blade | |
| CN109306512B (en) | Solidifying heat-preserving cylinder | |
| CN107283876A (en) | A kind of method for preparing fibre reinforced fold sandwich cylindrical shell | |
| CN102290780B (en) | Cold-shrinkable type rubber sleeve | |
| CN106574602B (en) | Reinforced wind turbine blade component | |
| CN109494544A (en) | A kind of 7 strand steel strand wires of aerial condutor dock embedding aluminium crimping structure and method | |
| CN105965866B (en) | Motor body and jet pipe integral formation method | |
| CN105719768B (en) | Aerial condutor aluminium packet fiber-reinforced composite core and its manufacturing method | |
| CN212359302U (en) | Insulating cross arm and power transmission pole | |
| CN107667201A (en) | A kind of modularization fiber reinforced plastic electric wire pole | |
| WO2016206199A1 (en) | External rotor motor | |
| CN110239111A (en) | A kind of composite material tube body and connector integrated molding method | |
| CN207553711U (en) | Composite material electric pole | |
| CN107453516A (en) | The manufacture of wind-driven generator SMC insulated end covers | |
| CN112081450A (en) | Insulating cross arm, manufacturing method thereof and power transmission pole | |
| CN112081449A (en) | Insulating cross arm, manufacturing method thereof and power transmission pole | |
| CN203787125U (en) | Fixing lantern ring for water-cooled cable | |
| CN206312667U (en) | A kind of hollow combined insulator | |
| CN111140711A (en) | Bundle section structure based on integral rubber ring and preparation method thereof | |
| CN213990076U (en) | Connecting hardware fitting and insulating cross arm | |
| CN206802584U (en) | A kind of sealing structure of composite soft tube | |
| CN219163063U (en) | Cable sealing structure | |
| CN108443609A (en) | A kind of anti-corrosion high voltage-resistant multiunit tube joint and attaching method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |