CN108692181A - A kind of preparation method of composites gas cylinder - Google Patents
A kind of preparation method of composites gas cylinder Download PDFInfo
- Publication number
- CN108692181A CN108692181A CN201810267047.2A CN201810267047A CN108692181A CN 108692181 A CN108692181 A CN 108692181A CN 201810267047 A CN201810267047 A CN 201810267047A CN 108692181 A CN108692181 A CN 108692181A
- Authority
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- China
- Prior art keywords
- gas cylinder
- winding
- end socket
- composites gas
- shell portion
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C1/00—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
- F17C1/02—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge involving reinforcing arrangements
- F17C1/04—Protecting sheathings
- F17C1/06—Protecting sheathings built-up from wound-on bands or filamentary material, e.g. wires
-
- 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
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C13/00—Details of vessels or of the filling or discharging of vessels
- F17C13/002—Details of vessels or of the filling or discharging of vessels for vessels under pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C13/00—Details of vessels or of the filling or discharging of vessels
- F17C13/06—Closures, e.g. cap, breakable member
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/01—Shape
- F17C2201/0104—Shape cylindrical
- F17C2201/0109—Shape cylindrical with exteriorly curved end-piece
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/03—Orientation
- F17C2201/032—Orientation with substantially vertical main axis
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/05—Size
- F17C2201/056—Small (<1 m3)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2203/00—Vessel construction, in particular walls or details thereof
- F17C2203/06—Materials for walls or layers thereof; Properties or structures of walls or their materials
- F17C2203/0634—Materials for walls or layers thereof
- F17C2203/0658—Synthetics
- F17C2203/0663—Synthetics in form of fibers or filaments
- F17C2203/067—Synthetics in form of fibers or filaments helically wound
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
- F17C2205/03—Fluid connections, filters, valves, closure means or other attachments
- F17C2205/0302—Fittings, valves, filters, or components in connection with the gas storage device
- F17C2205/0311—Closure means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2209/00—Vessel construction, in particular methods of manufacturing
- F17C2209/21—Shaping processes
- F17C2209/2154—Winding
- F17C2209/2163—Winding with a mandrel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2270/00—Applications
- F17C2270/01—Applications for fluid transport or storage
- F17C2270/0186—Applications for fluid transport or storage in the air or in space
- F17C2270/0197—Rockets
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Moulding By Coating Moulds (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The present invention relates to a kind of preparation methods of composites gas cylinder, are related to composite material pressure container manufacturing technology field.The method includes:Composites gas cylinder spiral is to winding layer by the way of reaming step by step, each winding angle is determined by the linear track of geodesic curve, and during the winding process, using Non-geodesic winding mode, varied angle gear ratio winding is carried out in seal head section, varying pitch winding is carried out in shell portion fringe region, make end socket region each point winding angle is opposite to increase, each in " fiber accumulations ring ", the difference of outer radius improves the practical yarn sheet width between 1.5 times -2 times, end socket is set to level off to equal thickness, end socket excess mass can effectively be reduced, improve container characteristics coefficient, reach the light-weighted purpose of gas cylinder.
Description
Technical field
The present invention relates to a kind of preparation methods of composites gas cylinder, belong to composite material pressure container manufacturing technology neck
Domain.
Background technology
Composites gas cylinder has many advantages, such as that light-weight, pressure tolerance is high, reliability is high, antifatigue, corrosion-resistant, is a kind of
More satisfactory high-strength light, high-performance gas cylinder, disclosure satisfy that aerospace components efficiently, the requirement of loss of weight.It has transported both at home and abroad
It carries in the Space Vehicle Systems such as rocket, space shuttle, artificial satellite, space station and has used composites gas cylinder, such as:HS2601,
HS2702 satellite platforms, Centaur carrier rockets Upper Stage and country's XX-5, XX-7 carrier rocket etc..The success of spacecraft
Huge cost needed for transmitting and potential technology risk, composites gas cylinder is carried in loss of weight, reliability, pressure tolerance etc.
Harsh requirement is gone out.
Composites gas cylinder spiral mostly uses greatly multi-angle reaming canoe step by step to winding layer, i.e., by each spiral winding
The winding angle of layer gradually increases since the minimum winding angle tangent with bottleneck, " the fiber accumulations at the hole of rear screw winding layer pole
Ring " internal diameter is just greater than " fiber accumulations ring " outer diameter at the hole of upper spiral wound pole, i.e., each " fiber accumulations ring " inside and outside half
The difference of diameter is not more than 1.5 times of practical yarn sheet width.In this way, after the completion of multi-angle spiral winding layer, in composites gas cylinder
End socket region is formd from bottleneck circumference to the more uniform several fiber accumulations rings in periphery.
Although reaming winding not only makes end socket change in shape tend towards stability to multi-angle step by step, the excess accumulation of fiber is avoided
With it is aerial, so that the intensity for each winding angle fiber accumulated at the hole of pole has been obtained more uniform distribution, be effectively reduced compound
Weight at material cylinder end socket, but reaming canoe does not consider liner Seal Head Strength in Intensity Design step by step, causes to seal
Head Intensity Design is excessively conservative.Composites gas cylinder destroys, end socket region is still from the point of view of practical explosion bulge test for shell portion simultaneously
The phenomenon that there are the density of load " surpluses ".
Invention content
The technology of the present invention solves the problems, such as:The problem of for the composites gas cylinder end socket region density of load " surplus ",
Overcome the deficiencies in the prior art proposes a kind of preparation method of composites gas cylinder.
Technical solution of the invention is:
A kind of preparation method of composites gas cylinder, it is characterised in that:The composites gas cylinder includes liner and composite wood
The bed of material;The step of this method includes:
(1) according to the design requirement of composites gas cylinder, the Intensity Design of composites gas cylinder composite layer is carried out, is obtained
To spiral to the thickness of the winding layer and number of plies, the thickness of the circumferential winding layer and number of plies;
(2) spiral obtained according to step (1) is to the thickness and the number of plies of winding layer, and adjoining spiral is to winding layer by 1.2-
1.3 times of bandwidth carry out end socket reaming winding design, and each winding layer carries out Trajectory Design according to geodesic mode, obtains each spiral
To the winding angle and quantity of winding layer, shell portion intensity is checked so that the longitudinal strength and ring of composites gas cylinder
It is almost the same to intensity;
(3) it is wound to winding angle according to each spiral that step (2) obtains in shell portion, n times is pressed in end socket region
Bandwidth carries out end socket reaming winding;
(4) end socket field strength is checked, so that Seal Head Strength is higher than shell portion intensity, so that it is determined that in step (3)
N optimal value;
(5) the winding layer number and winding angle for pressing above step design, are wound molding;
(6) cure.
The longitudinal strength of composites gas cylinder and circumferential intensity are almost the same in the step (2), generally composite wood
Expect that the longitudinal strength of gas cylinder is slightly above circumferential intensity, difference is generally not more than 2%.
The determination method of n in the step (3) is:The initial value of n is set first as 1.3, to end socket field strength into
Row is checked, if Seal Head Strength is higher than shell portion intensity, n values are increased, then is checked to end socket field strength, if envelope
Head intensity is higher than shell portion intensity, continues growing n values, until Seal Head Strength is less than shell portion intensity, then inverted second of n values
Value.
The determination method of n in the step (3) is:The initial value of n is set first as 1.3, to end socket field strength into
Row is checked, if Seal Head Strength is higher than shell portion intensity, n values is increased by 0.1, then check to end socket field strength, such as
Fruit Seal Head Strength is higher than shell portion intensity, continues growing n values, and when n values are 2.1, Seal Head Strength is less than shell portion intensity, then n values
Take 2.0.
N value ranges in the step (3) are more than 1.3, optimum range 1.5-2.0.
Reinforcing fiber used in the composite layer is one kind in carbon fiber, glass fibre, organic fiber
Or two or more mixing.
It is wound using Wet Winding Process or dry method when being wound molding in the step (5).
The liner is metal inner lining or plastic inner lining.
In the step (6), solidification temperature is 140 DEG C to 180 DEG C, and hardening time is 2 hours to 6 hours.
Advantageous effect
(1) method of the invention should be smaller winding angle as possible in composites gas cylinder shell portion spiral wound, with
Ensure gas cylinder longitudinal strength, and so that winding angle is increased in seal head section, is excessively accumulated near bottle neck to avoid fiber, cause to seal
Head position weight increases.Accordingly, optimization is proposed to the winding process of reaming step by step of the lightweight composites gas cylinder of space flight
Scheme.I.e. in composites gas cylinder Intensity Design, spiral wound presses geodesic curve line by the way of conventional reaming step by step
Shape track determines each winding angle, to ensure the longitudinal strength of shell portion, and uses Non-geodesic winding mode during the winding process,
Varied angle gear ratio winding is carried out in seal head section, or even varying pitch winding is carried out in shell portion fringe region, so that end socket region
Each winding angle is opposite to be increased, and the difference of each " fiber accumulations ring " inside and outside radius is made to improve the practical yarn sheet between 1.5 times -2 times
Width.
(2) spiral meets Geodesic winding to shell portion Alignment Design in method of the invention, and linear track is not at end socket
It is linear to meet geodesic curve.By each winding angle of the linear Trajectory Design of geodesic curve, to ensure shell portion longitudinal strength;In order to reduce end socket
Passive quality makes end socket be intended to equal thickness, and end socket region is designed for varying pitch, two neighboring fiber accumulations central spacer improve to
1.5 times of -2 times of winding yarn sheet width.
(3) Non-geodesic winding mode is used in method of the invention, shell portion is linear to meet geodetic line tracking;At end socket
Linear track does not meet Geodesic winding track;It is wound for gear ratio varying pitch at end socket;Each winding angle in end socket region is opposite to be increased
Greatly, the winding yarn sheet width that the difference of each " fiber accumulations ring " inside and outside radius is 1.5 times -2 times.Liner can be metal inner lining, non-
Metal inner lining;
(4) reinforcing fiber can be carbon fiber, glass fibre or organic fiber or two kinds or two in method of the invention
Kind or more composite fibre, if innermost layer and outermost layer reinforcing fiber are glass fibre, centre uses carbon fiber.
(5) moulding process of the invention can be that Wet Winding Process or dry method are wound.By process optimization, ensureing composite material
Under the premise of the mechanical property of gas cylinder, fibre bundle flattening property more preferably characteristic in larger winding angle can be played, end socket shape is made
Variation more tends towards stability, and shell portion and the circumferential intensity of end socket transition portion can be made also to have obtained effective reinforcement, particularly heavy
What is wanted is the excessive accumulation for avoiding fiber in end socket close to bottle neck region, ensure shell portion weight be basically unchanged in the case of into
One step alleviates the weight at composites gas cylinder end socket, has reached the improved purpose of composites gas cylinder lightweight.Purpose is
In order to reduce composites gas cylinder passiveness quality, reach the light-weighted purpose of gas cylinder.This method is suitable for fiber-reinforced resin base
Composite material pressure container designs and molding.
(6) the present invention relates to a kind of composites gas cylinder lightweight Alignment Design and technique optimization method, it is related to composite wood
Expect pressure vessel manufacturing technical field.The method includes:Composites gas cylinder spiral wound is using conventional reaming step by step
Mode, determine each winding angle by the linear track of geodesic curve, and during the winding process, using Non-geodesic winding mode, sealing
Head section carries out varied angle gear ratio winding, carries out varying pitch winding in shell portion fringe region, makes each winding angle phase in end socket region
To increasing, the difference of each " fiber accumulations ring " inside and outside radius improves the practical yarn sheet width between 1.5 times -2 times, makes end socket
It levels off to equal thickness, can effectively reduce end socket passiveness quality, improve container characteristics coefficient, reach the improved mesh of gas cylinder lightweight
's.
Description of the drawings
Fig. 1 is end socket reaming schematic diagram.
Specific implementation mode
A kind of preparation method of composites gas cylinder, the composites gas cylinder include aluminium alloy lining and composite layer;
The step of this method includes:
(1) according to the design requirement of composites gas cylinder, the Intensity Design of composites gas cylinder composite layer is carried out;
(2) each winding layer carries out Lay up design according to geodesic mode, and adjoining spiral presses 1.2-1.3 times of band to winding layer
Width carries out end socket reaming winding, is checked to shell portion intensity;
(3) according to cylinder design theory, end socket composite layer intensity is higher than shell portion, and during Intensity Design
Liner end socket bearing capacity is not considered, causes gas cylinder Seal Head Strength superfluous, can pass through the thickness of reduction end socket composite layer
Degree achievees the purpose that loss of weight.So obtaining each spiral to winding angle according to step (2), optimization design is carried out to it,
Shell portion keeps former winding angle, carries out end socket reaming winding by 1.5-2.0 times of bandwidth in end socket region, i.e. non-survey is pressed in end socket region
Ground wire mode is wound;
(4) end socket field strength is checked, meets Seal Head Strength and is higher than shell portion intensity;
(5) it is wound molding by winding layer;
(6) cure;
(7) hydraulic bursting test is carried out.
The invention will be further described with example below in conjunction with the accompanying drawings.
Embodiment
A kind of preparation method of composites gas cylinder, the composites gas cylinder include aluminium alloy lining and composite layer;
The step of this method includes:
(1) certain 9L composites gas cylinder design strength 70MPa, liner outer diameter 167mm, length 516mm, reinforcing fiber are
T1000。
(2) each winding layer carries out Lay up design according to geodesic mode, and adjoining spiral presses 1.2-1.3 times of band to winding layer
Width carries out end socket reaming winding, and ply stacking-sequence is ± 90 °2/±11°/±90°/±16°/±90°/±21°/±90°/±
27°/±90°/±33°;
(3) former winding angle is kept in shell portion, end socket reaming winding, envelope is carried out by 1.6-1.7 times of bandwidth in end socket region
Head winding angle becomes 11 °, 18 °, 25 °, 33 ° and 42 °;
(4) it presses (2) and (3) described laying angle and ply stacking-sequence is wound molding;
(6) cure according to 70 DEG C/2h+120 DEG C/2h+150 DEG C/3h;
(7) hydraulic bursting test is carried out, burst strength 78.7MPa, PV/W value is 59.7km.The result shows that the process modification
Effect of the scheme in terms of composites gas cylinder loss of weight is quite apparent, and the lightweight for being particularly suitable for aerospace composite gas cylinder is set
Meter and manufacture.
Claims (10)
1. a kind of preparation method of composites gas cylinder, it is characterised in that:The composites gas cylinder includes liner and composite material
Layer;The step of this method includes:
(1) according to the design requirement of composites gas cylinder, the Intensity Design of composites gas cylinder composite layer is carried out, spiral shell is obtained
The thickness and the number of plies of rotation direction winding layer, the thickness and the number of plies of circumferential winding layer;
(2) spiral obtained according to step (1) is to the thickness and the number of plies of winding layer, and adjoining spiral is to winding layer by 1.2-1.3 times
Bandwidth carries out end socket reaming winding design, and each winding layer carries out Trajectory Design according to geodesic mode, obtains each spiral to twining
The winding angle and quantity of winding layer, check shell portion intensity so that the longitudinal strength and circumferential direction of composites gas cylinder are strong
The difference of degree meets design requirement;
(3) it is wound to winding angle according to each spiral that step (2) obtains in shell portion, n times of bandwidth is pressed in end socket region
Carry out end socket reaming winding;
(4) end socket field strength is checked, Seal Head Strength is made to be higher than shell portion intensity, so that it is determined that the n in step (3)
Optimal value;
(5) the winding layer number and winding angle for pressing above step design, are wound molding;
(6) cure.
2. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The step (2)
The difference of the longitudinal strength of middle composites gas cylinder and circumferential intensity meets design requirement and refers to:The longitudinal direction of composites gas cylinder is strong
Degree is not higher than 2% higher than circumferential intensity, difference.
3. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The step (3)
In the determination method of n be:The initial value of n is set first as 1.3, end socket field strength is checked, if Seal Head Strength is high
In shell portion intensity, then n values are increased, then end socket field strength is checked, if Seal Head Strength is higher than shell portion intensity,
N values are continued growing, until Seal Head Strength is less than shell portion intensity, then inverted second of n values are worth.
4. a kind of preparation method of composites gas cylinder according to claim 2, it is characterised in that:The step (3)
In the determination method of n be:The initial value of n is set first as 1.3, end socket field strength is checked, if Seal Head Strength is high
In shell portion intensity, then n values are increased by 0.1, then check to end socket field strength, if Seal Head Strength is strong higher than shell portion
Degree, continues growing n values, and when n values are 2.1, Seal Head Strength is less than shell portion intensity, then n values take 2.0.
5. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The step (3)
In n value ranges be more than 1.3.
6. a kind of preparation method of composites gas cylinder according to claim 5, it is characterised in that:N value ranges are
1.5-2.0。
7. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The composite material
Reinforcing fiber used in layer is the mixing of one or more of carbon fiber, glass fibre, organic fiber.
8. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The step (5)
In wound using Wet Winding Process or dry method when being wound molding.
9. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The liner is gold
Belong to liner or plastic inner lining.
10. a kind of preparation method of composites gas cylinder according to claim 1, it is characterised in that:The step (6)
In, solidification temperature is 140 DEG C to 180 DEG C, and hardening time is 2 hours to 6 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810267047.2A CN108692181B (en) | 2018-03-28 | 2018-03-28 | Preparation method of composite material gas cylinder |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810267047.2A CN108692181B (en) | 2018-03-28 | 2018-03-28 | Preparation method of composite material gas cylinder |
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| CN108692181A true CN108692181A (en) | 2018-10-23 |
| CN108692181B CN108692181B (en) | 2020-08-14 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113128088A (en) * | 2021-04-02 | 2021-07-16 | 华东师范大学 | Winding line type design method and system for composite material pressure container |
| CN113478791A (en) * | 2021-07-16 | 2021-10-08 | 合肥工业大学 | Preparation method of woven gas cylinder and woven gas cylinder |
| CN114248477A (en) * | 2022-01-25 | 2022-03-29 | 南通中集能源装备有限公司 | Method for forming body of plastic lining high-pressure gas cylinder |
| 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 |
| WO2024041262A1 (en) * | 2022-08-25 | 2024-02-29 | 中材科技（苏州）有限公司 | Method for manufacturing compositely molded 99-mpa-grade hydrogen storage container for hydrogen refueling station |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5032016A (en) * | 1987-01-23 | 1991-07-16 | Thiokol Corporation | Radiation gathering reflector and method of manufacture |
| US5526994A (en) * | 1994-12-01 | 1996-06-18 | Essef Corporation | Filament-wound isotensoid pressure vessels having geodesic domes |
| EP0744274A2 (en) * | 1995-02-27 | 1996-11-27 | ESSEF Corporation | Hydropneumatic filament wound pressure vessel |
| RU2210697C2 (en) * | 2001-06-05 | 2003-08-20 | Общество с ограниченной ответственностью НПО "ПОИСК" | High-pressure metal-plastic cylinder, method of and device for checking serviceability of metal-plastic cylinder |
| CN102211405A (en) * | 2010-04-09 | 2011-10-12 | 航天材料及工艺研究所 | Process for forming light-weight and high-pressure gas bottle made of composite material |
| WO2012144929A1 (en) * | 2011-04-21 | 2012-10-26 | Lukyanets Sergei Vladimirovich | High-pressure vessel made of composite materials |
| CN103076331A (en) * | 2013-01-06 | 2013-05-01 | 航天材料及工艺研究所 | Wiring method for fibers for monitoring composite cylinder |
| CN104015345A (en) * | 2014-06-11 | 2014-09-03 | 沈阳航天新光集团有限公司 | Winding fabrication process method of ultrahigh-pressure composite gas cylinder |
| CN107850259A (en) * | 2016-02-12 | 2018-03-27 | 富饶科技有限公司德国分公司 | Strengthen the pressure vessel of end socket |
-
2018
- 2018-03-28 CN CN201810267047.2A patent/CN108692181B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5032016A (en) * | 1987-01-23 | 1991-07-16 | Thiokol Corporation | Radiation gathering reflector and method of manufacture |
| US5526994A (en) * | 1994-12-01 | 1996-06-18 | Essef Corporation | Filament-wound isotensoid pressure vessels having geodesic domes |
| EP0744274A2 (en) * | 1995-02-27 | 1996-11-27 | ESSEF Corporation | Hydropneumatic filament wound pressure vessel |
| RU2210697C2 (en) * | 2001-06-05 | 2003-08-20 | Общество с ограниченной ответственностью НПО "ПОИСК" | High-pressure metal-plastic cylinder, method of and device for checking serviceability of metal-plastic cylinder |
| CN102211405A (en) * | 2010-04-09 | 2011-10-12 | 航天材料及工艺研究所 | Process for forming light-weight and high-pressure gas bottle made of composite material |
| WO2012144929A1 (en) * | 2011-04-21 | 2012-10-26 | Lukyanets Sergei Vladimirovich | High-pressure vessel made of composite materials |
| CN103076331A (en) * | 2013-01-06 | 2013-05-01 | 航天材料及工艺研究所 | Wiring method for fibers for monitoring composite cylinder |
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