CN105674041A - Spherical composite gas cylinder for spaceflight - Google Patents
Spherical composite gas cylinder for spaceflight Download PDFInfo
- Publication number
- CN105674041A CN105674041A CN201610059330.7A CN201610059330A CN105674041A CN 105674041 A CN105674041 A CN 105674041A CN 201610059330 A CN201610059330 A CN 201610059330A CN 105674041 A CN105674041 A CN 105674041A
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- Prior art keywords
- gas cylinder
- spherical shell
- spherical
- boss
- adhesive layer
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Classifications
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- 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
-
- 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
-
- 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
- F17C2201/0128—Shape spherical or elliptical
-
- 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
- F17C2203/0602—Wall structures; Special features thereof
- F17C2203/0604—Liners
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- 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
- F17C2203/0636—Metals
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- 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
-
- 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
- F17C2205/0305—Bosses, e.g. boss collars
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- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a spherical composite gas cylinder for spaceflight. The spherical composite gas cylinder for spaceflight comprises a metal lining, an adhesive layer and a composite layer, wherein the adhesive layer is laid on the outer surface of the metal lining, and the composite layer is wound around the outer surface of the adhesive layer. The metal lining is composed of a spherical shell, a filler neck and a boss. The filler neck and the boss are located at the peaks of the two ends of the axis of the spherical shell correspondingly. Iso-wall thickness design is adopted in the thin film region of the spherical shell. Gradual-change thickness reinforcement design is adopted in the connection transition region of the spherical shell and the filler neck and the connection transition region of the spherical shell and the boss. The adhesive layer is evenly laid on the outer surface of the spherical shell, so that the spherical shell and the composite layer are firmly connected and prevented from making direct contact with each other. The spherical composite gas cylinder for spaceflight solves the problems that an existing composite gas cylinder is singular in structural form and a metal gas cylinder is low in structural efficiency, poor in installation space adaptability and the like. The spherical composite gas cylinder for spaceflight has the good beneficial effects of being low in structural mass, high in reliability, good in safety, high in space adaptability and the like.
Description
Technical field
The present invention relates to a kind of space flight storage sphere, concrete, relate to a kind of thin-wall metal liner/filament wound composite gas cylinder.
Background technology
Composites gas cylinder is widely applied at space industry because of its higher structure efficiency and the not quick-fried safety failure mode first leaked, and becomes one of most important stand-alone device of aerospace system. Along with the space flight development to the improving constantly of the performance requirements such as structure efficiency, reliability and safety, high-performance fiber winding material and winding process technology thereof, the complete substituted metal material cylinder of composites gas cylinder points the day and await for it.
The purposes of Composite Material in Space gas cylinder mainly carries high-pressure gas medium, for aerospace system offer work source of the gas. Composites gas cylinder development starts from the 1950's, progressively being developed into metal inner lining and Kevlar fiber, the contour performance fiber composite layer of carbon fiber of today by the rubber liner of early stage and glass fiber compound material layer, the combination property such as its structure efficiency, reliability and safety is greatly improved.
At present, the composites gas cylinder that aerospace system uses is nearly all cylindricality composites gas cylinder, and spherical composites gas cylinder not yet obtains practicality. This is primarily due to the design of cylindricality composites gas cylinder and manufacture is easier, technology maturation, and structure efficiency is high, develops and use experience is enriched; And the design of spherical composites gas cylinder and manufacture difficulty are big, technology is immature, lacks and develops and use experience, causes that structure efficiency is lower than cylindricality composites gas cylinder. Thus, the aerospace system newly developed is in order to alleviate architecture quality, improve reliability and safety, reduction developing risk generally first-selected cylindricality composites gas cylinder.
But, some aerospace system needs to adopt storage sphere because of its special installing space restriction, but owing to spherical composites gas cylinder is still immature, so having to use metal material gas cylinder. This had both added architecture quality, reduced again safety. In consideration of it, the spherical composites gas cylinder that the combination property such as aerospace system is high in the urgent need to development structure efficiency, safety is good, cost is low is high, to adapt to the development of aerospace industry.
Summary of the invention
In order to meet the requirements such as the special installing space needs of aerospace system, harsh architecture quality, high reliability and safety, the invention provides a kind of spherical composites gas cylinder of space flight.
For achieving the above object, the technical scheme that the present invention takes is:
A kind of spherical composites gas cylinder of space flight, including metal inner lining, it is laid in the adhesive layer of metal inner lining outer surface and is wrapped in the composite layer of adhesive layer outer surface, described metal inner lining is by spherical shell, pressure inlet and boss composition, pressure inlet and boss lay respectively at two endvertexs of spherical shell axis, the wall thickness designs such as the thin film region employing of spherical shell, connection transitional region at spherical shell with pressure inlet and boss adopts progressive thickness Strengthening Design, described adhesive layer is uniformly laid in the outer surface of spherical shell, spherical shell and composite layer are firmly connected, and prevent spherical shell from directly contacting with composite layer.
Preferably, the material of described metal inner lining is aluminium alloy 6061, and described spherical shell, pressure inlet and boss adopt the Technologies such as punching press, spinning and machining integrally formed, seamless link.
Preferably, the material of described metal inner lining is the one in titanium alloy T A0, TA1, TA2, TA3, TA4, TA5, TA6, TA7, TA8, TA9, TA10 or TC4, described spherical shell 11, pressure inlet 12 and boss 13 adopt forging, machining to shape, assemble welding.
Preferably, described adhesive layer is by having the adhesive film of stronger adhesion strength and good insulating performance or liquid adhesive coating is cured makes.
Preferably, described composite layer adopts multidirectional, multilamellar, planar winding quasi-isotropic winding layer design.
Preferably, described composite layer is by being wrapped in cured on the adhesive layer outside spherical shell forming after high-performance carbon fibre, pbo fiber and Kevlar fiber saturated ring epoxy resins liquid.
The spherical composites gas cylinder that the present invention proposes has compared to spherical metal gas cylinder that architecture quality is little, reliability is high, safety is good, low cost and other advantages, solve an aerospace system composites gas cylinder installing space adaptability difficult problem, enrich the type of aerospace composite gas cylinder. The spherical shell of metal inner lining is firmly connected by adhesive layer with composite layer, is effectively improved the thin spherical shell of the metal inner lining anti-unstability ability in composite layer winding, self-tightening, solidification, hydraulic test and use procedure and anti-fatigue ability. Additionally, by multidirectional, multilamellar, the design of planar winding quasi-isotropic winding layer, it is achieved minimal structure quality optimization design. The spherical composites gas cylinder of gained of the present invention has the features such as lightweight, safety highly reliable, high, low cost and adaptation special mounting space, can be widely used for the space industries such as missile armament, carrier rocket, satellite, airship, space station.
Accompanying drawing explanation
Fig. 1 is the structural representation of a specific embodiment of the spherical composites gas cylinder of a kind of space flight of the embodiment of the present invention.
Fig. 2 is the profile of A in Fig. 1.
Fig. 3 is the structural representation of a kind of space flight of the embodiment of the present invention another specific embodiment of spherical composites gas cylinder.
Fig. 4 is the profile of B in Fig. 3.
Detailed description of the invention
In order to make objects and advantages of the present invention clearly understand, below in conjunction with embodiment, the present invention is further elaborated. Should be appreciated that specific embodiment described herein is only in order to explain the present invention, is not intended to limit the present invention.
Embodiments provide a kind of spherical composites gas cylinder of space flight, by metal inner lining 1, be laid in the adhesive layer 2 of metal inner lining 1 outer surface and be wrapped in the composite layer 3 of adhesive layer 2 outer surface and constitute. Structure according to metal inner lining 1 and manufacturing process, have two kinds of embodiments.
Embodiment 1
As shown in Figure 1-2, comprise the steps:
Step one: metal inner lining 1 is made up of spherical shell 11, pressure inlet 12 and boss 13, pressure inlet and boss 13 lay respectively at two endvertexs of spherical shell 11 axis.
Step 2: the material preparing metal inner lining 1 is aluminium alloy 6061, constitutes the spherical shell 11 of metal inner lining 1, pressure inlet 12 and boss 13 and adopts the techniques such as punching press, spinning and machining integrally formed, seamless link.
Step 3: the thin film region wall thickness of spherical shell 11 is equal, the connection transitional region thickness at spherical shell 11 with pressure inlet 12 and boss 13 is gradually increased.
Step 4: adhesive layer 2 is uniformly laid according to prespecified thickness the outer surface of spherical shell 11, it is therefore an objective to the spherical shell 11 of metal inner lining 1 and composite layer 3 is firmly connected, and prevents spherical shell 11 from directly contacting with composite layer 3, it is to avoid galvanic corrosion occurs.
Step 5: after high performance carbon fiber, pbo fiber and Kevlar fiber etc. are wound around fiber saturated ring epoxy resins liquid by being prepared by of composite layer 3, adopts multidirectional, multilamellar, planar winding quasi-isotropic design to be wrapped in adhesive layer 2 surface outside spherical shell 11. Epoxy resin liquid is the colloidal liquid mixed according to a certain percentage with firming agent, accelerator and plasticizer etc. by epoxy resin.
Step 6: the gas cylinder after step 5 winding shaping is put into and is heated adhesive layer 2 and composite layer 3 in curing oven solidifying, metal inner lining 1, adhesive layer 2 and composite layer 3 are firmly linked, forms complete spherical composites gas cylinder.
Step 7: the composites gas cylinder after solidifying is carried out hydraulic pressure self-tightening according to the pressure of regulation, makes the spherical composites gas cylinder meeting requirement.
Embodiment 2
As shown in Figure 3-4, comprise the steps:
Step one: metal inner lining 1 is made up of spherical shell 11, pressure inlet 12 and boss 13, pressure inlet and boss 13 lay respectively at two endvertexs of spherical shell 11 axis.
Step 2: the material preparing metal inner lining 1 is the one in titanium alloy T A0, TA1, TA2, TA3, TA4, TA5, TA6, TA7, TA8, TA9, TA10 and TC4, constituting the spherical shell 11 of metal inner lining 1, pressure inlet 12 and boss 13 adopts forging, machining to shape, and carries out assemble welding at the Chi Daochu of metal inner lining 1 spherical shell 11.
Step 3: the thin film region wall thickness of spherical shell 11 is equal, the connection transitional region thickness at spherical shell 11 with pressure inlet 12 and boss 13 is gradually increased.
Step 4: adhesive layer 2 is uniformly laid according to prespecified thickness the outer surface of spherical shell 11, it is therefore an objective to the spherical shell 11 of metal inner lining 1 and composite layer 3 is firmly connected, and prevents spherical shell 11 from directly contacting with composite layer 3, it is to avoid galvanic corrosion occurs.
Step 5: after high performance carbon fiber, pbo fiber and Kevlar fiber etc. are wound around fiber saturated ring epoxy resins liquid by being prepared by of composite layer 3, adopts multidirectional, multilamellar, planar winding quasi-isotropic design to be wrapped in adhesive layer 2 surface outside spherical shell 11. Epoxy resin liquid is the colloidal liquid mixed according to a certain percentage with firming agent, accelerator and plasticizer etc. by epoxy resin.
Step 6: the gas cylinder after step 5 winding shaping is put into and is heated adhesive layer 2 and composite layer 3 in curing oven solidifying, metal inner lining 1, adhesive layer 2 and composite layer 3 are firmly linked, forms complete spherical composites gas cylinder.
Step 7: the composites gas cylinder after solidifying is carried out hydraulic pressure self-tightening according to the pressure of regulation, makes the spherical composites gas cylinder meeting requirement.
The above is only the preferred embodiment of the present invention; it should be pointed out that, for those skilled in the art, under the premise without departing from the principles of the invention; can also making some improvements and modifications, these improvements and modifications also should be regarded as protection scope of the present invention.
Claims (6)
1. the spherical composites gas cylinder of space flight, it is characterized in that, including metal inner lining (1), it is laid in the adhesive layer (2) of metal inner lining (1) outer surface and is wrapped in the composite layer (3) of adhesive layer (2) outer surface, described metal inner lining (1) is by spherical shell (11), pressure inlet (12) and boss (13) composition, pressure inlet (12) and boss (13) lay respectively at two endvertexs of spherical shell (11) axis, the wall thickness designs such as the thin film region employing of spherical shell (11), connection transitional region at spherical shell (11) with pressure inlet (12) and boss (13) adopts progressive thickness Strengthening Design, described adhesive layer (2) is uniformly laid in the outer surface of spherical shell (11), spherical shell (11) and composite layer (3) are firmly connected, and prevent spherical shell (11) from directly contacting with composite layer (3).
2. spherical composites gas cylinder according to claim 1, it is characterized in that, the material of described metal inner lining (1) is aluminium alloy 6061, and described spherical shell (11), pressure inlet (12) and boss (13) are integrally formed.
3. spherical composites gas cylinder according to claim 1, it is characterized in that, the material of described metal inner lining (1) is the one in titanium alloy T A0, TA1, TA2, TA3, TA4, TA5, TA6, TA7, TA8, TA9, TA10 or TC4, described spherical shell (11), pressure inlet (12) and boss (13) adopt forging, machining to shape, assemble welding.
4. spherical composites gas cylinder according to claim 1, it is characterised in that described adhesive layer (2) is by having the adhesive film of stronger adhesion strength and good insulating performance or liquid adhesive coating is cured makes.
5. spherical composites gas cylinder according to claim 1, it is characterised in that described composite layer (3) adopts multidirectional, multilamellar, planar winding quasi-isotropic winding layer design.
6. spherical composites gas cylinder according to claim 1, it is characterized in that, described composite layer (3) is by being wrapped in cured the adhesive layer (2) outside spherical shell (11) upper forming after high-performance carbon fibre, pbo fiber and Kevlar fiber saturated ring epoxy resins liquid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610059330.7A CN105674041A (en) | 2016-01-28 | 2016-01-28 | Spherical composite gas cylinder for spaceflight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610059330.7A CN105674041A (en) | 2016-01-28 | 2016-01-28 | Spherical composite gas cylinder for spaceflight |
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| Publication Number | Publication Date |
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| CN105674041A true CN105674041A (en) | 2016-06-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201610059330.7A Pending CN105674041A (en) | 2016-01-28 | 2016-01-28 | Spherical composite gas cylinder for spaceflight |
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| CN (1) | CN105674041A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107116340A (en) * | 2017-05-18 | 2017-09-01 | 上海空间推进研究所 | Space flight large size, thin walled liner and its manufacture method |
| CN108061241A (en) * | 2017-11-30 | 2018-05-22 | 北京宇航***工程研究所 | A kind of reusable composites gas cylinder and its design method |
| CN108253280A (en) * | 2017-12-22 | 2018-07-06 | 兰州空间技术物理研究所 | A kind of composite material spherical shape gas cylinder for being integrated with installation interface and preparation method thereof |
| CN109707989A (en) * | 2018-11-27 | 2019-05-03 | 航天特种材料及工艺技术研究所 | A kind of composite material spherical shape gas cylinder and preparation method thereof |
| CN113685718A (en) * | 2021-08-27 | 2021-11-23 | 兰州空间技术物理研究所 | Satellite composite gas cylinder end socket and manufacturing method thereof |
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| CN103437913A (en) * | 2013-07-25 | 2013-12-11 | 上海空间推进研究所 | Metal diaphragm storage box made of carbon-fiber composite materials and manufacturing method thereof |
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2016
- 2016-01-28 CN CN201610059330.7A patent/CN105674041A/en active Pending
Patent Citations (3)
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| DE9102936U1 (en) * | 1991-03-12 | 1992-07-09 | Cyron, Theodor, 5060 Bergisch Gladbach | Double-walled pressure vessel |
| JP2014081014A (en) * | 2012-10-15 | 2014-05-08 | Honda Motor Co Ltd | Pressure gas container and vehicle including the same |
| CN103437913A (en) * | 2013-07-25 | 2013-12-11 | 上海空间推进研究所 | Metal diaphragm storage box made of carbon-fiber composite materials and manufacturing method thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107116340A (en) * | 2017-05-18 | 2017-09-01 | 上海空间推进研究所 | Space flight large size, thin walled liner and its manufacture method |
| CN108061241A (en) * | 2017-11-30 | 2018-05-22 | 北京宇航***工程研究所 | A kind of reusable composites gas cylinder and its design method |
| CN108253280A (en) * | 2017-12-22 | 2018-07-06 | 兰州空间技术物理研究所 | A kind of composite material spherical shape gas cylinder for being integrated with installation interface and preparation method thereof |
| CN109707989A (en) * | 2018-11-27 | 2019-05-03 | 航天特种材料及工艺技术研究所 | A kind of composite material spherical shape gas cylinder and preparation method thereof |
| CN113685718A (en) * | 2021-08-27 | 2021-11-23 | 兰州空间技术物理研究所 | Satellite composite gas cylinder end socket and manufacturing method thereof |
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Application publication date: 20160615 |