CN109282139A - A kind of composites gas cylinder and preparation method thereof - Google Patents

A kind of composites gas cylinder and preparation method thereof Download PDF

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Publication number
CN109282139A
CN109282139A CN201710598519.8A CN201710598519A CN109282139A CN 109282139 A CN109282139 A CN 109282139A CN 201710598519 A CN201710598519 A CN 201710598519A CN 109282139 A CN109282139 A CN 109282139A
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Prior art keywords
winding
layer
gas cylinder
buffer layer
metal liner
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CN109282139B (en
Inventor
柯红军
徐铁峰
宋福英
张维军
杨晓勇
王国勇
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Aerospace Research Institute of Materials and Processing Technology
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Aerospace Research Institute of Materials and Processing Technology
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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
    • 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
    • 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
    • F17C2203/0607—Coatings
    • 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
    • F17C2203/0609—Straps, bands or ribbons
    • 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
    • F17C2203/0612—Wall structures
    • F17C2203/0614—Single wall
    • F17C2203/0619—Single wall with two layers
    • 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
    • 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
    • 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
    • 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
    • F17C2203/0673—Polymers
    • 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
    • F17C2209/00—Vessel construction, in particular methods of manufacturing
    • F17C2209/22—Assembling processes
    • F17C2209/225—Spraying
    • 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
    • F17C2221/00—Handled fluid, in particular type of fluid
    • F17C2221/01—Pure fluids
    • F17C2221/014—Nitrogen
    • 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
    • F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
    • F17C2223/03—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the pressure level
    • F17C2223/035—High pressure (>10 bar)

Abstract

The present invention proposes a kind of composites gas cylinder and preparation method thereof, it is made of metal liner and material shell, the material shell is made of buffer layer and winding layer, the buffer layer is thermoplastic polyimide film, the winding layer is the fibre bundle impregnated of polyimide resin, buffer layer is pasted onto metal liner outer surface, and winding layer is wrapped in buffer layer outer layer, and buffer layer and winding layer co-curing obtain material shell.The present invention introduces thermoplastic polyimide buffer layer between metal liner and polyimides winding layer, thermal stress matching in reinforced resin hot setting and cooling procedure between metal liner and composite material, thermoplastic polyimide film and main body thermoset polyimide resin are able to achieve co-curing simultaneously, increase the caking property of metal liner and outer layer of composite material, improves gas cylinder bearing capacity.

Description

A kind of composites gas cylinder and preparation method thereof
Technical field
The present invention relates to a kind of composites gas cylinders and preparation method thereof, and in particular to a kind of high temperature high voltage resistant polyimides Composites gas cylinder and preparation method thereof belongs to technical field of composite materials.
Background technique
With the rapid development of aeronautical and space technology, guided missile and aircraft are just towards high speed, long-range and structure function one The direction of change is developed, and guided missile and vehicle flight speeds are up to Ma3~4, and part even breaches Ma6, and remote high-speed causes Serious Aerodynamic Heating problem, so that body structure is faced with increasingly harsher working environment, hot environment is also limited very The utilization of the more common body structure material of subsonic speed such as aluminium alloys, epoxies composite material, further to adapt to the big load of aircraft Bullet amount and the long range multiple demand of guided missile, body structure need further loss of weight.
High pressure gas cylinder is the container for disposably storing compressed nitrogen, and main function is oil supply during missile flight Case pressurization, is the risk critical component of spacecraft, internal storage has very high energy, and early stage high pressure gas cylinder is mainly metal knot Structure.With the rapid development of aeronautical and space technology, the range requirement of aircraft is more and more remoter, in order to which structure accounting is effectively reduced, Composites gas cylinder gradually substitutes metal cylinder.Composites gas cylinder has evolved into boat due to structure efficiency with higher One of the key building block of empty space structure dynamical system, composites gas cylinder reliability with higher, loaded work piece longevity Life length, Leakage before burst and the gunslinging failure mode without high energy impact events fragment gradually substitute metal material.
High pressure gas cylinder is at present with containing based on the full wound composite gas cylinder of metal inner lining, there are mainly two types of structure types, One is metal inner lining+Filament Wound Composite layer+external protection coating, such Filament Wound Composite layer mainly uses epoxy resin body System, outer layer are coated using heat shield, and epoxy resin winding layer mainly plays carrying, and outer heat shield effect is barrier or reduces heat Source is internally transmitted, and this structure is thicker toward heat shield thickness outward, and weight is larger, and structure efficiency is lower, and heat shield is main Play the role of anti-heat effect, do not carry, while gas cylinder end socket position is Special-Shaped Surface, heat shield cladding process difficulty is larger.Separately A kind of structure type is metal inner lining+interface buffer layer+Filament Wound Composite layer, and interface buffer layer is thermal insulation layer or bonding agent, Wherein Filament Wound Composite layer is mainly epoxy-resin systems, and interface buffer layer mainly uses rubber or epoxy adhesive, epoxy Resin system is not able to satisfy heatproof requirement.
The resin system that high-pressure gas bottle made of composite material uses at present is mainly epoxies, as vehicle flight speeds are more next Faster, internal temperature is higher and higher, it is desirable that the structure efficiency of aircraft component is higher and higher, by flight vehicle aerodynamic profile envelope Limitation, high pressure gas cylinder increasingly require improve structure efficiency, i.e., under same external temperature environment, it is desirable that Filament Wound Composite Layer itself has high temperature resistant, high-mechanic characteristic, while reducing gas cylinder winding layer thickness as far as possible in a limited space, and epoxy Class composite material has been unable to satisfy the demand of high temperature carrying.
Polyimides is one of optimal high-molecular organic material of comprehensive performance, heat resisting temperature reach as high as 600 DEG C with On, long-term use temperature range is at 200~500 DEG C, and composite polyimide material is high temperature resistant general in the world, Gao Cheng at present Carry the material of main part of structure.Being used in composites gas cylinder is the weak think of of a solution current material high temperature bearing capacity Road, but find in the course of the research, since polyimide curing temperature is higher, metal liner is different with Composite Thermal Expansion Cause phenomenon obvious, while its curing process control difficulty is larger, is needed during the reaction by solvent volatilization, amidation, Asia In multiple stages such as amination, crosslinking curing, entire technical process is more complicated, and the technological parameter for needing to control is more.In addition resistance to height Warm polyimide resin can only be suitble to solwution method winding process, and solvent is contained in polyimide resin, be needed after winding to solvent It is removed, and after removing solvent, fiber can be shunk, and fiber buckling occurs after solidification, reduce the burst pressure of gas cylinder, shadow Ring bearing strength.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, a kind of lightweight, simple process, high-temperature and high-presure resistent is provided Composite polyimide material gas cylinder and preparation method thereof.
Technical solution of the invention: a kind of composites gas cylinder is made of metal liner and material shell, institute The material shell stated is made of buffer layer and winding layer, and the buffer layer is thermoplastic polyimide film, described Winding layer is the fibre bundle impregnated of polyimide resin, and buffer layer is pasted onto metal liner outer surface, and winding layer is in buffer layer The sequence alternate winding of outer layer is with H-Z-H-Z- ...-H-Z-H, wherein H is circumferential winding, and Z is spiral winding, buffer layer and winding Layer co-curing obtains material shell.
Circumferential direction winding is core model around itself uniform rotation, and Guide head is moved along the parallel direction of core model stack shell axis, core model Each rotation, the mobile yarn sheet width of Guide head；Spiral winding is core model around own axes uniform rotation, and Guide head is according to spy Constant speed degree is moved back and forth along core model axis direction, and substantial linear is made of the helix of space curve and cylindrical section on end socket； Circumferential direction winding and spiral winding are techniques well known term.
Each circumferential winding layer number is 2~3 times to winding layer number of spiral in the alternating winding process, in every winding Primary removal solvent is carried out at 6~12 layers, is further continued for being wound.
The number of plies that the spiral is wound every time to winding is 1~2 layer.
The present invention wind in winding process except the main function of solvent is that polyimides is wound up as Wet Winding Process by several times Layer has partial solvent, if carried out after the completion of to be wound except solvent, because thickness is larger, solvent content is more, solvent volatilization meeting Cause to wind fiber buckling, while a large amount of solvent volatilizations will lead to the increase of winding layer voidage, influence to carry.One given layer of every winding It carries out removing solvent by several times after number, because solvent content is relatively fewer, solvent is easily removed, while effectivelying prevent fiber buckling, reduces hole Gap rate.
The technique of the removal solvent handles 1~2h in such a way that vacuum removes solvent in 180~240 DEG C of temperature Afterwards, it is cooled to room temperature.Vacuum bag specifically can be used, other vacuum forms can also be used, as long as can guarantee can incite somebody to action in treatment process The solvent discharge that small molecule solvent and imidization in winding layer generate.
Winding tension successively decreases in the winding process, i.e., at every 6~12 layers of winding, winding tension successively decreases initial tension 3%~8%.
Winding tension refers to during the winding process, tensile force suffered by fiber, tension suffered by fiber in winding process The Tension Evenness of fiber between size, the uniformity and each winding layer of each bundle fiber tension, on product properties influence compared with Greatly.
Winding tension has larger impact to gas cylinder bearing capacity, winding initial tension according to the 5%~10% of fibre strength, Tension is too small, and product strength is relatively low, and when liner pressurising deforms larger, and anti-fatigue performance is poor, and bearing capacity is weak, while the small meeting of tension Cause resin content higher, winding thickness is partially thick, overtension, and fiber attrition increases, and leads to fiber portion fractures, influences to hold It carries, simultaneously wound tension increases, and gel content is caused to reduce.Winding tension successively decreases during the winding process, i.e., it is every winding 6~12 layers when Successively decrease the 3%~8% of initial tension.The method that tension gradually successively decreases is in order to avoid there is the outer tight phenomenon of interior pine, if tension Do not successively decrease or decrement is inadequate, the reduction of inner fiber tension can be made, causes fiber relaxation fold, lead to bearing strength and fatigability It can decline.If tension successively decreases too much, it is higher to will lead to outer layer fiber winding layer resin content, while making to generate in product micro- Hole causes mechanical performance to decline.
The technique of other winding processes is techniques well known, and wind band is prepared as techniques well known.
The spiral winding angle carries out calculating determination according to gas cylinder internal diameter and resistance to pressure request, general winding angle using 10~ 25°。
Angle between winding fiber and core model rotation axis is known as winding angle.It is exactly circumferential when winding angle is close to 90 ° Winding, so pressure vessel circumferential direction winding angle is 90 °, the theoretical winding angle of spiral winding is obtained by theoretical calculation, α0= Arcsin (r/R), wherein α0For theoretical winding angle, R is stack shell radius, and r is pole pore radius, and winding angle when reality is wound is in α ∈α0± 1% α0It chooses in range, not slip when guaranteeing winding also meets the requirement of end socket equal strength.
Metal liner of the present invention provides the structure of good airtight reliability for composites gas cylinder, and carrying relies primarily on outer layer Continuous winding layer, since polyimides gas cylinder needs to bear 350 DEG C of high temperature or more, liner material need to have certain heat-resisting etc. Grade can be titanium alloy, stainless steel, heat resisting steel etc., and metal liner thickness is determined according to gas cylinder bearing capacity, generally 0.2mm~ 1.5mm.Liner end enclosure and stack shell can be formed by spinning stretching integral, or stack shell is rotary press modelling, and end socket uses machine Tool machine-shaping, then end socket and stack shell pass through welding fabrication.
The polyimide resin system that the present invention uses does not have special limit for thermoset polyimide resin, to its type System, it is such as sub- using acetylene sealing end, allyl norbornene sealing end or phenylacetylene-capped polyamides as long as heat resistance meets use One or more of polyimide resin etc..
Buffer layer of the present invention uses thermoplastic polyimide film, and main function is enhancing polyimide resin hot setting And the thermal stress matching in cooling procedure between metal liner and composite polyimide material, while thermoplastic polyimide is thin Membrane material and main body thermoset polyimide resin are able to achieve co-curing, increase the bonding of metal liner and outer layer of composite material Property.Buffer layer thickness is generally 0.05~0.5mm, and specific thickness is determined by the thermal expansion coefficient of metal liner diameter and material, By theoretical calculation, suitable thickness is selected, if thickness is larger, outer layer winding fiber cannot be guaranteed fiber under tension It is exceptionally straight, intensity is influenced, if thickness is smaller, the thermal stress matching effect in hot setting and cooling procedure cannot be played very well.
Thermal expansion amount: Δ l=αr* Δ T*l, wherein Δ l is thermal expansion amount, αrFor metal liner thermal expansion coefficient, Δ T is For room temperature to the temperature variation of polyimide resin solidification temperature, l is the initial length (length when room temperature) of metal liner.
Buffer layer thickness d >=Δ the l.
The present invention is not particularly limited thermoplastic polyimide resin type, as long as can function as described above, work Condensation polymer type polyimides is generally used in journey, such as Vespel polyimides, Ultem and Extem polyetherimide, Torlon polyamides The one or more of amine acid imide, UPIMOL polyimides and Aurum polyimides etc..
The kinds of fibers that winding layer of the present invention uses carries pressure according to gas cylinder and temperature resistant grade is selected, can be used High modulus carbon fiber, such as T700 grades, T800 grades, T1000 grades of one or more, can also be used other fibre types, such as high-strength Glass fibre, aramid fiber, quartz fibre, ultra high molecular weight polyethylene fiber, polyphenyl the third oxazole fiber etc..
The present invention is the organic solvent removed in Wet Winding Process fiber except solvent processing craft main function, while polyamides is sub- Polyimide resin response characteristic is to be needed during the reaction by multiple ranks such as solvent volatilization, amidation, imidization, crosslinking curings Section, preceding 3 step be pretreatment stage, mainly reacting to each other between monomer and with a large amount of gas generate, so necessary System is carried out in resin imidization to reduce winding fiber solvent content, while carrying out Asia except solvent and gas exhaust treatment Amination treatment reduces winding layer voidage by vacuum except solvent can be such that the small molecule in imidization excludes in time, improves Gas cylinder bearing strength.
The present invention uses certain thick first to wind on cylinder liner except the process of solvent by several times during the winding process After degree, solvent method is removed using vacuum and removes internal solvent on solvent boiling point temperature, room temperature is cooled to, is further continued for carrying out Winding, until reaching design winding thickness.Its main function are as follows: position of fibers is fixed in time, reduces fiber fold and pine It dissipates, avoids fiber buckling, improve gas cylinder quality uniformity.
The gas cylinder curing mode that the present invention uses is integrally curing, since polyimide resin has part in the curing process Small molecule is released, therefore using vacuumizing heat-pressure curing form, it is necessary to heat curing process can by vacuumizing and When the small molecule that reaction is released is discharged, while pressurizeing to composites gas cylinder, improve compactness and Forming Quality, tool The modes such as autoclave can be used in body.
A kind of preparation method of composites gas cylinder, is realized by following steps:
The first step, the processing of metal liner outer surface；
Blast processing is carried out to metal liner outer surface, and guarantees that outer surface blast is uniform；Metal liner processing is ability Domain well-known technique.
Second step is coated with buffer layer,
In metal liner outer surface brushing polyimide resin solution, thermoplastic polyimide resin film is covered in gold Belong to outer surface of liner, obtains buffer layer；
Metal liner outer surface is handled completely before being coated with buffer layer, degreases and impurity, the process of processing is Techniques well known.
Third step, winding,
A3.1, fiber infiltrate polyimide resin solution, obtain fibre bundle；
For techniques well known.
A3.2, it is wound on the buffer layer of second step using the fibre bundle infiltrated,
The sequence alternate winding of fibre bundle is in buffer layer outer layer with H-Z-H-Z- ...-H-Z-H, wherein H is circumferential winding, Z For spiral winding, 6~12 layers of every winding when, carries out primary removal solvent, and winding tension successively decreases the 3%~8% of initial tension；
4th step, vacuumizes, and pressurized, heated integrally curing obtains composites gas cylinder.
Concrete technology is determined according to polyimide resin solution type.
Following technique specifically can be used, can also be adjusted according to actual production:
The composites gas cylinder that winding is completed is put into high temperature hot pressing tank and is solidified, vacuum degree is -0.090MPa or so, Gu Changing temperature is 240 DEG C~370 DEG C, and pressure point is 350 DEG C or so, and advanced High Temperature Resistant Polyimide Composites gas is obtained after the completion of solidification Bottle.
The present invention compared with prior art the utility model has the advantages that
(1) present invention introduces thermoplastic polyimide buffer layer, enhancing between metal liner and polyimides winding layer Thermal stress matching in resin hot setting and cooling procedure between metal liner and composite material, while thermoplasticity polyamides is sub- Amine film and main body thermoset polyimide resin are able to achieve co-curing, increase the bonding of metal liner and outer layer of composite material Property, improve gas cylinder bearing capacity；
(2) true by taking out at a certain temperature using the process for removing solvent by several times in present invention alternating winding process Sky can effectively remove the small molecule generated in solvent and resin imidization in resin, while by resin imidization temperature It is pre-processed under the conditions of degree, can further promote resin imidization, reduce winding layer voidage, improve gas cylinder bearing strength；
(3) present invention is wound by alternating then by several times except solvent integrally vacuumizes the curing mode of heat-pressure curing, On the one hand the small molecule that reaction is released can be discharged in time by vacuumizing, on the other hand composites gas cylinder is added Pressure improves compactness and Forming Quality.
Specific embodiment
Below with reference to specific example, the present invention is described in detail.
Embodiment 1
After stainless steel metal liner blasting treatment, surface impurity and greasy dirt are removed with alcohol, metal liner is loaded on On wrapping machine, YH-550 polyimide solution is brushed in metal liner outer surface, by the thermoplasticity Vespel polyimides of 0.1mm Film is coated in metal liner outer surface.Then two axis T1000 carbon fibers are taken, YH-550 polyimide solution is got out, will match The polyimide resin solution made pours into steeping vat, is wound, is twined in metal liner using the fibre bundle infiltrated Winding-type arrangement are as follows: 2 layers of 1 layer of circumferential direction-, 2 layers of spiral-, 1 layer of circumferential direction-, 2 layers of spiral-, 1 layer of circumferential direction-, 2 layers of spiral ...-ring To.
A solvent is removed after 9-11 layers of every winding, removes solvent process are as follows: successively use the gas cylinder of winding from inside to outside Perforated film, airfelt cladding, then beat vacuum bag, and 2h is handled in 200 DEG C of temperature baking ovens, and vacuum degree is -0.095MPa, then It is cooled to room temperature, is further continued for being wound.After 9-11 layers of every winding, tension successively decreases the 3% of initial tension (initially to be opened in this example Power is 40N).
Entire winding process three times, finally solidifies in autoclave except solvent, and the composites gas cylinder that winding is completed is put Enter and solidify in high temperature hot pressing tank, vacuum degree is -0.090MPa, and curing cycle is 240 DEG C/2h+370 DEG C/3h, pressure point 350 DEG C, advanced High Temperature Resistant Polyimide Composites gas cylinder is obtained after the completion of solidification.
Fire resistant polyimide gas cylinder is subjected to room temperature hydraulic bursting test and high-temperature pressure-proof test, room temperature burst pressure are 116MPa, 200 DEG C of pressure resistances are 104MPa, and 300 DEG C of pressure resistances are 79MPa, and 400 DEG C of pressure resistances are 52MPa.
Unspecified part of the present invention is known to the skilled person technology.

Claims (10)

1. a kind of composites gas cylinder, is made of metal liner and material shell, it is characterised in that: the composite material Shell is made of buffer layer and winding layer, and the buffer layer is thermoplastic polyimide film, and the winding layer is dipping The fibre bundle of polyimide resin, buffer layer are pasted onto metal liner outer surface, and winding layer is in buffer layer outer layer with H-Z-H- The sequence alternate of Z- ...-H-Z-H is wound, and wherein H is circumferential winding, and Z is spiral winding, and buffer layer and winding layer co-curing obtain Material shell.
2. a kind of composites gas cylinder according to claim 1, it is characterised in that: in the alternating winding process every time Circumferential winding layer number is 2~3 times to winding layer number of spiral, carries out primary removal solvent at 6~12 layers of every winding, is further continued for It is wound.
3. a kind of composites gas cylinder according to claim 1, it is characterised in that: the spiral is wound every time to winding The number of plies be 1~2 layer.
4. a kind of composites gas cylinder according to claim 2, it is characterised in that: the technique of the removal solvent uses Vacuum removes the mode of solvent, after handling 1~2h in 180~240 DEG C of temperature, is cooled to room temperature.
5. a kind of composites gas cylinder according to claim 1, it is characterised in that: winding tension in the winding process Successively decrease, i.e., at every 6~12 layers of winding, winding tension successively decreases the 3%~8% of initial tension.
6. a kind of composites gas cylinder according to claim 1, it is characterised in that: the buffer layer thickness d >=Δ l, Wherein Δ l is thermal expansion amount, and Δ l=αr* Δ T*l, αrFor metal liner thermal expansion coefficient, Δ T is room temperature to polyimides tree The temperature variation of rouge solidification temperature, l are the initial length of metal liner.
7. a kind of preparation method of composites gas cylinder, which is characterized in that realized by following steps:
The first step, the processing of metal liner outer surface；
Second step is coated with buffer layer,
In metal liner outer surface brushing polyimide resin solution, thermoplastic polyimide resin film is covered in metal Gallbladder outer surface, obtains buffer layer；
Third step, winding,
A3.1, fiber infiltrate polyimide resin solution, obtain fibre bundle；
A3.2, it is wound on the buffer layer of second step using the fibre bundle infiltrated,
The sequence alternate winding of fibre bundle is in buffer layer outer layer with H-Z-H-Z- ...-H-Z-H, wherein H is circumferential winding, and Z is spiral shell Rotation winding；
4th step, vacuumizes, and pressurized, heated integrally curing obtains composites gas cylinder.
8. a kind of preparation method of composites gas cylinder according to claim 7, it is characterised in that: in the step A3.2 The winding angle α ∈ α of spiral winding0± 1% α0, and α0=arcsin (r/R), wherein α0For theoretical winding angle, R is stack shell radius, R is pole pore radius.
9. a kind of preparation method of composites gas cylinder according to claim 7, it is characterised in that: in the step A3.2 Primary removal solvent is carried out at 6~12 layers of every winding.
10. a kind of preparation method of composites gas cylinder according to claim 7, it is characterised in that: the step A3.2 Middle winding process is successively decreased using winding tension, i.e., at every 6~12 layers of winding, winding tension successively decreases the 3%~8% of initial tension.
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