CN107891634A - Composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing metal lining and preparation process thereof - Google Patents
Composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing metal lining and preparation process thereof Download PDFInfo
- Publication number
- CN107891634A CN107891634A CN201711062686.7A CN201711062686A CN107891634A CN 107891634 A CN107891634 A CN 107891634A CN 201711062686 A CN201711062686 A CN 201711062686A CN 107891634 A CN107891634 A CN 107891634A
- Authority
- CN
- China
- Prior art keywords
- foam strip
- cylindrical shell
- composite
- foam
- strip
- 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
- 239000011229 interlayer Substances 0.000 title claims abstract description 68
- 239000002131 composite material Substances 0.000 title claims abstract description 59
- 239000002184 metal Substances 0.000 title claims abstract description 48
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 48
- 238000002360 preparation method Methods 0.000 title claims abstract description 38
- 239000006260 foam Substances 0.000 claims abstract description 134
- 239000011159 matrix material Substances 0.000 claims abstract description 71
- 239000000835 fiber Substances 0.000 claims abstract description 32
- 238000004804 winding Methods 0.000 claims abstract description 18
- 238000000034 method Methods 0.000 claims abstract description 15
- 210000003205 muscle Anatomy 0.000 claims description 27
- 238000005516 engineering process Methods 0.000 claims description 22
- 239000010410 layer Substances 0.000 claims description 21
- 239000004744 fabric Substances 0.000 claims description 19
- 238000003825 pressing Methods 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 7
- 230000007547 defect Effects 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229920006231 aramid fiber Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 20
- 238000004519 manufacturing process Methods 0.000 description 8
- 238000003860 storage Methods 0.000 description 4
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 2
- 239000000284 extract Substances 0.000 description 2
- 239000002657 fibrous material Substances 0.000 description 2
- 239000002023 wood Substances 0.000 description 2
- 206010054949 Metaplasia Diseases 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000011031 large-scale manufacturing process Methods 0.000 description 1
- 230000015689 metaplastic ossification Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000000178 monomer Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000002760 rocket fuel Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a non-planar shape
- B32B1/08—Tubular products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
- B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
- B32B3/085—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts spaced apart pieces on the surface of a layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
- B32B2262/0261—Polyamide fibres
- B32B2262/0269—Aromatic polyamide fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2266/00—Composition of foam
- B32B2266/02—Organic
- B32B2266/0214—Materials belonging to B32B27/00
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2266/00—Composition of foam
- B32B2266/02—Organic
- B32B2266/0214—Materials belonging to B32B27/00
- B32B2266/0221—Vinyl resin
- B32B2266/0235—Vinyl halide, e.g. PVC, PVDC, PVF, PVDF
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2266/00—Composition of foam
- B32B2266/02—Organic
- B32B2266/0214—Materials belonging to B32B27/00
- B32B2266/0242—Acrylic resin
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/718—Weight, e.g. weight per square meter
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2439/00—Containers; Receptacles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2597/00—Tubular articles, e.g. hoses, pipes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
A composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing a metal lining and a preparation process thereof relate to a preparation process of a large-size automatic high-level lightweight pressure-bearing container and pipeline. The invention aims to solve the problems that the existing composite cylindrical shell cannot well realize organic unification of high strength, high rigidity and light weight, the conventional preparation process is complex and a large-scale structure is not easy to produce in batches. The preparation process adopted by the invention is as follows: the method comprises the following steps: winding a preset fiber wire on the metal lining in a winding machine to form an inner skin; step two: laying a dot matrix sandwich containing foam strips and corrugated ribs; step three: winding preset fiber yarns along the outer wall of the lattice sandwich to form an outer skin; step four: and (3) placing the structure in a curing furnace for curing to obtain the composite material lattice interlayer double-skin cylindrical shell structure containing the metal lining. The invention is suitable for a composite material lattice interlayer double-skin cylindrical shell structure containing a metal lining and a preparation process thereof.
Description
Technical field
The present invention relates to the preparation technology of a kind of high lightweight pressure resistant vessel of large scale automatization level or pipeline, tool
Body is a kind of preparation technology for the double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure.
Background technology
At present, petroleum chemical industry pressure vessel develops towards high parameter direction, and this is wanted to the strength of materials and rigidity
More and more higher is sought, and aerospace field proposes the requirement of high-strength high just light weight and ne-leakage to rocket fuel storage tank.This is specially
Niche establishes the double covering cylindrical shell structures of composite dot-matrix interlayer and its preparation technology of all-metal liner in the demand.Its
Advantage is：In configuration aspects：1. metal inner lining, can select the higher metal of corrosion resistance, medium is reduced to its corrosivity,
Fine and close metal inner lining can effectively prevent media leaks simultaneously；2. using fibrous material high specific strength, specific modulus and respectively to
The characteristics of different in nature, meets the intensity requirement of pressure vessel；3. composite material sandwich structure, there is provided enough rigidity, realize lightweight
And the requirement of high rigidity.In terms of preparation technology：1. that realizes large scale, high accuracy and high stability contains metal lining composite material
Sandwich preparation technology；2. automated production can be realized.Based on These characteristics, this class formation can be applied to the large-scale storage of petrochemical industry
The field such as tank, reaction tower, reactor and all kinds of aircraft fuel storage tanks and transport storage tank.
Composite Cylindrical Shell structure designs to meet engineering structure lightness and multifunction requirement
A kind of new structure.At present, the preparation on some Composite Cylindrical Shells, people only focus on the axial compression resistance energy of shell structure
Power, therefore, often ignore in actual fabrication process shell structure radial rigidity and fibrous material to housing ring pretension
Influence, i.e., these structures are not suitable for bearing device field.Also, for the preparation technology of composite material dot matrix structure, people
Have been presented for integrated forming technique and secondary forming process.Integrated forming technique can solve dot matrix fuse and composite
The adhesion strength problem of panel, but its preparation process excessively relies on manual operations, is not easy to realize automation；Secondary forming process is easy
Automate in realizing, but be combined with each other between its dot matrix fuse monomer by the way of bonding, because adhesion strength is relatively low so that
The shear strength of composite material dot matrix structure is low.Therefore, when the dot matrix sandwich of internal pressure is born in preparation and has size and song
During the dot matrix sandwich shell structure of rate radius requirement, by conventional preparation technology, the ability of automated production and high parameter is obtained
The performance such as the anti-internal pressure of structure, anti-axle pressure, bending resistance and shear strength also has a certain distance from expected.
The content of the invention
For above problems of the prior art, the invention provides a kind of answering containing metal inner lining for bearing internal pressure
The double covering cylindrical shell structures of condensation material dot matrix interlayer and its preparation technology, can preferably solve existing composite material interlayer cylinder
Shell can not realize the problem of high internal pressure intensity, high rigidity and lightweight organic unity, and preparation technology complexity well, be not easy reality
Now the problem of maximization, mass and automated production, and existing preparation technology is coarse, and preparation process easily produces defect etc.
Problem.
Technical scheme is as follows：
A kind of double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure, it is characterised in that
Including：Thin-wall metal liner (1), inside panel (2), dot matrix interlayer and exterior skin (6), wherein, dot matrix interlayer includes：Specification one is steeped
Foam bar (3), the foam strip of specification two (4) and ripple muscle (5)；Wherein, inside panel (2) and exterior skin (6) use composite；Gold
It is inside panel (2) made of fiber winding to belong to liner (1) outer wall；Between the foam strip of specification one (3) and the foam strip of specification two (4) across
Along inside panel (2 outer walls around one circle, be corrugated reinforced rib (5) between the foam strip of specification one (3) and the foam strip of specification two (4), then
Fixed by exterior skin (6) to meet the rigidity requirement of internal pressure Thin-Wall Cylindrical Shells metal lining composite material cylindrical shell；Ripple is strengthened
Muscle (5) uses composite；Match somebody with somebody between the foam strip of specification one (3) and the foam strip of specification two (4) and ripple muscle (5) for gapless
Close；Exterior skin (6) is that filament is made through wrapping machine winding.
The filament or fiber cloth are carbon fiber, glass fibre or aramid fiber；The foam strip of specification one (3) and specification
The material of two foam strips (4) is PVC foams, PEI foams or PMI foams.
The parameter of the foam strip of specification one (3) and the foam strip of specification two (4) includes obtuse angle, height and upper and lower bottom, specification
The size of one foam strip (3) and the foam strip of specification two (4) meets following formula respectively：
The foam strip (3 of specification one：Obtuse angle θ=90+180/N；Bottom：Upper bottom：
The foam strip (4 of specification two：Obtuse angle θ=90+180/N；Bottom：Upper bottom：
Wherein, T is ripple muscle thickness；H is the height and R of foam strip0For inside panel external diameter.
A kind of preparation technology for the double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure,
It is characterized in that comprise the following steps：
Step 1：Thin-wall metal internal lining pipe (1) is wound into predetermined fibrous layer on wrapping machine, forms inside panel (2)；
Step 2：Dot matrix interlayer is prepared, interlayer mainly passes through alternate row by the foam strip and fiber cloth (5) of two kinds of specifications
Row, and cooperated by five kinds of specific purpose tools and formed along the circle of inside panel (2) ring laying one.
Step 3：The cylindrical shell for completing dot matrix interlayer is wound into default fibrous layer along outer wall, forms exterior skin；
Step 4：Cylindrical shell after winding is sent into curing oven and solidified, that is, the composite wood shots containing metal inner lining are made
The double covering cylindrical shell structures of battle array interlayer.The present invention is applied to a kind of double covering cylinders of the composite dot-matrix interlayer containing metal inner lining
The preparation of shell structure.
The step 2 comprises the following steps：
Dot matrix interlayer is prepared, interlayer is mainly by the foam strip of specification one (3) and the foam strip of specification two (4) and ripple of two kinds of specifications
Line muscle (5) is cooperated by five kinds of specific purpose tools and formed along the circle of inside panel (2) ring laying one by spaced, folder
Detailed process prepared by layer is as follows：
1) process that two kinds of quantity are equal by sawing machine, the foam strip of specification one (3) of the isosceles trapezoid at different upper and lower bottoms and not
Ibid, the foam strip of specification two (4) of the isosceles trapezoid of bottom common N number of, specification one and specification two, N is even number and N≤16；
2) the upper bottom of the foam strip (3) of specification one and the ripple muscle (5) of preimpregnation are passed through into lower platen (8) and top board (7)
Fixed, equidistant arrangement, keeps fiber cloth (5) to be in tiling straight condition, and the distance between foam strip of specification one (3) is two-by-two
L：
3) by top board (7), lower platen (8) and between the foam strip of specification one (3 and preimpregnation ripple muscle (5) it is fixed,
Controlling the foam strip of specification one, (the distance between 3 be L '：
L '=L2+L2 '+2*T
4) it is the sky that L ' is recessed by the ripple muscle (5) presoaked the foam strip (4) of specification two to be placed in into previous step distance
Intracavitary, and it is fixed with lower platen (7) and top board (8), form the rectangular slab with specific length and width；
5) strip pressing plate (9) through the cavity of top board (7) and is compressed into the foam strip of specification one (3), the foam strip of specification two
(4) top board (7) and ripple muscle (5), is taken out, replaces top board (7) to fix the ripple muscle of preimpregnation using strip pressing plate (9)
(5), the foam strip of specification one (3) and the foam strip of specification two (4)；
6) special fixture 10 is circumferentially uniformly installed at the cylindrical shell both ends with inside panel (2) for forming step 1, is made
Distance between fixture can just install the foam strip of specification one (3) and the foam strip of specification two (4) of length-specific, often hold fixture
(10) quantity and the quantity of the foam strip of specification one (3), the foam strip of specification two (4) are all mutually N；
7) cylindrical shell of the both ends equipped with special fixture (10) is horizontally placed to first foam of dot matrix rectangular foam plate of tiling
On bar, keeping one pair of which fixture, (10 are alignd with the end foam bar, and fixture (10) will be pressed from both sides automatically by the gravity of cylindrical shell itself
Tight foam strip and lower platen (8), control cylindrical shell rotate to the rectangular slab other end and control strip pressure simultaneously at a given speed
Plate (9) extracts rectangular slab out with same speed, meets every foam strip by cylindrical shell both ends clamp before all by strip pressure
Plate (9) carries out spacing；
8) Composite Cylindrical Shell of circumferentially fixed dot matrix interlayer is placed in special radial support frame (11), drives hydraulic pressure
Bar carrys out all lower platens of radial support (8) and is secured to, and removes both ends special fixture (10).
The step 3 comprises the following steps：Exterior skin (6) is prepared, exterior skin (6) is that filament is wound by wrapping machine
Obtain, require in winding process between the foam strip of specification one (3), the foam strip of specification two (4) and ripple muscle (5) of dot matrix interlayer not
Produce sliding and loosen to ensure the dimensional accuracy of final structure and prevent the generation of defect, exterior skin (6) prepares specific mistake
Journey is as follows：
1) radial support frame (11) is moved into small segment distance together with lower platen (8) to one end, the composite circle vacateed
The small segment distance in post shell end carries out pre-wound by wrapping machine；
2) speed and wrapping machine axial direction speed of wrap phase for controlling radial support frame (11) to be moved with lower shoe (8) to one end
Together, the composite for making just to have vacateed from lower shoe is covered by fibrous layer, when radial support frame (11) and lower shoe (8) are completely de-
From Composite Cylindrical Shell, wrapping machine is the first layer fiber for completing exterior skin, is further continued for the outer illiteracy that the specific number of plies is completed in winding
The preparation of skin (6).
The step 4 comprises the following steps：The structure for having twined exterior skin (6) is placed in curing oven solidification, that is, one kind is made
Bear the double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining of internal pressure.
The beneficial effects of the invention are as follows：
The present invention can not realize high internal pressure intensity, Gao Gang well to solve existing composite dot-matrix Cylindrical Sandwich Shells
The problem of degree and lightweight organic unity, and preparation technology is complicated and is limited by physical dimension and is not easy asking for mass production
Topic.
First, the present invention forms exterior skin by the way of fiber winding in thin-wall metal liner outer wall, is bearing internal pressure
When meet that the requirement of intensity can realize light-weighted purpose again.
Secondly, the preparation technology of the dot matrix interlayer containing corrugated reinforced rib can realize maximization by special fixture, automatically
The production requirement of change, also, the production process of dot matrix interlayer remains that the relative position of fiber cloth and foam strip is fastened to each other,
Process will not be relaxed so that the dot matrix interlayer precision of preparation is high, and defect is few；Exterior skin by fiber wind be made, dot matrix interlayer and
Exterior skin can provide enough rigidity for total, to meet requirement of the structure in complex work environment；Finally, whole knot
Structure one-step solidification moulding, and make primary solidification by the way of rotation, each layer fiber is uniformly impregnated with resin.
Therefore, a kind of composite dot-matrix containing metal inner lining for bearing internal pressure produced by the preparation technology presss from both sides
The double covering cylindrical shell structure of layer have that the adhesive strength between each layer is high, and final product quality is high, and large-scale production and automatic can be achieved
The mission requirements of metaplasia production.
Brief description of the drawings
Fig. 1 is a kind of double covering cylindrical shell knots of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure of the present invention
Structure schematic diagram；
Fig. 2 (a), Fig. 2 (b) and Fig. 2 (c) be the tiling of dot matrix interlayer be arranged in rectangular slab prepare schematic diagram, wherein, scheme
2 (a) be the foam strip of specification one with preimpregnation fiber cloth tiling arrangement mode schematic diagram, Fig. 2 (b) be specification two foam strip with
Cooperation schematic diagram between the foam strip of specification one and the fiber cloth of preimpregnation, Fig. 2 (c) are the dot matrix interlayer tile rectangle plate prepared
With the cooperation schematic diagram between three kinds of pressing plates；
Fig. 3 (a), Fig. 3 (b) and Fig. 3 (c) be the dot matrix rectangular slab of tiling along cylindrical shell circumferencial direction laying schematic diagram, its
In, Fig. 3 (a) is dot matrix interlayer ring ply sequence schematic diagram, and Fig. 3 (b) is the snap fitting schematic diagram of fixture and interlayer, Fig. 3
(c) it is the structural representation of completing dot matrix interlayer；
Fig. 4 is the dot matrix interlayer partial schematic diagram laid along cylindrical shell circumferential direction；
Fig. 5 (a) and Fig. 5 (b) be fiber be wound exterior skin prepare schematic diagram, wherein, Fig. 5 (a) is to complete folder
Special radial support frame schematic diagram is installed on the cylindrical shell of layer, the radial support frame is by circumferentially evenly distributed N number of electronic
Hydraulic stem forms, and Fig. 5 (b) is the schematic diagram for preparing exterior skin.
Embodiment
Below in conjunction with the accompanying drawings, by embodiment, the present invention will be further described.
Embodiment one.
The double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure of the present invention include：It is thin
Wall cylindrical metal liner, inside panel, dot matrix fuse and outer layer covering composition, wherein, inside panel and exterior skin use composite wood
Material；Needed according to by internal pressure thin-wall metal liner cylinder shell intensity, inside panel is wound by fiber and is made；Dot matrix fuse includes ripple
Line reinforcement and isosceles trapezoid foam strip, corrugated reinforced rib uniformly enclose with foam strip along inside panel outer wall around one, then by outer illiteracy
Skin fixation is to meet the rigidity requirement of internal pressure Thin-Wall Cylindrical Shells metal lining composite material cylindrical shell；Corrugated reinforced rib is using compound
Material；The cavity blind-mate of foam strip and corrugated reinforced rib；Two adjacent foam strips be with two kinds of identical height not
The foam strip in the isosceles trapezoid section ibid gone to the bottom.Exterior skin is that filament is made through wrapping machine winding.
The parameter of foam strip includes obtuse angle, height and upper and lower bottom, and the foam strip size of two kinds of specifications meets following formula：
Specification one (foam strip)：Obtuse angle θ=90+180/N；Bottom：Upper bottom：
Specification two (foam strip)：Obtuse angle θ=90+180/N；Bottom：Upper bottom：
Wherein, T is ripple muscle thickness；H is the height and R of foam strip0For inside panel external diameter.
A kind of as shown in figure 1, composite dot-matrix interlayer containing metal inner lining for bearing internal pressure prepared in the present embodiment
Double covering cylindrical shell structures, including：Thin-wall metal liner 1, inside panel 2, dot matrix interlayer and exterior skin 6, wherein, dot matrix interlayer bag
Include：The foam strip 3 of specification one, the foam strip 4 of specification two and ripple muscle 5；Wherein, inside panel 2 and exterior skin 6 use composite；
The outer wall of metal inner lining 1 is that fiber winding layer is inside panel 2；Corrugated reinforced rib 5 and the foam strip 3,4 of two kinds of adjacent specifications are uniform
Enclose around one along the outer wall of inside panel 2, then fixed by exterior skin 6 to meet that internal pressure Thin-Wall Cylindrical Shells metal lining composite material is justified
The rigidity requirement of post shell；Corrugated reinforced rib 5 uses composite；The cavity blind-mate of foam strip and corrugated reinforced rib；Outside
Covering 6 is that filament is made through wrapping machine winding；
The horizontal ply sequence of dot matrix interlayer fuse such as Fig. 2 (a), Fig. 2 (b) and Fig. 2 (c) are shown, include the bubble of specification one
Foam bar 3, the foam strip 4 of specification two, the fiber cloth (ripple muscle 5) and top board 7, lower platen 8 and strip pressing plate 9 of preimpregnation；Its
In, Fig. 2 (a) is the 3 paired cooperation schematic diagram of foam strip of top board 7, lower platen 8 and specification one；Fig. 2 (b) is the bubble of specification two
Foam bar 4 cooperatively forms the rectangular foam plate schematic diagram of tiling with top board 8 and lower platen 9；Fig. 2 (c) is that strip pressing plate 9 passes through
The cavity of top board side by side, rectangular foam plate is fixed instead of top board 7 using strip pressing plate 9；
Fig. 3 (a), Fig. 3 (b) and Fig. 3 (c) are that the dot matrix rectangular slab of tiling is wound with curvature along cylindrical shell ring
Dot matrix interlayer fuse.Including the symmetrical fixture 10 in cylindrical shell both ends；Wherein, the fixture is mainly made up of clip and spring, Fig. 3
(a) it is dot matrix interlayer ring ply sequence schematic diagram, Fig. 3 (b) is the snap fitting schematic diagram of lower platen 8 of fixture 10 and interlayer,
When fixture is by the radial pressure of foam strip, the fixture is by Automatic-clamping foam strip and lower platen；Fig. 3 (c) is to complete dot matrix folder
The structural representation of layer；
Fig. 4 is ripple muscle and two kinds of foam strips along the circumferentially wound cooperation schematic diagram of cylindrical shell；
Fig. 5 (a) and Fig. 5 (b) are that exterior skin 6 prepares schematic diagram, wherein, Fig. 5 (a) for radial support structure 11 peace
Schematic diagram is filled, Fig. 5 (b) is the preparation method schematic diagram of exterior skin 6.
The filament or fiber cloth of present embodiment are carbon fiber, glass fibre or aramid fiber；Foam strip is PVC, PEI
Or PMI foams.
Embodiment two.
A kind of double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure of the present embodiment
Preparation technology, its preparation technology comprises the following steps：
Step 1：Thin-wall metal internal lining pipe 1 is wound into predetermined fibrous layer on wrapping machine, forms inside panel 2；
Step 2：Prepare dot matrix interlayer, interlayer mainly by the foam strip and fiber cloth 5 of two kinds of specifications by spaced, and
Cooperated by five kinds of specific purpose tools and formed along the circle of the ring of inside panel 2 laying one, detailed process prepared by interlayer is as follows：
1) it is equal by two kinds of quantity of sawing machine processing, the common N number of (specification of isosceles trapezoid foam strip 3,4 at different upper and lower bottoms
One and specification two, N are even number and N≤16)
2) the upper bottom of the foam strip 3 of specification one is fixed with the fiber cloth 5 presoaked by lower platen 8 and top board 7, two
Two equidistant arrangements, fiber cloth 5 is kept to be in tiling straight condition, and the distance between foam strip 3 of specification one is L：
3) by top board 7, lower platen 8 and between the foam strip 3 of specification one and preimpregnation fiber cloth (ripple muscle) 5 it is solid
Fixed, the distance between control foam strip 3 of specification one is L '：
L '=L2+L2 '+2*T
4) foam strip 4 of specification two is placed in previous step in the cavity being recessed for L ' by the fiber cloth 5 presoaked,
And fixed with lower platen 7 and top board 8, form the rectangular slab with specific length and width；
5) strip pressing plate 9 through the cavity of top board 7 and is compressed into foam strip 3,4 and the fiber cloth 5 presoaked, pressed in taking-up
Plate 7, top board 7 is replaced to fix the fiber cloth 5 of preimpregnation and foam strip 3,4 using strip pressing plate 9；
6) special fixture 10 is circumferentially uniformly installed at the cylindrical shell both ends with inside panel 2 for forming step 1, makes folder
Distance between tool can just install the foam strip 3,4 of length-specific, often hold the quantity and the quantity phase of foam strip 3,4 of fixture 10
It is all N；
7) cylindrical shell of the both ends equipped with special fixture 10 is horizontally placed to first foam strip of dot matrix rectangular foam plate of tiling
On, keep one pair of which fixture 10 to be alignd with the end foam bar, fixture 10 is steeped Automatic-clamping by the gravity of cylindrical shell itself
Foam bar and lower platen 8, control cylindrical shell rotate to the rectangular slab other end and control strip pressing plate 9 simultaneously with phase at a given speed
Same speed extracts rectangular slab out, meets that every foam strip is all limited before the clamp of cylindrical shell both ends by strip pressing plate 9
Position；
8) Composite Cylindrical Shell of circumferentially fixed dot matrix interlayer is placed in special radial support frame 11, drives hydraulic stem
Carry out all lower platens 8 of radial support and be secured to, and remove both ends special fixture 10；
Step 3：The cylindrical shell for completing dot matrix interlayer is wound into default fibrous layer along outer wall and forms exterior skin 6, is wrapped over
Require not produce sliding between the foam strip 3,4 of dot matrix interlayer and the fiber cloth (ripple muscle) 5 of preimpregnation in journey and loosen to ensure
The dimensional accuracy of final structure and the generation for preventing defect, the preparation detailed process of exterior skin 6 are as follows：
1) radial support frame 11 is moved into small segment distance, the Composite Cylindrical Shell vacateed together with lower platen 8 to one end
The small segment distance in end carries out pre-wound by wrapping machine；
2) control radial support frame 11 identical with wrapping machine axial direction speed of wrap to the speed that one end is moved with lower shoe 8,
The composite for making just to have vacateed from lower shoe is covered by fibrous layer, when radial support frame 11 completely disengage with lower shoe 8 it is compound
Material cylindrical shell, wrapping machine are the first layer fiber for completing exterior skin, are further continued for the system that the exterior skin 6 of the specific number of plies is completed in winding
It is standby；
Step 4：The structure for having twined exterior skin 6 is placed in curing oven and solidified, that is, be made it is a kind of bear internal pressure contain metal
The double covering cylindrical shell structures of composite dot-matrix interlayer of liner.
It is finally noted that the purpose for publicizing and implementing mode is that help further understands the present invention, but ability
The technical staff in domain is appreciated that：Without departing from the spirit and scope of the invention and the appended claims, it is various replacement and
Modification is all possible.Therefore, the present invention should not be limited to embodiment disclosure of that, the scope of protection of present invention with
The scope that claims define is defined.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, Er Qie
In the case of without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, embodiment all should be regarded as exemplary, and be nonrestrictive, the scope of the present invention is by appended power
Profit requires rather than described above limits, it is intended that all in the implication and scope that obtain with important document of claim by falling
Change is included in the present invention.Any reference in claim should not be considered as to the involved claim of limitation.
Moreover, it will be appreciated that although the present specification is described in terms of embodiments, not each embodiment is only wrapped
Containing an independent technical scheme, this narrating mode of specification is only that those skilled in the art should for clarity
Using specification as an entirety, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
It is appreciated that other embodiment.
Claims (7)
- A kind of 1. double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure, it is characterised in that bag Include：Thin-wall metal liner (1), inside panel (2), dot matrix interlayer and exterior skin (6), wherein, dot matrix interlayer includes：The foam of specification one Bar (3), the foam strip of specification two (4) and ripple muscle (5)；Wherein, inside panel (2) and exterior skin (6) use composite；Metal Liner (1) outer wall is inside panel (2) made of fiber winding；Across edge between the foam strip of specification one (3) and the foam strip of specification two (4) Inside panel (2 outer walls enclose around one, are corrugated reinforced rib (5) between the foam strip of specification one (3) and the foam strip of specification two (4), then by Exterior skin (6) is fixed to meet the rigidity requirement of internal pressure Thin-Wall Cylindrical Shells metal lining composite material cylindrical shell；Corrugated reinforced rib (5) composite is used；It is blind-mate between the foam strip of specification one (3) and the foam strip of specification two (4) and ripple muscle (5)； Exterior skin (6) is that filament is made through wrapping machine winding.
- A kind of 2. double covering cylinders of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure according to claim 1 Shell structure, it is characterised in that：The filament or fiber cloth are carbon fiber, glass fibre or aramid fiber；The foam strip of specification one (3) and the material of the foam strip of specification two (4) is PVC foams, PEI foams or PMI foams.
- A kind of 3. double covering cylinders of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure according to claim 1 Shell structure, it is characterised in that：The parameter of the foam strip of specification one (3) and the foam strip of specification two (4) include obtuse angle, height and The size of upper and lower bottom, the foam strip of specification one (3) and the foam strip of specification two (4) meets following formula respectively：The foam strip (3 of specification one：Obtuse angle θ=90+180/N；Bottom：Upper bottom：The foam strip (4 of specification two：Obtuse angle θ=90+180/N；Bottom：Upper bottom：Wherein, T is ripple muscle thickness；H is the height and R of foam strip0For inside panel external diameter.
- 4. a kind of preparation technology for the double covering cylindrical shell structures of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure, its It is characterized in comprising the following steps：Step 1：Thin-wall metal internal lining pipe (1) is wound into predetermined fibrous layer on wrapping machine, forms inside panel (2)；Step 2：Prepare dot matrix interlayer, interlayer mainly by the foam strip and fiber cloth (5) of two kinds of specifications by spaced, and Cooperated by five kinds of specific purpose tools and formed along the circle of inside panel (2) ring laying one；Step 3：The cylindrical shell for completing dot matrix interlayer is wound into default fibrous layer along outer wall, forms exterior skin；Step 4：Cylindrical shell after winding is sent into curing oven and solidified, that is, the composite dot-matrix folder containing metal inner lining is made The double covering cylindrical shell structures of layer.
- A kind of 5. double covering cylinders of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure according to claim 4 The preparation technology of shell structure, it is characterised in that：The step 2 comprises the following steps：Dot matrix interlayer is prepared, interlayer is mainly by the foam strip of specification one (3) and the foam strip of specification two (4) and ripple muscle of two kinds of specifications (5) by spaced, and cooperated by five kinds of specific purpose tools and formed along the circle of inside panel (2) ring laying one, interlayer system Standby detailed process is as follows：1) it is equal by two kinds of quantity of sawing machine processing, the foam strip of specification one (3) and difference of the isosceles trapezoid at different upper and lower bottoms The foam strip of specification two (4) of the isosceles trapezoid at upper and lower bottom common N number of, specification one and specification two, N is even number and N≤16；It is 2) the upper bottom of the foam strip (3) of specification one and the ripple muscle (5) of preimpregnation is fixed by lower platen (8) and top board (7), Equidistant arrangement two-by-two, fiber cloth (5) is kept to be in tiling straight condition, and the distance between foam strip of specification one (3) is L：3) by top board (7), lower platen (8) and between the foam strip of specification one (3 and preimpregnation ripple muscle (5) it is fixed, control (the distance between 3 be L ' to the foam strip of specification one：L '=L2+L2 '+2*T4) foam strip (4) of specification two is placed in previous step in the cavity being recessed for L ' by the ripple muscle (5) presoaked, And it is fixed with lower platen (7) and top board (8), form the rectangular slab with specific length and width；5) by strip pressing plate (9) through top board (7) cavity and compress the foam strip of specification one (3), the foam strip of specification two (4) and Ripple muscle (5), top board (7) is taken out, replace top board (7) using strip pressing plate (9) to fix the ripple muscle (5) of preimpregnation, rule The foam strip of lattice one (3) and the foam strip of specification two (4)；6) special fixture 10 is circumferentially uniformly installed at the cylindrical shell both ends with inside panel (2) for forming step 1, makes fixture Between distance the foam strip of specification one (3) and the foam strip of specification two (4) of length-specific can be just installed, often hold fixture (10) Quantity and the quantity of the foam strip of specification one (3), the foam strip of specification two (4) are all mutually N；7) cylindrical shell of the both ends equipped with special fixture (10) is horizontally placed on first foam strip of dot matrix rectangular foam plate of tiling, Keeping one pair of which fixture, (10 are alignd with the end foam bar, and fixture (10) is steeped Automatic-clamping by the gravity of cylindrical shell itself Foam bar and lower platen (8), control cylindrical shell rotate to the rectangular slab other end and control strip pressing plate (9) simultaneously at a given speed Rectangular slab is extracted out with same speed, meets every foam strip by cylindrical shell both ends clamp before all by strip pressing plate (9) Carry out spacing；8) Composite Cylindrical Shell of circumferentially fixed dot matrix interlayer is placed in special radial support frame (11), drives hydraulic stem All lower platens of radial support (8) are simultaneously secured to, and remove both ends special fixture (10).
- A kind of 6. double covering cylinders of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure according to claim 4 The preparation technology of shell structure, it is characterised in that：The step 3 comprises the following steps：Exterior skin (6) is prepared, exterior skin (6) is Filament is wound by wrapping machine and obtained, and the foam strip of specification one (3), the foam strip of specification two of dot matrix interlayer are required in winding process (4) sliding is not produced between ripple muscle (5) and is loosened to ensure the dimensional accuracy of final structure and prevent the generation of defect, outside The preparation detailed process of covering (6) is as follows：1) radial support frame (11) is moved into small segment distance, the Composite Cylindrical Shell vacateed together with lower platen (8) to one end The small segment distance in end carries out pre-wound by wrapping machine；2) control radial support frame (11) identical with wrapping machine axial direction speed of wrap to the speed that one end is moved with lower shoe (8), The composite for making just to have vacateed from lower shoe is covered by fibrous layer, when radial support frame (11) and lower shoe (8) completely disengage Composite Cylindrical Shell, wrapping machine are the first layer fiber for completing exterior skin, are further continued for the exterior skin that the specific number of plies is completed in winding (6) preparation.
- A kind of 7. double covering cylinders of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure according to claim 4 The preparation technology of shell structure, it is characterised in that：The step 4 comprises the following steps：The structure for having twined exterior skin (6) is placed in Solidify in curing oven, that is, a kind of double covering cylindrical shell knots of the composite dot-matrix interlayer containing metal inner lining for bearing internal pressure are made Structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711062686.7A CN107891634B (en) | 2017-11-02 | 2017-11-02 | Composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing metal lining and preparation process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711062686.7A CN107891634B (en) | 2017-11-02 | 2017-11-02 | Composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing metal lining and preparation process thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107891634A true CN107891634A (en) | 2018-04-10 |
| CN107891634B CN107891634B (en) | 2022-06-07 |
Family
ID=61802987
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711062686.7A Active CN107891634B (en) | 2017-11-02 | 2017-11-02 | Composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing metal lining and preparation process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107891634B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109127773A (en) * | 2018-07-17 | 2019-01-04 | 西安交通大学 | A kind of bilayer gradient ripple dot matrix metal sandwich cylindrical shell and preparation method thereof |
| CN109130351A (en) * | 2018-07-23 | 2019-01-04 | 南京航空航天大学 | A kind of carbon fiber interlayer cylinder and preparation method thereof |
| CN109631688A (en) * | 2018-11-21 | 2019-04-16 | 中国运载火箭技术研究院 | A kind of X-type composite material rocket interstage section or inter-tank section connection structure |
| CN109795163A (en) * | 2019-01-29 | 2019-05-24 | 南京航空航天大学 | A kind of carbon fiber collapsed corrugations interlayer cylinder |
| CN109948255A (en) * | 2019-03-20 | 2019-06-28 | 北京空间飞行器总体设计部 | Increasing material manufacturing metal skin lattice structure and its design method for storage tank installation |
| CN111539107A (en) * | 2020-04-23 | 2020-08-14 | 北京玻钢院复合材料有限公司 | Quick prediction method for critical axial pressure load of grid reinforced composite material cylindrical shell |
| CN112061405A (en) * | 2020-09-29 | 2020-12-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | High-bearing-capacity dot matrix lightweight connecting rod structure and application thereof |
| CN112171646A (en) * | 2020-10-28 | 2021-01-05 | 西北工业大学深圳研究院 | Flexible spine mechanism and kangaroo-simulated jumping robot |
| CN114459306A (en) * | 2022-01-13 | 2022-05-10 | 北京理工大学 | Corrugated annular flexible composite explosion-proof device |
| CN114905762A (en) * | 2022-05-23 | 2022-08-16 | 中国兵器装备集团西南技术工程研究所 | Winding and 3D printing technology-based composite material light sandwich structure forming method |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE852234A (en) * | 1976-03-09 | 1977-09-08 | Mc Donnell Douglas Corp | TANK OR VESSEL FOR STORAGE OR TRANSPORT OF LIQUID AT VERY LOW TEMPERATURE |
| CN2509126Y (en) * | 2001-10-10 | 2002-09-04 | 中国国际海运集装箱(集团)股份有限公司 | Bottom structure of container |
| CN201803001U (en) * | 2010-02-26 | 2011-04-20 | 黄骅市康华玻璃钢有限公司 | Glass reinforced plastic and metal wire compound pipeline |
| CN102271888A (en) * | 2008-12-09 | 2011-12-07 | 古瑞特（英国）有限公司 | Core for composite laminated article and manufacture thereof |
| CN105443973A (en) * | 2015-11-09 | 2016-03-30 | 大连理工大学 | Fibrous-composite-wound pressure container with thin-walled metal lining and manufacturing process thereof |
| CN105479772A (en) * | 2016-01-20 | 2016-04-13 | 南京工业大学 | Quasi-three-dimensional reinforced composite material lattice sandwich structure and manufacturing method thereof |
| CN106542123A (en) * | 2016-12-09 | 2017-03-29 | 大连理工大学 | Carrier rocket composite tank with cellular sandwich wall and its processing method |
| CN106626536A (en) * | 2017-01-24 | 2017-05-10 | 中国人民解放军理工大学 | Reinforced composite material foam sandwich cylinder and preparation method thereof |
-
2017
- 2017-11-02 CN CN201711062686.7A patent/CN107891634B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE852234A (en) * | 1976-03-09 | 1977-09-08 | Mc Donnell Douglas Corp | TANK OR VESSEL FOR STORAGE OR TRANSPORT OF LIQUID AT VERY LOW TEMPERATURE |
| CN2509126Y (en) * | 2001-10-10 | 2002-09-04 | 中国国际海运集装箱(集团)股份有限公司 | Bottom structure of container |
| CN102271888A (en) * | 2008-12-09 | 2011-12-07 | 古瑞特（英国）有限公司 | Core for composite laminated article and manufacture thereof |
| CN201803001U (en) * | 2010-02-26 | 2011-04-20 | 黄骅市康华玻璃钢有限公司 | Glass reinforced plastic and metal wire compound pipeline |
| CN105443973A (en) * | 2015-11-09 | 2016-03-30 | 大连理工大学 | Fibrous-composite-wound pressure container with thin-walled metal lining and manufacturing process thereof |
| CN105479772A (en) * | 2016-01-20 | 2016-04-13 | 南京工业大学 | Quasi-three-dimensional reinforced composite material lattice sandwich structure and manufacturing method thereof |
| CN106542123A (en) * | 2016-12-09 | 2017-03-29 | 大连理工大学 | Carrier rocket composite tank with cellular sandwich wall and its processing method |
| CN106626536A (en) * | 2017-01-24 | 2017-05-10 | 中国人民解放军理工大学 | Reinforced composite material foam sandwich cylinder and preparation method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 余乐权等: "点阵截面对点阵夹芯圆柱壳性能的影响", 《机械制造》 * |
| 冯丽娜等: "复合材料波纹夹层圆柱壳设计及轴压性能", 《复合材料学报》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109127773A (en) * | 2018-07-17 | 2019-01-04 | 西安交通大学 | A kind of bilayer gradient ripple dot matrix metal sandwich cylindrical shell and preparation method thereof |
| CN109130351A (en) * | 2018-07-23 | 2019-01-04 | 南京航空航天大学 | A kind of carbon fiber interlayer cylinder and preparation method thereof |
| CN109631688B (en) * | 2018-11-21 | 2021-09-07 | 中国运载火箭技术研究院 | X-shaped composite material rocket stage section or box section connecting structure |
| CN109631688A (en) * | 2018-11-21 | 2019-04-16 | 中国运载火箭技术研究院 | A kind of X-type composite material rocket interstage section or inter-tank section connection structure |
| CN109795163A (en) * | 2019-01-29 | 2019-05-24 | 南京航空航天大学 | A kind of carbon fiber collapsed corrugations interlayer cylinder |
| CN109948255B (en) * | 2019-03-20 | 2022-04-22 | 北京空间飞行器总体设计部 | Additive manufacturing metal skin lattice structure for storage tank installation and design method thereof |
| CN109948255A (en) * | 2019-03-20 | 2019-06-28 | 北京空间飞行器总体设计部 | Increasing material manufacturing metal skin lattice structure and its design method for storage tank installation |
| CN111539107A (en) * | 2020-04-23 | 2020-08-14 | 北京玻钢院复合材料有限公司 | Quick prediction method for critical axial pressure load of grid reinforced composite material cylindrical shell |
| CN111539107B (en) * | 2020-04-23 | 2023-05-09 | 北京玻钢院复合材料有限公司 | Rapid prediction method for critical axial pressure load of grid reinforced composite cylindrical shell |
| CN112061405A (en) * | 2020-09-29 | 2020-12-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | High-bearing-capacity dot matrix lightweight connecting rod structure and application thereof |
| CN112171646A (en) * | 2020-10-28 | 2021-01-05 | 西北工业大学深圳研究院 | Flexible spine mechanism and kangaroo-simulated jumping robot |
| CN114459306A (en) * | 2022-01-13 | 2022-05-10 | 北京理工大学 | Corrugated annular flexible composite explosion-proof device |
| CN114905762A (en) * | 2022-05-23 | 2022-08-16 | 中国兵器装备集团西南技术工程研究所 | Winding and 3D printing technology-based composite material light sandwich structure forming method |
| CN114905762B (en) * | 2022-05-23 | 2024-04-30 | 中国兵器装备集团西南技术工程研究所 | Forming method of composite light sandwich structure based on winding and 3D printing technology |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107891634B (en) | 2022-06-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107891634A (en) | Composite material lattice interlayer double-skin cylindrical shell structure bearing internal pressure and containing metal lining and preparation process thereof | |
| US11299312B2 (en) | Method for producing a leak-tight vessel, and a leak-tight vessel | |
| EP2310192B1 (en) | Process and apparatus for molding continuous-fiber composite articles | |
| US7803241B2 (en) | Composite pressure tank and process for its manufacture | |
| CN106542123B (en) | Carrier rocket composite material tank and its processing method with cellular sandwich wall | |
| US20100230417A1 (en) | Vessel for a compressed gas and method for producing the vessel | |
| CN112344199B (en) | Composite pressure vessel with internal load support | |
| CN108058406B (en) | Preparation method of seepage-proof and leakage-proof carrier rocket all-composite material low-temperature liquid oxygen storage tank | |
| EP2828064A1 (en) | Method of manufacturing a compressed gas cylinder | |
| EP2571671B1 (en) | Method for producing a leak-tight vessel, and leak-tight vessel produced by said method | |
| CN106586035B (en) | Carrier rocket low-temperature composite material tank and its processing method with triangular sandwich wall | |
| CN102582091A (en) | Spherical frame of airplane body and manufacturing method thereof | |
| JP5609249B2 (en) | High pressure tank manufacturing method, high pressure tank manufacturing apparatus, and high pressure tank | |
| US7195133B1 (en) | Composite pressure tank and process for its manufacture | |
| EP3075524B1 (en) | Pressure bulkhead and method for producing a pressure bulkhead | |
| CN103994319A (en) | Winding and curing method of thin-wall metal lining fiber completely-wound light high-pressure gas cylinder | |
| US20150128844A1 (en) | Type-4 tank for cng containment | |
| US20220403980A1 (en) | Storage tank for liquid hydrogen | |
| Miller et al. | Selection and validation of a minimum-cost cold water pipe material, configuration, and fabrication method for ocean thermal energy conversion (OTEC) systems | |
| CN114103168A (en) | Die for preparing composite material curved surface honeycomb structural member and preparation method of structural member | |
| JP2021187094A (en) | Manufacturing method of high pressure tank | |
| RU2333412C1 (en) | Pipe or capacity | |
| GB2610667A (en) | Pressure vessel, use and method of manufacture | |
| JPS6168232A (en) | Preparation of curved pipe | |
| CN107866989B (en) | Composite material energy absorption box and manufacturing 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 |