CN111931302B - Winding tension design method for high-pressure composite material gas cylinder - Google Patents
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- 239000002131 composite material Substances 0.000 title claims abstract description 92
- 238000004804 winding Methods 0.000 title claims abstract description 79
- 238000000034 method Methods 0.000 title claims abstract description 25
- 239000000835 fiber Substances 0.000 claims abstract description 49
- 230000009471 action Effects 0.000 claims abstract description 19
- 239000010410 layer Substances 0.000 claims description 145
- 230000008859 change Effects 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 6
- 230000009467 reduction Effects 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 239000002356 single layer Substances 0.000 claims description 3
- 230000003213 activating effect Effects 0.000 claims description 2
- 230000007423 decrease Effects 0.000 claims description 2
- 238000006073 displacement reaction Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 abstract description 24
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 abstract description 7
- 229910052739 hydrogen Inorganic materials 0.000 abstract description 7
- 239000001257 hydrogen Substances 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/32—Hydrogen storage
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Abstract
A winding tension design method of a high-pressure composite material gas cylinder comprises the following steps of S1, establishing a finite element numerical model of the high-pressure composite material gas cylinder, and analyzing a distribution rule of stress in a fiber direction along a thickness direction under the action of internal pressure; s2, designing initial winding tension of each layer of composite material, setting residual stress of each layer due to the winding tension based on a linear superposition principle according to stress difference between each layer of composite material and the first layer, and compensating for the stress difference between each layer of stress and the first layer; s3, building a finite element analysis model of the composite material gas storage bottle considering winding tension, analyzing the distribution characteristics of stress of each layer under the action of internal pressure, determining the winding stress of each layer if the stress difference of each layer and the stress difference of the first layer are within a set range, and otherwise, entering the step S2. The invention has the advantages that: the fiber strength exertion rate is improved, the fiber use amount is reduced, and the hydrogen storage density of the high-pressure composite material gas storage bottle is improved.
Description
Technical Field
The invention relates to the field of high-pressure composite material gas cylinders, in particular to a winding tension design method of a high-pressure composite material gas cylinder.
Background
The composite material gas cylinder has the advantages of high specific strength, specific modulus, designable performance and the like, and has wider and wider application in the field of high-pressure hydrogen storage. In order to increase the hydrogen storage capacity, composite gas cylinders are being developed towards high pressures. In order to improve the working pressure of the gas cylinder, the number of winding layers of the carbon fiber of the composite gas cylinder is increased. As the number of winding layers increases, the thick-wall effect becomes more and more obvious, and the stress of the fiber gradually decreases from the inner layer to the outer layer. When the inner layer fiber meets the damage condition, the outer layer fiber does not reach the damage condition, the strength is not fully exerted, the winding layer number is increased after the fiber winding layer number reaches a certain number, the bearing capacity of the gas cylinder is not obviously increased, and the gas cylinder becomes a technical bottleneck for restricting the development and the application of the high-pressure composite gas cylinder.
In order to solve the technical problem, foreign companies have proposed a method of modifying the design of the cylinder liner and arranging the circumferential winding layer on the inner side, thereby improving the fiber strength utilization rate, reducing the fiber winding layer number and reducing the weight of the cylinder. However, the method introduces geometric abrupt change points at the joint of the liner sealing head and the cylinder body, increases the stress concentration coefficient, and simultaneously changes the initial laying position of each layer of fiber, thereby increasing the winding difficulty. The winding tension has an important influence on the mechanical property of the composite material gas cylinder, the distribution characteristic of stress along the thickness direction is not changed by a common equal tension design method, and the graphs shown in fig. 2 (a) -2 (c) show that the outer layer fiber strength exerting rate is low.
Disclosure of Invention
In order to achieve the purposes of uniformly distributing fiber stress along the thickness direction under the combined action of internal pressure and winding tension, improving the fiber strength utilization rate and reducing the weight of the high-pressure gas cylinder, the invention provides a winding tension design method of the high-pressure composite gas cylinder. The invention adopts the following technical scheme:
s1, establishing a finite element numerical model of a high-pressure composite material gas storage bottle, and analyzing a distribution rule of stress in a fiber direction along a thickness direction under the action of internal pressure;
S2, designing initial winding tension of each layer of composite material, setting residual stress of each layer due to the winding tension based on a linear superposition principle according to stress difference between each layer of composite material and the first layer, and compensating for the stress difference between each layer of stress and the first layer;
s3, building a finite element analysis model of the composite material gas storage bottle considering winding tension, analyzing the distribution characteristics of stress of each layer under the action of internal pressure, determining the winding stress of each layer if the stress difference of each layer and the stress difference of the first layer are within a set range, and otherwise, entering the step S2.
The invention has the advantages that:
(1) By the design of winding tension, the stress of each layer of the high-pressure composite material gas storage bottle is basically and uniformly distributed under the action of internal pressure, the stress of the inner layer and the stress of the outer layer are consistent, the defects that the stress of the outer layer composite material is small and the stress of the inner layer composite material is large due to the thick-wall effect and the strength of the outer layer fiber cannot be well exerted due to the stress distribution characteristics are overcome, the fiber strength exerting rate is improved, the fiber use amount is reduced, and the hydrogen storage density of the high-pressure composite material gas storage bottle is improved.
(2) According to the invention, by adopting a cooling and cold shrinking method, the winding tension of the composite material is simulated, and by setting different thermal expansion rates of the composite materials of different layers in the model, the applied temperature of the whole model is consistent, so that the problems of heat conduction between layers and model accuracy reduction caused by the heat conduction are avoided.
Drawings
FIG. 1 is a schematic flow chart of the present invention;
Fig. 2 (a) is a schematic diagram showing the distribution of stress in the fiber direction along the thickness direction under the action of internal pressure, fig. 2 (b) is a schematic diagram showing the distribution of stress in the fiber direction along the thickness direction under the action of the internal pressure and the equal tension, and fig. 2 (c) is a schematic diagram showing the distribution of stress in the fiber direction along the thickness direction under the action of the combined action of the internal pressure and the equal tension;
Fig. 3 (a) is a schematic view showing the distribution of the stress in the fiber direction in the thickness direction under the action of the internal pressure, fig. 3 (b) is a schematic view showing the distribution of the stress in the fiber direction in the thickness direction under the action of the tension of the present invention, and fig. 3 (c) is a schematic view showing the distribution of the stress in the fiber direction in the thickness direction under the action of the combined action of the internal pressure and the tension of the present invention;
FIG. 4 is a finite element model in an embodiment;
FIG. 5 is a graph showing the distribution of fiber stress in the thickness direction using the iso-tension and the winding tension design method of the present invention.
Detailed Description
The invention relates to a winding tension design method of a high-pressure composite material gas cylinder, which is characterized in that an embodiment of the invention is a 70MPa/150L composite material hydrogen storage gas cylinder, an inner container is formed by adopting aluminum alloy T6061 for spinning, a composite material layer is obtained by adopting T700 carbon fiber reinforced epoxy resin for winding and is divided into circumferential winding and spiral winding, wherein the circumferential winding angle is 90 degrees, the spiral winding angle is +/-16 degrees, the layering sequence is [90 2/±16]21/902 ], the single-layer thickness of the composite material wound on the cylinder body is 0.31mm, the fiber bandwidth is 15mm, the thickness of the cylinder body of the aluminum alloy inner container is 6mm, the overall length of the gas cylinder is 1950mm, the volume is 150L, and the outer diameter of the inner container is 350mm. As shown in fig. 3 (a) -3 (c).
The embodiment adopts a winding tension design method considering thickness effect to carry out tension design, and as shown in fig. 1, the main steps are as follows:
S1, establishing a finite element numerical model of a high-pressure composite material hydrogen storage cylinder, analyzing a distribution rule of stress in a fiber direction along a thickness direction under the action of internal pressure, and obtaining the influence of a thick-wall effect on the stress of each layer of the composite material; the method comprises the following steps:
S11, establishing a geometric model of the liner according to the geometric shape and thickness information of the liner; for better utilization of the axial symmetry of the model and more convenient arrangement of the composite material layering, 5 ° is taken in the circumferential direction as a study object.
S12, according to the layer thickness and the layer number of the composite material layers. The thickness calculation modes of the cylinder body and the end socket are different, and the thickness of the composite material at the cylinder body can be calculated according to the rule of comparison of the cylinder body, and the thickness of the end socket can be calculated according to the grid theory, so that a geometric model of the composite material layer is established. The geometric model of the composite material layer is built by combining the change rule of the layering angle theta and the thickness t f of each layer along with the radius r on the seal head, and the geometric model is combined with the liner layer; wherein the change rule is as follows:
θ＝arcsin(ro/r)
wherein R o is the radius of a polar hole, R is the radius of a cylinder body, and t fθ is the single-layer thickness of the composite material at the position of the cylinder body.
S13, respectively carrying out grid division on the liner and the composite material, wherein each layer of composite material adopts three-dimensional solid units, and each layer of composite material adopts one unit division in the thickness direction;
S14, respectively setting properties of the liner and the composite material, wherein the property settings comprise the settings of fiber directions and local coordinates of different positions at the sealing head of the composite material layer; the material properties are shown in table 1, table 2 is a composite material property, the angle and the coordinate system of the composite material layer are set, especially for the end socket, the fiber angle and the thickness change along with the radius change, the accuracy is required to be improved, the accuracy of the calculation result is improved, and the model is built as shown in fig. 4;
| E(MPa) | υ | σs(MPa) | σb(MPa) |
| 70000 | 0.33 | 246 | 324 |
TABLE 1
| E11(MPa) | E22(MPa) | G12(MPa) | G13(MPa) | G23(MPa) | υ12 |
| 134220 | 8180 | 4700 | 4700 | 2960 | 0.36 |
TABLE 2
And S15, applying boundary conditions and loads, solving, and extracting the stress of each layer of the composite material layer after the solving is completed, so as to obtain the distribution rule of the stress born by the fiber along the thickness direction, as shown in the table 3.
TABLE 3 Table 3
S2, designing initial winding tension of each layer of composite material, setting residual stress of each layer due to the winding tension based on a linear superposition principle according to stress difference between each layer of composite material and the first layer, and compensating for the stress difference between each layer of stress and the first layer; the method comprises the following steps:
s21, calculating the stress difference between each layer of stress and the first layer according to the stress of each layer of composite material obtained in the step S1; as shown in the table 4 below,
TABLE 4 Table 4
S22, in order to compensate for the stress difference, the residual stress generated by each layer under the action of winding tension must be more than that of the first layer by a corresponding value, so that any number can be added to all numbers in the table due to the residual stress generated by the winding tension of each layer, and the corresponding stress difference can be compensated, but in order to ensure that the fiber cannot flex, the stress of each layer must be maintained to be not less than 0, and in order to reduce the winding tension, the numbers shown in Table 4 are taken as the winding residual stress of each layer;
S23, starting from the outermost layer, according to the residual stress of winding tension born by each layer, considering the relaxation effect of the stress of each layer outside the layer on the layer, and combining the bandwidth and the thickness of each layer of composite material to obtain the initial winding tension until the winding tension of each layer is obtained;
Wherein F k and F i are initial winding tension of the k-th layer and i-th layer composite materials, sigma k is residual stress of the winding tension of the k-th layer composite materials, n is total layer number of the composite materials, i is sum order number, t is thickness of each layer of composite materials 0.31mm, B is fiber bandwidth 15mm during winding, theta k and theta i are fiber winding angles, E A is elastic modulus 70000MPa of the liner materials, E G is elastic modulus 134220MPa of the fiber direction of the composite materials, and t A is wall thickness of the liner cylinder body 6mm. The initial tension of the final hoop wound layer was obtained according to the above formula as shown in table 5.
TABLE 5
S3, building a finite element analysis model of the composite material hydrogen storage cylinder considering winding tension, analyzing the distribution characteristics of stress of each layer under the action of internal pressure, determining the winding stress of each layer if the stress difference of each layer and the stress difference of the first layer are within a set range, and otherwise, entering the step S2. The method comprises the following steps:
S31, on the basis of the finite element model established in the step S1, calculating initial winding stress of each layer according to initial winding tension, layer thickness and bandwidth, calculating fiber direction strain of the layer by combining elastic modulus of the composite material layer, and calculating expansion rate of the layer by adopting a method of reducing the whole model by 1 ℃, wherein the fiber thermal expansion rate of each layer is set as shown in the following formula;
Wherein ε k is the strain caused by the initial winding tension, deltaT is the temperature reduction degree, alpha 11k is the thermal expansion rate of the k-th layer composite material in the fiber direction, the other two directions are set to 0, and the thermal expansion rates of the composite material in the fiber directions of the layers are obtained through calculation and are shown in Table 6.
| Layer number | 1 | 2 | 3 | 4 | 5 | 6 | 7 | 8 | 9 | 10 | 11 |
| α11 | 0.00362 | 0.0032 | 0.0029 | 0.0027 | 0.0025 | 0.0024 | 0.0023 | 0.00229 | 0.00225 | 0.00221 | 0.00219 |
| Layer number | 12 | 13 | 14 | 15 | 16 | 17 | 18 | 19 | 20 | 21 | 22 |
| α11 | 0.00217 | 0.00216 | 0.00215 | 0.00215 | 0.00214 | 0.00214 | 0.00215 | 0.00215 | 0.00215 | 0.00216 | 0.00217 |
TABLE 6
S32, activating a layer of composite material in each load analysis step through a unit death method in finite element software, simultaneously reducing the temperature of the layer by 1 degree, and simulating winding tension until all composite material layers are activated and winding tension is applied;
s33, applying boundary conditions and loads to the whole model, and solving a system equation to obtain the stress of each layer of composite material;
S34, if the stress difference between each layer and the first layer is within a set range, determining the winding stress of each layer, otherwise, entering step S2.
The final result is shown in fig. 5, and after the winding tension designed according to the invention is applied, the stress of each layer of fiber direction is more uniform compared with equal tension winding, which is beneficial to improving the fiber strength exerting rate.
The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of the present invention.
Claims (7)
1. The winding tension design method of the high-pressure composite material gas cylinder is characterized by comprising the following steps of:
s1, establishing a finite element numerical model of a high-pressure composite material gas storage bottle, and analyzing a distribution rule of stress in a fiber direction along a thickness direction under the action of internal pressure;
S2, designing initial winding tension of each layer of composite material, setting residual stress of each layer due to the winding tension based on a linear superposition principle according to stress difference between each layer of composite material and the first layer, and compensating for the stress difference between each layer of stress and the first layer;
s3, establishing a finite element analysis model of the composite material gas storage bottle considering winding tension, analyzing the distribution characteristics of stress of each layer under the action of internal pressure, determining the winding stress of each layer if the stress difference of each layer and the stress difference of the first layer are within a set range, otherwise, entering a step S2; the step S2 is specifically as follows:
s21, calculating the stress difference between each layer of stress and the first layer according to the stress of each layer of composite material obtained in the step S1;
s22, setting residual stress of each layer due to winding tension based on a linear superposition principle, and compensating for stress differences of each layer calculated in the step S21;
S23, starting from the outermost layer, according to the residual stress of winding tension born by each layer, considering the relaxation effect of the stress of each layer outside the layer on the layer, and combining the bandwidth and the thickness of each layer of composite material to obtain the initial winding tension until the winding tension of each layer is obtained;
Wherein F k and F i are initial winding tension of the k-th layer and i-th layer composite materials, sigma k is residual stress of the winding tension of the k-th layer composite materials, n is total layer number of the composite materials, i is sum order number, t is thickness of each layer of composite materials, B is fiber bandwidth during winding, theta k and theta i are fiber winding angles, E A is elastic modulus of the liner materials, E G is elastic modulus of the composite materials in fiber directions, and t A is wall thickness of the liner barrel.
2. The method for designing winding tension of a high-pressure composite gas cylinder according to claim 1, wherein step S1 is specifically as follows:
s11, establishing a geometric model of the liner according to the geometric shape and thickness information of the liner;
S12, according to the layer thickness and the layer number of the composite material layers, a geometric model of the composite material layers is built according to the change rule of the layer angle theta and the thickness t f of each layer along with the radius r on the seal head, and the geometric model is combined with the liner layer;
s13, respectively carrying out grid division on the liner and the composite material, wherein each layer of the composite material adopts a three-dimensional entity unit;
S14, respectively setting properties of the liner and the composite material, wherein the property settings comprise the settings of fiber directions and local coordinates of different positions at the sealing head of the composite material layer;
and S15, applying boundary conditions and loads, solving, and extracting the stress of each layer of the composite material layer after the solving is completed, so as to obtain the distribution rule of the fiber bearing stress along the thickness direction.
3. The method for designing winding tension of a high-pressure composite gas cylinder according to claim 2, wherein 5 ° is taken in the circumferential direction in step S11.
4. The method for designing winding tension of a high-pressure composite gas cylinder according to claim 2, wherein the change rule of step S12 is as follows:
θ＝arcsin(ro/r)
wherein R o is the radius of a polar hole, R is the radius of a cylinder body, and t fθ is the single-layer thickness of the composite material at the position of the cylinder body.
5. The method for designing winding tension of a high-pressure composite gas cylinder according to claim 1, wherein the applying of the boundary condition and load in step S15 comprises the steps of: and (3) applying symmetrical boundary conditions on the section, fixing the axial displacement of one end face of the gas cylinder, and applying internal pressure of 70MPa.
6. The method for designing winding tension of a high-pressure composite gas cylinder according to claim 1, wherein step S3 is specifically as follows:
S31, calculating the fiber direction strain of each layer according to the initial winding tension, the layer thickness and the bandwidth of each layer on the basis of the finite element model established in the step S1, and setting the fiber thermal expansion rate of each layer according to the strain and the temperature reduction, wherein the fiber thermal expansion rate is shown in the following formula;
Wherein epsilon k is the strain generated by the initial winding tension, delta T is the temperature reduction degree ,α11k is the thermal expansion rate of the k-layer composite material in the fiber direction, and the other two directions are set to be 0;
s32, activating a layer of composite material in each load analysis step through a unit death method in finite element software, reducing the temperature of the layer by a set degree, and simulating winding tension until all composite material layers are activated and winding tension is applied;
s33, applying boundary conditions and loads to the whole model, and solving a system equation to obtain the stress of each layer of composite material;
S34, if the stress difference between each layer and the first layer is within a set range, determining the winding stress of each layer, otherwise, entering step S2.
7. The method for designing winding tension for a high pressure composite gas cylinder according to claim 6, wherein the set degree of temperature decrease of the layer in step S32 is 1 degree.
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| CN114248477A (en) * | 2022-01-25 | 2022-03-29 | 南通中集能源装备有限公司 | Method for forming body of plastic lining high-pressure gas cylinder |
| CN115447175B (en) * | 2022-09-13 | 2024-05-24 | 中国计量大学 | Winding tension adjusting method for composite material in gas cylinder |
| CN116100841B (en) * | 2023-01-13 | 2024-01-26 | 江苏集萃复合材料装备研究所有限公司 | Preparation method for high-pressure hydrogen cylinder |
| CN117610385B (en) * | 2024-01-24 | 2024-04-09 | 合肥通用机械研究院有限公司 | Method for designing layering of IV-type hydrogen storage cylinder considering strength and fatigue life |
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