CN104760300A - Thin wall cylindrical structure - Google Patents
Thin wall cylindrical structure Download PDFInfo
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- CN104760300A CN104760300A CN201510193906.4A CN201510193906A CN104760300A CN 104760300 A CN104760300 A CN 104760300A CN 201510193906 A CN201510193906 A CN 201510193906A CN 104760300 A CN104760300 A CN 104760300A
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- thin
- machine direction
- fiber
- direction angle
- shaped structure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/205—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration
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- Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a thin wall cylindrical structure, which comprises multiple thin wall single layers with fibers; a spreading method of the fibers in each thin wall single layer is as follows: the track of the fibers is divided into multiple zones along the circumferential direction of a cylinder and the directional angle of the fibers at the boundary of each zone is different with others; meanwhile, the directional angle of each fiber in each zone changes in a linear or curve manner according to the angle of each boundary. According to the thin wall cylindrical structure, by controlling the drawing direction of a fiber bundle, the fiber direction changing continuously along the spatial position can be freely designed in each single layer; the purpose of adjusting the rigidity and the strength in each direction is realized; the entire mechanical performance is improved and the weight for desired structural performance can be minimized.
Description
Technical field
The present invention relates to material and structure-design technique field, particularly relate to a kind of wavy fiber composite material thin wall tubular construction.
Background technology
Due to features such as structure is simple, reasonable stress, material usage are economized, easy processing, thin-wall tube-shaped structure is widely used in engineering and even sphere of life.But weak point is, the easy flexing of thin-walled cylindrical workpiece.From a structural point, the method improving thin-walled cylindrical workpiece Critical Buckling Load has two: one to be increase wall thickness, but increasing wall thickness will inevitably gain in weight, and this is unallowed at aerospace field; Two is adopt stringer structure, can improve its anti-bending strength to a certain extent, but cause complex structure to a certain extent, add the arrangement space of thin cylinder.
The fabric preparation that traditional fiber composite material workpiece adopts parallel straight fiber placement to be formed, this fiber composite material workpiece compresses in bearing plane, shear action time, easily there is buckling failure.
Summary of the invention
In view of this, the object of the invention is to propose a kind of thin-wall tube-shaped structure, to improve the Critical Buckling Load of thin-wall tube-shaped structure.
Based on above-mentioned purpose, thin-wall tube-shaped structure provided by the invention comprises the thin-walled individual layer that some layers are equipped with fiber, in every layer of thin-walled individual layer, the track lay mode of fiber is divided into multiple region along the circumferencial direction of cylinder, arrange different machine direction angles at the boundary in each region, the machine direction angle simultaneously in each region carries out linear change or curvilinear motion according to the angle of described boundary.
As one embodiment of the present of invention, the linear or curvilinear motion mode in described each region is single order straight line, second order parabola, at least one in third degree curve and B-spline curves.
As another embodiment of the present invention, the linear change of machine direction angle in described each region, the equation of locus of its fiber is:
In formula, θ is cylindrical barrel angle changing, T
i, T
i+1be respectively the machine direction angle at each zone boundary place of thin-walled individual layer, n is the areal divided along the circumferencial direction of cylinder.
As a preferred embodiment of the present invention, the machine direction angle in described each region becomes curvilinear motion, and the equation of locus of its fiber is:
Or
In formula, θ is cylindrical barrel angle changing, T
i, T
i+1be respectively the machine direction angle at each zone boundary place of thin-walled individual layer, n is the areal divided along the circumferencial direction of cylinder.
As a preferred embodiment of the present invention, the circumferencial direction equivalent along cylinder is divided into multiple region.
As one embodiment of the present of invention, in described every layer of thin-walled individual layer, the track lay mode of fiber is divided into 6 ~ 10 regions along cylindrical barrel direction, arranges different machine direction angle T at the boundary in each region
1, T
2, T
3, T
4... .., the machine direction angle of odd indexed is 0 ~ 45 °, and the machine direction angle of even number sequence number is 45 ~ 90 °.
As a preferred embodiment of the present invention, in the machine direction angle of described odd indexed, the difference of the machine direction angle of adjacent sequence number is 5 ~ 15 °.
As a preferred embodiment of the present invention, in the machine direction angle of described even number sequence number, the difference of the machine direction angle of adjacent sequence number is 0.5 ~ 25 °.
As a preferred embodiment of the present invention, n is 8.
As can be seen from above, thin-wall tube-shaped structure provided by the invention is by controlling the lead of fibre bundle, can freely design in each individual layer with locus continually varying fiber-wall-element model, reach the object adjusting rigidity and intensity in all directions, thus improve overall mechanical property, for required structural behaviour carries out minimum weight, this thin-wall tube-shaped structure is by rational Lay up design, optimize its fiber angles to arrange, anti-flexion capabilities can be made to obtain optimize to the limit, thus realize better light-weight design at engineering field, no matter be that lift structure performance or reduction energy resource consumption aspect can be contributed to some extent.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the fiber path deflection definition of the embodiment of the present invention;
Fig. 2 is the machine direction angle on every layer of 8 zone boundary of the embodiment of the present invention, and these 8 machine direction angles are as the design variable optimized;
Fig. 3 is the schematic diagram arranging wavy fiber along its length of the embodiment of the present invention;
Fig. 4 is the schematic diagram along the circumferential direction arranging wavy fiber of the embodiment of the present invention.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearly understand, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
See Fig. 1, it is the schematic diagram of the fiber path deflection definition of the embodiment of the present invention.Thin-wall tube-shaped structure provided by the invention comprises the thin-walled individual layer that some layers are equipped with fiber, in every layer of thin-walled individual layer, the track lay mode of fiber is divided into multiple region along cylindrical barrel direction, arranges different machine direction angle T (T at the boundary in each region
1, T
2, T
3, T
4... ..), the machine direction angle simultaneously in each region carries out linear change or curvilinear motion according to the angle of described boundary
this thin-wall tube-shaped structure is the composite being equipped with wavy fiber, and its entirety forms composite and the cylindrical structure made with the fiber of certain track for multilayer under suture or adhesive effect.Described fiber can be carbon fiber, glass fibre etc.According to Fig. 1, described machine direction angle T is defined as zone boundary place and the tangent fiber of drum surface cuts angle in the present invention, and θ is defined as drum surface fiber and T everywhere
1the angle along the circumferential direction of place's fiber.
As one embodiment of the present of invention, the linear or curvilinear motion mode in described each region is single order straight line, second order parabola, at least one in third degree curve and B-spline curves.
For example, the linear change of machine direction angle in described each region, the equation of locus of its fiber is:
In formula, θ is cylindrical barrel angle changing, T
i, T
i+1be respectively the machine direction angle at each zone boundary place of thin-walled individual layer, n is the areal divided along cylindrical barrel direction.Preferably, n is the areal divided along the circumferencial direction equivalent of cylinder.
Second order parabola equation of locus:
Parameter declaration is the same.
Third degree curve equation of locus:
Parameter declaration is the same.
In order to ensure the reliability designed, but also the feasibility of manufacture will be guaranteed, need the number of reasonably restricted area border machine direction angle, in each individual layer layer, the track lay mode of fiber can be divided into 8 regions (region 1, region 2 with cylindrical barrel direction ... region 8), the linear change of machine direction angle in each region, the equation of locus of its fiber is:
It should be noted that, because fiber is laid with cylindrical barrel direction, T
9be T
1, as shown in Figure 2.
As an alternative embodiment of the invention, in each individual layer layer, the track lay mode of fiber can be divided into 10 regions with cylindrical barrel direction, also can be divided into 7 regions, or 6 regions etc.
Further, different machine direction angle T is set at the boundary in each region
1, T
2, T
3, T
4... .., odd indexed (T
1, T
3, T
5..) machine direction angle is 0 ~ 45 °, even number sequence number (T
2, T
4, T
6..) machine direction angle is 45 ~ 90 °.
As a preferred embodiment of the present invention, in the machine direction angle of described odd indexed, the difference of the machine direction angle of adjacent sequence number is 5 ~ 15 °.More preferably, in the machine direction angle of described even number sequence number, the difference of the machine direction angle of adjacent sequence number is 0.5 ~ 25 °.
Embodiment 1
In Abaqus software, carry out simulation modeling calculating, be of a size of φ 610 × 810mm, wall thickness of cylinder t=3.2mm, by the wavy fiber [± θ (x)] of 16 layers of balance and symmetry
4slaying forms, and every layer thickness is 0.2mm.Wherein the material parameter of fiber is as following table:
| Project | Numerical value |
| Machine direction Young's modulus E1 | 181Mpa |
| The Young's modulus E2 of fiber transverse direction | 10.27Mpa |
| In-plane Shear Modulus G12 | 7.17Mpa |
| Poisson's ratio v12 | 0.28 |
| Density | 1500kg/m 3 |
Load mode: carry out completely clamped for cylinder two free terminals, is positioned at mid-length end at cylinder outer surface and applies Based on Pure Bending Moment 1000Nm.Carry out in Abaqus software in simulation modeling, being divided into length direction to model meshes is 231 grids, and diametric(al) is 121 grids.In each individual layer layer, the track lay mode of fiber can be divided into 8 regions with cylindrical barrel direction, and the machine direction angle of each zone boundary of individual layer is:
| Deflection | T 1 | T 2 | T 3 | T 4 | T 5 | T 6 | T 7 | T 8 |
| Curve | 27.2° | 54.3° | 17.7° | 57.9° | 26.6° | 78.3° | 36.4° | 78.8° |
The linear change of machine direction angle in each region, the equation of locus of its fiber is:
According to composite individual layer laying sequence design guide:
(1) in order to eliminate unnecessary (with being difficult to analyze) film/bending coupling, the laying order of thin cylinder should be symmetrical.
(2) in order to eliminate stretching/shearing coupling, laying group should be balanced (in thin cylinder, each
laying should have a corresponding same material and thickness
laying).
(3) in order to avoid bent/twisted to be coupled as far as possible,
with
laying should gather together.
As shown in Figures 3 and 4.
By the thin-wall tubular structure that obtains according to above-mentioned paving mode and another group straight fibres [± 45,0 by 16 layers of balance and symmetry
2, ± 45,90
2]
sthe composite material thin wall cylinder that deflection is laid is compared, and result is as follows:
| Fiber arrangement | Straight line | Curve |
| Critical Buckling Load value | 6624N | 7242N |
Known accordingly, the anti-flexion capabilities of thin-wall tubular structure provided by the invention is significantly better than generic linear fiber cylindrical structure.
Embodiment 2
In each individual layer layer, the track lay mode of fiber can be divided into 8 regions with cylindrical barrel direction, and the machine direction angle of each zone boundary of individual layer is:
| Deflection | T 1 | T 2 | T 3 | T 4 | T 5 | T 6 | T 7 | T 8 |
| Curve | 25.8° | 58.6° | 37.9° | 66.2° | 22.4° | 61.6° | 26.3° | 49.2° |
The linear change of machine direction angle in each region, the equation of locus of its fiber is:
Other are with embodiment 1.
By the thin-wall tubular structure that obtains according to above-mentioned paving mode and another group straight fibres [± 45,0 by 16 layers of balance and symmetry
2, ± 45,90
2]
sthe composite material thin wall cylinder that deflection is laid is compared, and result is as follows:
| Fiber arrangement | Straight line | Curve |
| Critical Buckling Load value | 6624N | 7201N |
Known accordingly, the anti-flexion capabilities of thin-wall tubular structure provided by the invention is significantly better than generic linear fiber cylindrical structure.
Embodiment 3
In each individual layer layer, the track lay mode of fiber can be divided into 6 regions with cylindrical barrel direction, and the machine direction angle of each zone boundary of individual layer is:
| Deflection | T 1 | T 2 | T 3 | T 4 | T 5 | T 6 |
| Curve | 26.6° | 59.6° | 17.5° | 59.9° | 32.5° | 77.9° |
The linear change of machine direction angle in each region, the equation of locus of its fiber is:
Other are with embodiment 1.
By the thin-wall tubular structure that obtains according to above-mentioned paving mode and another group straight fibres [± 45,0 by 16 layers of balance and symmetry
2, ± 45,90
2]
sthe composite material thin wall cylinder that deflection is laid is compared, and result is as follows:
| Fiber arrangement | Straight line | Curve |
| Critical Buckling Load value | 6624N | 6855N |
Known accordingly, the anti-flexion capabilities of thin-wall tubular structure provided by the invention is significantly better than generic linear fiber cylindrical structure.
Embodiment 4
In each individual layer layer, the track lay mode of fiber can be divided into 10 regions with cylindrical barrel direction, and the machine direction angle of each zone boundary of individual layer is:
| Deflection | T 1 | T 2 | T 3 | T 4 | T 5 | T 6 | T 7 | T 8 | T 9 | T 10 |
| Curve | 28.1° | 59.1° | 16.0° | 62.2° | 30.6° | 82.6° | 23.5° | 55.9° | 38.0° | 69.2° |
The linear change of machine direction angle in each region, the equation of locus of its fiber is:
Other are with embodiment 1.
By the thin-wall tubular structure that obtains according to above-mentioned paving mode and another group straight fibres [± 45,0 by 16 layers of balance and symmetry
2, ± 45,90
2]
sthe composite material thin wall cylinder that deflection is laid is compared, and result is as follows:
| Fiber arrangement | Straight line | Curve |
| Critical Buckling Load value | 6624N | 6793N |
Known accordingly, the anti-flexion capabilities of thin-wall tubular structure provided by the invention is significantly better than generic linear fiber cylindrical structure.
Embodiment 5
In each individual layer layer, the track lay mode of fiber can be divided into 8 regions with cylindrical barrel direction, and the machine direction angle of each zone boundary of individual layer is:
| Deflection | T 1 | T 2 | T 3 | T 4 | T 5 | T 6 | T 7 | T 8 |
| Curve | 34.1° | 51.4° | 23.3° | 65.1° | 28.1° | 76.9° | 18.1° | 48.0° |
The linear change of machine direction angle in each region, the equation of locus of its fiber is:
Other are with embodiment 1.
By the thin-wall tubular structure that obtains according to above-mentioned paving mode and another group straight fibres [± 45,0 by 16 layers of balance and symmetry
2, ± 45,90
2]
sthe composite material thin wall cylinder that deflection is laid is compared, and result is as follows:
| Fiber arrangement | Straight line | Curve |
| Critical Buckling Load value | 6624N | 7222N |
Known accordingly, the anti-flexion capabilities of thin-wall tubular structure provided by the invention is significantly better than generic linear fiber cylindrical structure.
Embodiment 6
In each individual layer layer, the track lay mode of fiber can be divided into 8 regions with cylindrical barrel direction, and the machine direction angle of each zone boundary of individual layer is:
| Deflection | T 1 | T 2 | T 3 | T 4 | T 5 | T 6 | T 7 | T 8 |
| Curve | 17.6° | 71.9° | 26.6° | 83.8° | 39.6° | 70.2° | 34.8° | 86.5° |
The linear change of machine direction angle in each region, the equation of locus of its fiber is:
Other are with embodiment 1.
By the thin-wall tubular structure that obtains according to above-mentioned paving mode and another group straight fibres [± 45,0 by 16 layers of balance and symmetry
2, ± 45,90
2]
sthe composite material thin wall cylinder that deflection is laid is compared, and result is as follows:
| Fiber arrangement | Straight line | Curve |
| Critical Buckling Load value | 6624N | 7209N |
Known accordingly, the anti-flexion capabilities of thin-wall tubular structure provided by the invention is significantly better than generic linear fiber cylindrical structure.
Advantage of the present invention and effect:
(1) compared with conventional composite cylinder, anti-flexion capabilities significantly promotes;
(2) compared with generic linear fibrous composite cylinder, designability is stronger.
As can be seen here, thin-wall tube-shaped structure provided by the invention is by controlling the lead of fibre bundle, can freely design in each individual layer with locus continually varying fiber-wall-element model, reach the object adjusting rigidity and intensity in all directions, thus improve overall mechanical property, for required structural behaviour carries out minimum weight, this thin-wall tube-shaped structure is by rational Lay up design, optimize its fiber angles to arrange, anti-flexion capabilities can be made to obtain optimize to the limit, thus realize better light-weight design at engineering field, no matter be that lift structure performance or reduction energy resource consumption aspect can be contributed to some extent.
Those of ordinary skill in the field are to be understood that: the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (9)
1. a thin-wall tube-shaped structure, it is characterized in that, comprise the thin-walled individual layer that some layers are equipped with fiber, in every layer of thin-walled individual layer, the track lay mode of fiber is divided into multiple region along the circumferencial direction of cylinder, arrange different machine direction angles at the boundary in each region, the machine direction angle simultaneously in each region carries out linear change or curvilinear motion according to the angle of described boundary.
2. thin-wall tube-shaped structure according to claim 1, is characterized in that, the linear or curvilinear motion mode in described each region is single order straight line, second order parabola, at least one in third degree curve and B-spline curves.
3. thin-wall tube-shaped structure according to claim 2, is characterized in that, the linear change of machine direction angle in described each region, and the equation of locus of its fiber is:
In formula, θ is cylindrical barrel angle changing, T
i, T
i+1be respectively the machine direction angle at each zone boundary place of thin-walled individual layer, n is the areal divided along the circumferencial direction of cylinder.
4. thin-wall tube-shaped structure according to claim 2, is characterized in that, the machine direction angle in described each region becomes curvilinear motion, and the equation of locus of its fiber is:
Or
In formula, θ is cylindrical barrel angle changing, T
i, T
i+1be respectively the machine direction angle at each zone boundary place of thin-walled individual layer, n is the areal divided along the circumferencial direction of cylinder.
5. the thin-wall tube-shaped structure according to claim 3 or 4, is characterized in that, the circumferencial direction equivalent along cylinder is divided into multiple region.
6. thin-wall tube-shaped structure according to claim 1, is characterized in that, in described every layer of thin-walled individual layer, the track lay mode of fiber is divided into 6 ~ 10 regions along cylindrical barrel direction, arranges different machine direction angle T at the boundary in each region
1, T
2, T
3, T
4... .., the machine direction angle of odd indexed is 0 ~ 45 °, and the machine direction angle of even number sequence number is 45 ~ 90 °.
7. thin-wall tube-shaped structure according to claim 6, is characterized in that, in the machine direction angle of described odd indexed, the difference of the machine direction angle of adjacent sequence number is 5 ~ 15 °.
8. thin-wall tube-shaped structure according to claim 6, is characterized in that, in the machine direction angle of described even number sequence number, the difference of the machine direction angle of adjacent sequence number is 0.5 ~ 25 °.
9. thin-wall tube-shaped structure according to claim 1, is characterized in that, n is 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510193906.4A CN104760300B (en) | 2015-04-22 | 2015-04-22 | Thin-wall tube-shaped structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510193906.4A CN104760300B (en) | 2015-04-22 | 2015-04-22 | Thin-wall tube-shaped structure |
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| Publication Number | Publication Date |
|---|---|
| CN104760300A true CN104760300A (en) | 2015-07-08 |
| CN104760300B CN104760300B (en) | 2017-03-01 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113977981A (en) * | 2021-10-26 | 2022-01-28 | 中国电子科技集团公司第三十六研究所 | Thin-wall cylindrical structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102521435A (en) * | 2011-11-29 | 2012-06-27 | 苏州大学 | Laminating manufacture method for symmetric laminated plate |
| CN102555316A (en) * | 2011-12-12 | 2012-07-11 | 中国科学院宁波材料技术与工程研究所 | Fiber fabric with high buckling resistance and method for preparing fiber composite material part with high buckling resistance |
| CN104154405A (en) * | 2014-07-07 | 2014-11-19 | 北京航空航天大学 | Carbon fiber composite thin-walled cylinder structure of imitated bamboo structure |
| CN104175565A (en) * | 2014-08-11 | 2014-12-03 | 杭州健途科技有限公司 | Construction method of fiber grids of spherical surface with any openings |
-
2015
- 2015-04-22 CN CN201510193906.4A patent/CN104760300B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102521435A (en) * | 2011-11-29 | 2012-06-27 | 苏州大学 | Laminating manufacture method for symmetric laminated plate |
| CN102555316A (en) * | 2011-12-12 | 2012-07-11 | 中国科学院宁波材料技术与工程研究所 | Fiber fabric with high buckling resistance and method for preparing fiber composite material part with high buckling resistance |
| CN104154405A (en) * | 2014-07-07 | 2014-11-19 | 北京航空航天大学 | Carbon fiber composite thin-walled cylinder structure of imitated bamboo structure |
| CN104175565A (en) * | 2014-08-11 | 2014-12-03 | 杭州健途科技有限公司 | Construction method of fiber grids of spherical surface with any openings |
Non-Patent Citations (2)
| Title |
|---|
| 戴维蓉等: "基于自由曲面构件的纤维变刚度", 《固体火箭技术》 * |
| 牛雪娟等: "变刚度纤维曲线铺放复合材料层合板的", 《计算材料力学》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113977981A (en) * | 2021-10-26 | 2022-01-28 | 中国电子科技集团公司第三十六研究所 | Thin-wall cylindrical structure |
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