CN112434381A - Rigidity equivalent method of grid reinforced structure of heavy carrier rocket in scaling model - Google Patents
Rigidity equivalent method of grid reinforced structure of heavy carrier rocket in scaling model Download PDFInfo
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- CN112434381A CN112434381A CN202011487816.3A CN202011487816A CN112434381A CN 112434381 A CN112434381 A CN 112434381A CN 202011487816 A CN202011487816 A CN 202011487816A CN 112434381 A CN112434381 A CN 112434381A
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000002131 composite material Substances 0.000 claims abstract description 33
- 239000000463 material Substances 0.000 claims abstract description 15
- 239000004744 fabric Substances 0.000 claims description 24
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- 239000003365 glass fiber Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims 1
- 238000002474 experimental method Methods 0.000 abstract description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000012545 processing Methods 0.000 abstract description 3
- 238000013461 design Methods 0.000 abstract description 2
- 238000005452 bending Methods 0.000 description 5
- 230000002787 reinforcement Effects 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/26—Composites
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
A rigidity equivalent method of a grid reinforced structure of a heavy carrier rocket in a scaling model belongs to the field of design and manufacture of ground vibration experiment scaling models. The rigidity equivalent method analyzes a grid structure formed by ribs to obtain the properties of an orthotropic material of the grid structure; designing a composite material laminated plate for an equivalent grid reinforced structure, using an orthotropic paving layer to perform equivalent rib strips according to the in-plane rigidity, and using an isotropic paving layer to perform equivalent skin according to the in-plane rigidity; carrying out scaling on the composite laminated plate according to a similar criterion; and equivalently replacing the composite laminated plate after scaling with the original grid reinforced structure to produce the rocket overall scaling model. The rigidity equivalent method solves the problem that the grid reinforced structure of the heavy carrier rocket is too thin and difficult to produce after direct scaling; the processing difficulty and the production cost of the scaled model are reduced; and the overall frequency of the heavy carrier rocket scaling model is similar to that of the original model.
Description
Technical Field
The invention relates to a rigidity equivalent method of a grid reinforced structure of a heavy carrier rocket in a scaling model, and belongs to the field of design and manufacture of scaling models of ground vibration experiments.
Background
With the continuous development of aerospace technology in China and the continuous improvement of the requirement of aerospace missions in the future, the development of heavy carrier rockets is indispensable. The large whole rocket size of the heavy carrier rocket brings difficulty to the ground vibration experiment of the structural dynamics model of the heavy carrier rocket. The existing vibration tower is difficult to meet the experiment requirement, and if a full arrow vibration experiment is carried out, a huge vibration experiment tower capable of accommodating arrow bodies needs to be newly built, so that huge cost is undoubtedly generated. Therefore, a scaling model experiment is carried out under the existing conditions, and the method becomes an important means for obtaining the vibration characteristics of the whole rocket of the heavy rocket instead of an actual measurement experiment.
The grid reinforced structure is a light high-strength structure with excellent mechanical properties, has good specific strength and specific stiffness and anti-buckling capacity, greatly improves the structural efficiency, reduces the mass and increases the effective load. However, the heavy-duty launch vehicle having such a structure has difficulties in designing and manufacturing a scaled model thereof. That is, if the grid is scaled exactly to the whole, the grid becomes very small and it is difficult to perform the physical processing.
Disclosure of Invention
In order to overcome the problems in the prior art, the invention provides a rigidity equivalent method of a grid reinforced structure of a heavy carrier rocket in a scaling model, and the rigidity equivalent method is used for reducing the manufacturing difficulty of the scaling model on the premise of meeting the requirement that the overall frequency of the scaling model is similar to that of an original model.
The technical scheme adopted by the invention is as follows: a rigidity equivalent method of a grid reinforced structure of a heavy-duty carrier rocket in a scaling model comprises the following steps:
s1: analyzing the grid structure formed by the ribs to obtain the properties of the orthotropic material;
s2: designing a composite material laminated plate for an equivalent grid reinforced structure, wherein orthogonal anisotropic ply is used for equivalent ribs according to the in-plane rigidity, and isotropic ply is used for equivalent skin according to the in-plane rigidity;
s3: scaling the composite laminated plate obtained in the step S2 according to a similar criterion;
s4: and equivalently replacing the original grid reinforced structure with the scaled composite laminated plate for producing the rocket overall scaling model.
The orthotropic layer is formed by laying composite material cloth in a layer angle of 0 degree in a stacking mode, and the isotropic layer is formed by alternately laying the composite material cloth in the layer angle of 0 degree and 45 degrees.
The composite laminated board is paved by single material of carbon fiber cloth and glass fiber cloth or by mixed paving of the carbon fiber cloth and the glass fiber cloth and still complies with the in-plane rigidity equivalence criterion
The invention has the beneficial effects that: the rigidity equivalent method of the grid reinforced structure of the heavy carrier rocket in a scaling model analyzes the grid structure formed by ribs to obtain the properties of the orthotropic material of the grid reinforced structure; designing a composite material laminated plate for an equivalent grid reinforced structure, wherein orthogonal anisotropic ply is used for equivalent ribs according to the in-plane rigidity, and isotropic ply is used for equivalent skin according to the in-plane rigidity; scaling the obtained composite material laminated plate according to a similar rule; and equivalently replacing the original grid reinforced structure with the scaled composite laminated plate for producing the rocket overall scaling model. The rigidity equivalent method solves the problem that the heavy carrier rocket grid reinforced structure is too thin and difficult to produce after strict direct scaling is carried out on the structure; the processing difficulty and the production cost of the scaled model are reduced; the method also ensures that the overall frequency of the heavy carrier rocket scaling model designed and manufactured by the method is similar to that of the original model.
Drawings
Fig. 1 is a schematic diagram of a grid reinforcement structure.
Fig. 2 is a flowchart of an equivalent method for rigidity of a grid reinforced structure.
FIG. 3 is a schematic view of an isotropic ply of a composite cloth.
FIG. 4 is a schematic view of an orthotropic lay-up of a composite cloth.
In the figure: 1. skin, 2. ribs.
Detailed Description
The flow of the present invention is further described below with reference to the drawings.
A rigidity equivalent method of a grid reinforced structure of a heavy carrier rocket in a scaling model comprises the following steps:
s1: and analyzing the grid structure formed by the ribs 2 to obtain the properties of the orthotropic material.
The grid reinforcement structure is shown in figure 1 and comprises a skin 1 and ribs 2, wherein the skin mainly bears the load in the plane, and the ribs mainly bear the tensile, compression and bending loads in the rib direction, and the following assumptions are made aiming at the structure and the method: the lateral elastic modulus of the ribs of the grid reinforced structure is far smaller than the axial modulus, so that the influence of the Poisson effect is ignored, and the ribs are supposed to be only loaded in the axial direction; considering that the ribs have no stretch bending coupling effect, and neglecting the stretch bending coupling rigidity; the in-plane stiffness is equivalent as a simplified equivalence principle. To satisfy the overall frequency similarity, the in-plane stiffness (EA) and the bending stiffness (EI) should both be similar. The section size of the rocket body is far larger than the thickness of the grid reinforcing rib, the grid reinforcing rib structure belongs to a thin-wall structure, and the bending rigidity calculation formula is
. Therefore, on the premise that the outer shape is similar, that is, y is similar, the overall frequency is similar when the in-plane stiffness (EA) is similar.
The square grid has a positiveCross-anisotropic material properties, the grid is considered as a hypothetical plate of cross-anisotropic material of equal thickness to the grid. As shown in fig. 1, in the grid reinforcement structure, t is the thickness of the rib, l is the span,
is the modulus of the original grid and the skin material,
the poisson ratio of the material is as follows:
relative density
Equivalent modulus
。（E1，E2Respectively representing moduli in two orthogonal directions)
Equivalent shear modulus
Equivalent poisson's ratio
S2: the composite laminate is designed for an equivalent grid stiffened structure, wherein an orthotropic lay-up is used for an in-plane stiffness equivalent grid 2, and an isotropic lay-up is used for an in-plane stiffness equivalent skin 1.
Firstly, the actual mechanical property parameters of the used composite material cloth are obtained through a tensile experiment. And paving the composite material cloth in different modes according to the actual mechanical property parameters, and equating the grid and the skin according to the in-plane rigidity. The orthotropic layer is formed by laying composite material cloth according to a layer angle of 0 degree in an overlapping mode, and the isotropic layer is formed by alternately laying the composite material cloth according to the layer angle of 0 degree and 45 degrees. The thickness of the composite material layer is calculated according to the material performance parameters obtained by the composite material cloth stretching experiment and the in-plane rigidity of the original grid or skin. Calculation methodThe method comprises the following steps:𝐸𝐺modulus of the actual composite cloth, A0、A1The cross-sectional areas of the materials before and after the equivalent replacement are respectively
. The thickness of the composite material layer can be calculated according to the cross section area of the composite material layer. When the composite material laminated plate is designed, one material of carbon fiber cloth or glass fiber cloth can be adopted, and two materials of the carbon fiber cloth and the glass fiber cloth can be mixed and paved, and the in-plane rigidity equivalence criterion is observed according to the above.
S3: scaling the composite laminated plate obtained in the step S2 according to a similar criterion;
s4: and equivalently replacing the original grid reinforced structure with the scaled composite laminated plate for producing the rocket overall scaling model.
Claims (3)
1. Rigidity equivalent method of grid reinforced structure of heavy carrier rocket in scaling model, wherein the grid reinforced structure comprises
The method comprises a skin (1) and ribs (2), and is characterized in that the rigidity equivalence method comprises the following steps:
s1: analyzing the grid structure formed by the ribs (2) to obtain the properties of the orthotropic material;
s2: designing a composite material laminated plate for an equivalent grid reinforced structure, wherein orthogonal anisotropy ply is used for equivalent ribs (2) according to the in-plane rigidity, and isotropic ply is used for equivalent skin (1) according to the in-plane rigidity;
s3: scaling the composite laminated plate obtained in the step S2 according to a similar criterion;
s4: and equivalently replacing the original grid reinforced structure with the scaled composite laminated plate for producing the rocket overall scaling model.
2. The stiffness equivalence method for a grid-stiffened structure of a heavy launch vehicle in a scaled model according to claim 1, wherein the orthotropic plies are made by laying up composite material cloth at a ply angle of 0 °, and the isotropic plies are made by laying up composite material cloth alternately at ply angles of 0 ° and 45 °.
3. The stiffness equivalence method for grid stiffened structures of heavy launch vehicles in scaled models according to claim 1 wherein said composite laminate is laid from carbon fiber cloth, glass fiber cloth, single material, or a mixture of carbon fiber cloth and glass fiber cloth, and still obeys the in-plane stiffness equivalence criterion.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011487816.3A CN112434381A (en) | 2020-12-16 | 2020-12-16 | Rigidity equivalent method of grid reinforced structure of heavy carrier rocket in scaling model |
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| CN202011487816.3A CN112434381A (en) | 2020-12-16 | 2020-12-16 | Rigidity equivalent method of grid reinforced structure of heavy carrier rocket in scaling model |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023142333A1 (en) * | 2022-01-25 | 2023-08-03 | 大连理工大学 | Correction method and system for thin-walled cylindrical shell model |
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|---|---|---|---|---|
| US20120245862A1 (en) * | 2009-09-14 | 2012-09-27 | Airbus Operations (S.A.S.) | Method for the structural analysis of panels consisting of an isotropic material and stiffened by triangular pockets |
| CN103324782A (en) * | 2013-05-29 | 2013-09-25 | 北京航空航天大学 | Uncertainty optimization method for stability and bearing capability of composite material pressed skin |
| CN103342167A (en) * | 2013-05-18 | 2013-10-09 | 大连理工大学 | Method for making scaled composite material wing model |
| CN107515088A (en) * | 2017-08-04 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of model test part design method of the main box section bending stiffness test of metal wings |
-
2020
- 2020-12-16 CN CN202011487816.3A patent/CN112434381A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120245862A1 (en) * | 2009-09-14 | 2012-09-27 | Airbus Operations (S.A.S.) | Method for the structural analysis of panels consisting of an isotropic material and stiffened by triangular pockets |
| CN103342167A (en) * | 2013-05-18 | 2013-10-09 | 大连理工大学 | Method for making scaled composite material wing model |
| CN103324782A (en) * | 2013-05-29 | 2013-09-25 | 北京航空航天大学 | Uncertainty optimization method for stability and bearing capability of composite material pressed skin |
| CN107515088A (en) * | 2017-08-04 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of model test part design method of the main box section bending stiffness test of metal wings |
Non-Patent Citations (2)
| Title |
|---|
| 郑青;鞠苏;范书群;吴会强;黄春芳;江大志;: "基于失效模式的格栅承力筒结构缩比模型研究", 载人航天, vol. 23, no. 01, 15 February 2017 (2017-02-15), pages 45 - 50 * |
| 马斌捷;盛祖铭;贾亮;王淑范;: "轴外压作用下复合材料网格加筋柱壳蒙皮铺层和筋条角度优化分析", 导弹与航天运载技术, no. 01, 10 February 2009 (2009-02-10), pages 41 - 47 * |
Cited By (1)
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| WO2023142333A1 (en) * | 2022-01-25 | 2023-08-03 | 大连理工大学 | Correction method and system for thin-walled cylindrical shell model |
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