CN108694300A - A kind of method that finite element submodel automatically generates - Google Patents
A kind of method that finite element submodel automatically generates Download PDFInfo
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- CN108694300A CN108694300A CN201810792498.8A CN201810792498A CN108694300A CN 108694300 A CN108694300 A CN 108694300A CN 201810792498 A CN201810792498 A CN 201810792498A CN 108694300 A CN108694300 A CN 108694300A
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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
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
Abstract
The invention discloses a kind of methods that finite element submodel automatically generates, and comprise the steps of:A, the local finite meta-model and submodel network at the position in aircraft model are established;B, in obtaining step A local finite meta-model unit number, four node numbers, and obtain four points coordinate;C, unit number, the node number of obtaining step A neutrons prototype network, and obtain the coordinate of four angle points.The shortcomings that present invention can overcome first two scheme using the method for submodel network of network.Submodel network technology is first to solve the finite element model of coarse grid, obtain the result of calculation on coarse grid, a set of details grid is re-established according to the boundary sizes of coarse grid, the result of calculation of coarse grid is applied to as boundary condition on refined net, refined net is solved, can obtain the higher local practical structures stress of precision.
Description
Technical field
The present invention relates to a kind of model building method, method that specifically a kind of finite element submodel automatically generates.
Background technology
In airplane design, after the completion of the aircraft model solution of aircraft, it is each that aircraft is reflected to a certain extent
The Path of Force Transfer and stress level of a structure, it is indicated that the position being easily destroyed in aircaft configuration, can be structural test and
It improves and beneficial reference is provided.But the solution of finite element is a numerical solution, solves finite element grid in theory and gets over
Carefully, interpolation result is more accurate, and if full machine finite element grid all uses very thin grid, and the performance to computer and calculating
Efficiency propose the test that can not estimate;And it is coarse grid to use full machine finite element grid, the position for comparing care uses fine-structure mesh
Lattice easy to produce lopsided grid in thick and refined net transition region, cause result of calculation undesirable again;For another example certain CONSTRUCTED SPECIFICATION is out
The plate in hole, but aircraft model indicates that the details stress of tapping can not be true with a complete quadrilateral units
It obtains.
The method that tradition establishes submodel is as follows:
1, full machine finite element coarse grid is established, and applies outer load, it is solved and obtains solving result;
2, submodel is established, the coordinate of boundary point and the boundary point of finite element coarse grid are completely corresponding;
3, coarse grid and refined net are subjected to boundary constraint, interpolation manually;
4, submodel is solved, obtains the result of calculation of submodel
The shortcomings that conventional method:
1, conventional method needs to complete by ripe finite element software, cannot be by full machine model and submodel point
Open, then require unit number in submodel and node serial number can not in full machine model unit number and node number repeat,
Otherwise None- identified causes to conflict;
2, when submodel and full machine model are put together, the boundary to submodel manually and full machine model portion are needed
Matching and interpolation boundary displacement are removed in position, can not achieve automation.
Invention content
The purpose of the present invention is to provide a kind of methods that finite element submodel automatically generates, to solve above-mentioned background technology
The problem of middle proposition.
To achieve the above object, the present invention provides the following technical solutions:
A kind of method that finite element submodel automatically generates, comprises the steps of:
A, the local finite meta-model and submodel network at the position in aircraft model are established;
B, in obtaining step A local finite meta-model unit number, four node numbers, and obtain four points coordinate;
C, unit number, the node number of obtaining step A neutrons prototype network, and obtain the coordinate of four angle points;
D, according to the coordinate matching of tetra- nodes of the angular coordinate of submodel network and Fig. 2, submodel network drawn game is obtained
Portion's finite element model is overlapped in the position in space;
E, the displacement of No. 1,2,3,4 nodes in local finite meta-model is respectively applied in submodel network
On 9000230,9000210,9000000,9000020;
F, by 9000020,9000230 lines, linear equation is established, brings node all in details grid into straight line side
Journey filters out the node (i.e. 9000020, other nodes on 9000230 lines) for meeting linear equation, according to linear interpolation
Method calculates the displacement of these nodes, and is applied with;
G, similarly, the modal displacement interpolation on other three sides is come out, and be applied with;
H, the finite element solving input file of submodel network is generated, finite element solving is carried out, obtains solving result.
Further technical solution as the present invention:When network model is tablet, and details submodel network is bent plate
It waits, the nodal method obtained on angle point line is as follows:
1., establish the plane equation of full machine quadrangle flat board unit, obtain the normal vector of plane;
2., the node on traversal details submodel network, obtain its coordinate, and carried out to the unit of full machine quadrangle to it
Projection;
3., the line of each angle point established into linear equation, bring the coordinate after projection into linear equation, satisfaction merely desired to
The point of equation screens, and carries out positional displacement interpolation;
4., interpolation result is applied on the corresponding node of atom model network.
Compared with prior art, the beneficial effects of the invention are as follows:The present invention uses the method for submodel network of network can be with
The shortcomings that overcoming first two scheme.Submodel network technology is first to solve the finite element model of coarse grid, is obtained thick
Result of calculation on grid re-establishes a set of details grid, by the result of calculation of coarse grid according to the boundary sizes of coarse grid
It is applied on refined net as boundary condition, refined net is solved, can obtain the higher local practical structures stress of precision.
Description of the drawings
Fig. 1 is the structural schematic diagram of submodel network.
Fig. 2 is the local finite meta-model diagram at the position in aircraft model.
Fig. 3 is submodel network node displacement constraint schematic diagram.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Please refer to Fig.1-3, a kind of boundary condition method of the acquisition submodel network of high-efficient simple, while to sub- model net
There is no limit for network unit and node serial number, to the worry repeated to node and element number when saving engineer's modeling, thus
Working efficiency is improved, error probability is reduced.
As shown in Figure 1, being submodel network, that is, the detail model of a part, the number of black is submodel in figure
Node number on network boundary, Fig. 2 show the local finite meta-model at the position in aircraft model, 1,2,3,4 point
Not Wei four nodes node serial number.
1, known conditions
1) the full machine finite element position grid node number it is known that can with four node jack per lines of submodel network, four
The coordinate of a node it is known that unit number it is known that known to the displacement of four nodes
2) in detail model each node number and unit number, known to node coordinate.It can be used not in detail model
With material, it is specified that different thickness, can more really and accurately express practical structures.
2, process is realized
1) unit number in Fig. 2, four node numbers are obtained, and obtain the coordinate of four points
2) the unit number node number in Fig. 1 is obtained, and obtains the coordinate of four angle points
3) according to the coordinate matching of tetra- nodes of the angular coordinate of Fig. 1 and Fig. 2, show that Fig. 1 and Fig. 2 are heavy in the position in space
It closes
4) displacement of No. 1,2,3,4 nodes in Fig. 2 is respectively applied to 9000230,9000210 in Fig. 1,
On 9000000,9000020
5) by 9000020,9000230 lines, linear equation is established, brings node all in details grid into straight line side
Journey filters out the node (i.e. 9000020, other nodes on 9000230 lines) for meeting linear equation, according to linear interpolation
Method calculates the displacement of these nodes, and is applied with
6) similarly, the modal displacement interpolation on other three sides is come out, and is applied with
7) the finite element solving input file for generating submodel network, carries out finite element solving, obtains solving result.
The present invention operation principle be:1) linear interpolation
Known 9,000,020 three direction displacements be (dx0, dy0, dz0), coordinate be (x0, y0, z0), the three of 9000230
The displacement in a direction is (dx1.dy1, dz1), and coordinate is (x1, y1, z1), if certain node is in 9000020 and 9000230 line
On, the coordinate of the node is (x, y, z), asks its displacement dx, dy, dz.Specific formula is as follows:
2) when it is bent plate that full machine grid, which is tablet details submodel network, the node side on angle point line is obtained
Method
A) plane equation for establishing full machine quadrangle flat board unit, obtains the normal vector of plane;
B) node on details submodel network is traversed, obtains its coordinate, and carried out to the unit of full machine quadrangle to it
Projection;
C) line of each angle point is established into linear equation, brings the coordinate after projection into linear equation, satisfaction is merely desired to
The point of equation screens, and carries out positional displacement interpolation;
D) interpolation result is applied on the corresponding node of atom model network.
Representation of the displacement exerted in finite element solving file is as shown in Figure 3.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, 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, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Profit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent requirements of the claims
Variation is included within the present invention.Any reference signs in the claims should not be construed as limiting the involved claims.
In addition, it should be understood that although this specification is described in terms of embodiments, but not each embodiment is only wrapped
Containing an independent technical solution, this description of the specification is merely for the sake of clarity, and those skilled in the art should
It considers the specification as a whole, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
The other embodiment being appreciated that.
Claims (2)
1. a kind of method of finite element submodel Auto--Generating Mesh, which is characterized in that comprise the steps of:
A, the local finite meta-model and submodel grid at the position in aircraft model are established;
B, in obtaining step A local finite meta-model unit number, four node numbers, and obtain four points coordinate;
C, unit number, the node number of obtaining step A neutrons model meshes, and obtain the coordinate of four angle points;
D, according to the coordinate matching of tetra- nodes of the angular coordinate of submodel grid and Fig. 2, show that submodel grid and part have
Meta-model is limited to overlap in the position in space;
E, the displacement of No. 1,2,3,4 nodes in local finite meta-model is respectively applied to 9000230 in submodel grid,
On 9000210,9000000,9000020;
F, by 9000020,9000230 lines, linear equation is established, brings node all in details grid into linear equation,
The node (i.e. 9000020, other nodes on 9000230 lines) for meeting linear equation is filtered out, according to the side of linear interpolation
Method calculates the displacement of these nodes, and is applied with;
G, similarly, the modal displacement interpolation on other three sides is come out, and be applied with;
H, the finite element solving input file of submodel is generated, finite element solving is carried out, obtains solving result.
2. a kind of method of finite element submodel Auto--Generating Mesh according to claim 1, which is characterized in that work as network
Model is tablet, and when details submodel grid is bent plate, the nodal method obtained on angle point line is as follows:
1., establish the plane equation of full machine quadrangle flat board unit, obtain the normal vector of plane;
2., traversal details submodel grid on node, obtain its coordinate, and thrown to the unit of full machine quadrangle it
Shadow;
3., the line of each angle point established into linear equation, bring the coordinate after projection into linear equation, satisfaction merely desired into equation
Point screen, and carry out positional displacement interpolation;
4., interpolation result is applied on the corresponding node of atom model grid.
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| CN201810792498.8A CN108694300A (en) | 2018-07-18 | 2018-07-18 | A kind of method that finite element submodel automatically generates |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111177848A (en) * | 2019-12-26 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for acquiring strain theoretical value based on finite element model |
| CN112149213A (en) * | 2020-09-23 | 2020-12-29 | 中广核工程有限公司 | Method, device and equipment for transmitting finite element model grid data of nuclear island structure |
-
2018
- 2018-07-18 CN CN201810792498.8A patent/CN108694300A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111177848A (en) * | 2019-12-26 | 2020-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for acquiring strain theoretical value based on finite element model |
| CN111177848B (en) * | 2019-12-26 | 2023-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for acquiring strain theoretical value based on finite element model |
| CN112149213A (en) * | 2020-09-23 | 2020-12-29 | 中广核工程有限公司 | Method, device and equipment for transmitting finite element model grid data of nuclear island structure |
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Application publication date: 20181023 |