CN105550384B - A kind of post-processing approach of aerodynamics grid Metis auto-partition - Google Patents
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Abstract
The invention belongs to data post processing method technical fields, and in particular to the post-processing approach of aerodynamics grid Metis auto-partition.The following steps are included: step 1: deleting redundancy gridden data；Step 2: the non-directed graph TA of aerodynamics grid A is generated according to following methods；Step 3: creation array E [4] [N]；Step 4: the boundary element of grid A is determined according to non-directed graph TA and following boundary element method of discrimination；... grid the point set G1, G2 ... ..., GP of each subregion of final output；The grid cell set of each subregion is respectively E1, E2 ... ..., EP, inner boundary set B1, B2 ... ..., BP；Complete post-processing.The requirement that this method can satisfy each multiblock technique unit, mesh point renumbers；It can quickly determine the boundary element of each multiblock technique inner boundary.
Description
Technical field
The invention belongs to data post processing method technical fields, and in particular to aerodynamics grid Metis auto-partition
Post-processing approach.
Background technique
CFD (Fluid Mechanics Computation) is obtained by numerical solution fluid on computers and aerodynamics fundamental equation
Take it is various under the conditions of the data that flow and the subject for acting on the power streamed on object, torque, flow image and heat, all kinds of
Important function has been played in the Design of Aerodynamic Configuration of Aeronautics and Astronautics aircraft and optimization.CFD calculates general by the way of iteration
Carry out, reach the condition of convergence need it is thousands of to tens of thousands of secondary iteration, to need to accelerate calculating speed using parallel computing.
With parallel numerical calculation method be constantly progressive and the rapid development of high-performance computer technology, parallel computation
Be more and more obvious in the effect of aerospace field aerodynamics numerical simulation and advantage, relevant item demonstration early period,
It plays an increasingly important role in design and analysis optimization.Such as Boeing is considered as high-performance calculation can speed up numerical value
Simulation process, enhancing analog capability and improvement simulation precision, obtain more efficient aircraft and less wing and flight is surveyed
Examination, keeps lower cost to reach while process is designed and developed in shortening.
METIS is one and divides extensive irregular component, big grid and the software for calculating sparse matrix filling reduction order
Packet.The algorithm of METIS is the algorithm divided based on multilayer graph.The principle of Metis be based on multistage figure division, first to figure into
Row continuous coarsening is split the figure after roughening, on the area maps to tiny figure after being calculated segmentation.Finally again
This division is gradually reverted to the figure that scale constantly increases, and division is finely adjusted with partial approach in reduction process,
Division until obtaining original image.
It includes mesh point, grid cell, inner boundary unit that the completeness of aerodynamics grid data, which is defined as the subregion,
All data.Inner boundary cell data includes two parts, first is that the grid cell data of itself, second is that the grid that it is relied on
Cell data (partition number, itself number).
On the basis of grid cell, after aerodynamics grid is divided using the mpmetis in METIS, NPART output
File only includes the information which subregion grid cell belongs to and which subregion mesh point belongs to.It needs to carry out post-processing realization:
1) each multiblock technique unit renumbers；
2) each partition network lattice point renumbers；
3) determination of each multiblock technique subregion inner boundary unit.
Research both at home and abroad is concentrated on the algorithm of multilayer graph division, how to be divided using METIS to particular problem.But
For the output data after using METIS mpmetis to divide, due to the difference of problem types, currently without open for pneumatic
The post-processing approach of flow field grid dividing.
So needing to develop a kind of post-processing approach for meeting aerodynamics grid Metis auto-partition requirement, to solve
The post-processing problem of aerodynamics grid Metis auto-partition.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of post-processing sides of aerodynamics grid Metis auto-partition
Method meets the completeness demand of each subregion to solve the problems, such as the post-processing of aerodynamics grid Metis auto-partition.
In order to realize the purpose, the technical solution adopted by the present invention is that:
A kind of post-processing approach of aerodynamics grid Metis auto-partition, comprising the following steps:
Setting to the aerodynamics grid A of subregion includes M mesh point, N number of grid cell, number of partitions P；Metis is certainly
The data of subregion belonging to N number of grid cell are generated after dynamic subregion；
If the grid point set of each subregion is G1, G2 ... ..., GP；The grid cell set of each subregion is respectively E1,
E2 ... ..., EP；The inner boundary set of each subregion distinguishes B1, B2 ... ..., BP；
Either element includes three Data Labels (li, zi, ni) in inner boundary set: li indicates grid cell in this subregion
Interior number, zi indicate that the affiliated partition number of adjacent grid cell, ni indicate the number of adjacent grid cell；I=1~P；
Specific step is as follows:
Step 1: deleting the redundancy gridden data in aerodynamics grid A in N number of grid cell according to following methods；
Redundancy mesh point delet method: the mesh point in unit E is set as (e1,e2,…,eK), repeated grid point is found first
And it is set to -1, then delete the gridden data that value is -1, so that redundancy mesh point in grid cell be deleted；Specific algorithm is such as
Shown in lower:
Step 2: the non-directed graph TA of aerodynamics grid A is generated according to following methods；
The low computation complexity generation method of single partition aerodynamics grid non-directed graph: 1) determine that grid cell a is unduplicated
Grid point set G；2) all grid cell set E comprising mesh point in G are obtained；3) a and element in E one by one compared with, obtain a
All neighboring grid cells；Wherein the vertex of non-directed graph is grid cell, and side is the adjacent surface of neighboring grid cells；
Step 3: creation array E [4] [N]；N represents N number of grid cell, and E [1] [:] represents the net in aerodynamics grid A
Whether lattice unit is boundary element, and the value of the item in E [1] [:] is the 0 non-boundary element of expression, and the value of the item in E [1] [:] is 1
It is expressed as boundary element, is defaulted as 0；E [2] [:] indicates which subregion the grid cell of reference numeral belongs to, by Metis subregion
Data determine；E [3] [:] indicates the local number of each multiblock technique unit；E [4] [:] is to reuse part；Symbol ": " table
Show that whole items of corresponding array, E [1] [:] indicate E [1] [1], E [1] [2] ... ..., E [1] [N]；E [2] [:] indicates E [2]
[1], [2] [2] E ... ..., E [2] [N]；E [3] [:] indicates E [3] [1], E [3] [2] ... ..., E [3] [N]；E [4] [:] indicates E
[4] [1], E [4] [2] ... ..., E [4] [N]；
Step 4: determining the boundary element of grid A according to non-directed graph TA and following boundary element method of discrimination, set corresponding E
[1] value of the item in [:] is 1；
Boundary element method of discrimination: if the adjacent unit number of grid cell is less than its face number, it is considered as boundary element；Net
The adjacent unit number of lattice unit is the number of edges of corresponding nonoriented graph；
Step 5: the affiliated subregion of grid cell after being divided according to Metis is loaded directly into the every value of E [2] [:]；According to
Respective grid points, are added corresponding grid point set by the affiliated subregion of mesh point after Metis division；
Step 6: set Ep, local number Ip is added in grid cell n；
Be arranged Ip=0, p=1,2 ..., P；
Step 7:n=1；
Step 8:Ip=Ip+1；Wherein p=E [2] [n]+1；
Step 9:E [3] [n]=Ip by the local number of all grid divisions and is stored in E [3] [:]；
Step 10: if n≤N meets, going to step 8, otherwise go to step 11；
Step 11: setting Ip=0, p=1,2 ..., P；
Step 12:m=1；
Step 13:Ip=Ip+1；Wherein the value of p is that the value of the affiliated subregion of mesh point after Metis is divided adds 1；
Step 14: set Gp, local number Ip is added in mesh point m；
Step 15: if m≤M meets, going to step 13, otherwise go to step 16；
Step 16:p=1；
Step 17: setting E [4] [:] is 0；
Step 18: pth is generated according to the low computation complexity generation method of single partition aerodynamics grid non-directed graph in step 2
The non-directed graph of a subregion (Gp, Ep)；
Step 19: the boundary element of multiblock technique p is determined according to the boundary element method of discrimination in non-directed graph and step 4,
Setting the entry value in corresponding E [4] [:] is 1；
Local grid element number is to the mapping between the grid grid element number of global grid A by E in multiblock technique p
[2] [:], E [3] [:] are obtained；
All entry value of step 20:E [4] [:] and E [1] [:] are subtracted each other, and obtained result is 1,0, -1 three kind；It as a result is 1
Grid cell be multiblock technique p inner boundary unit, local number is set as l1, l2 ..., lO, and overall situation number is g1,
G2 ..., gO；
Step 21: according to non-directed graph TA adjacent vertex, all adjoining grid cells of gi (1≤i≤O) are obtained, it is adjacent
The global number of grid cell is k1, k2 ..., kI；
According to E [2] [:], the adjoining grid cell for belonging to p subregion is deleted, remaining grid cell overall situation number is kj1,
Kj2 ..., kjJ；
According to E [2] [:], E [3] [:] obtains partition number zi, the local number ni of corresponding global number, compiles with the overall situation
Number correspond；
Then a series of triples (li, zi, ni) is obtained；If (li, zi, ni) is not repeated in set Bp, then
Set Bp is added in (li, zi, ni)；
Step 22:p=p+1；
Step 23: if p≤P meets, going to step 17, otherwise go to step 24；
Step 24: exporting grid the point set G1, G2 ... ..., GP of each subregion；The grid cell set of each subregion is respectively
E1, E2 ... ..., EP, inner boundary set B1, B2 ... ..., BP；
Step 25: post-processing is completed.
Further, a kind of post-processing approach of aerodynamics grid Metis auto-partition as described above, final subregion
The data format of the aerodynamics grid of completion is Tecplot data format.
Further, a kind of post-processing approach of aerodynamics grid Metis auto-partition as described above, this method
Concrete operations process is realized using lightweight Python scripting language.
Further, a kind of post-processing approach of aerodynamics grid Metis auto-partition as described above, size determine
Array E [4] [N] defined with array, set sizes are indefinite to be realized with list () dynamic object.
The invention has the benefit that
(1) each multiblock technique unit, the requirement that mesh point renumbers be can satisfy；
(2) boundary element of each multiblock technique inner boundary can be quickly determined；
Detailed description of the invention
Fig. 1 is grid division schematic diagram；
Fig. 2 is Metis partition data.
Specific embodiment
Technical solution of the present invention is carried out it is further believed that explanation in the following with reference to the drawings and specific embodiments.
Fig. 1 is the aerodynamics containing 1-6 grid cell, and wherein side is adjacent surface, and circle is grid cell, is divided
For 3 subregions, number difference 0,1,2.The data format of grid cell part (is named as Metis unit after Metis auto-partition
Data) as shown in Fig. 2, only indicating subregion belonging to each grid cell.Mesh point partial data format is similar.
A kind of post-processing approach of aerodynamics grid Metis auto-partition of the present invention, comprising the following steps:
Setting to the aerodynamics grid A of subregion includes M mesh point, N number of grid cell, number of partitions P；Metis is certainly
The data of subregion belonging to N number of grid cell are generated after dynamic subregion；
If the grid point set of each subregion is G1, G2 ... ..., GP；The grid cell set of each subregion is respectively E1,
E2 ... ..., EP；The inner boundary set of each subregion distinguishes B1, B2 ... ..., BP；
Either element includes three Data Labels (li, zi, ni) in inner boundary set: li indicates grid cell in this subregion
Interior number, zi indicate that the affiliated partition number of adjacent grid cell, ni indicate the number of adjacent grid cell；I=1~P；
Specific step is as follows:
Step 1: deleting the redundancy gridden data in aerodynamics grid A in N number of grid cell according to following methods；
Redundancy mesh point delet method: the mesh point in unit E is set as (e1,e2,…,eK), repeated grid point is found first
And it is set to -1, then delete the gridden data that value is -1, so that redundancy mesh point in grid cell be deleted；Specific algorithm is such as
Shown in lower:
It include (1,2,3,4) four mesh points such as to the tetrahedron element on the left side Fig. 1.And in the actual number of grid cell
When according to indicating, may be (1,2,3, Isosorbide-5-Nitrae, 4,4,4).Need to reject the gridden data of redundancy, algorithm is as shown in Figure 2.If single
Mesh point in first E is (e1,e2,…,eK), the row 1-4 in Fig. 2 finds repeated grid point and is set to -1, row 5-7 deletion value
For -1 gridden data.
Step 2: the non-directed graph TA of aerodynamics grid A is generated according to following methods；
The low computation complexity generation method of single partition aerodynamics grid non-directed graph: 1) determine that grid cell a is unduplicated
Grid point set G；2) all grid cell set E comprising mesh point in G are obtained；3) a and element in E one by one compared with, obtain a
All neighboring grid cells；Wherein the vertex of non-directed graph is grid cell, and side is the adjacent surface of neighboring grid cells；
Step 3: creation array E [4] [N]；N represents N number of grid cell, and E [1] [:] represents the net in aerodynamics grid A
Whether lattice unit is boundary element, and the value of the item in E [1] [:] is the 0 non-boundary element of expression, and the value of the item in E [1] [:] is 1
It is expressed as boundary element, is defaulted as 0；E [2] [:] indicates which subregion the grid cell of reference numeral belongs to, by Metis subregion
Data determine；E [3] [:] indicates the local number of each multiblock technique unit；E [4] [:] is to reuse part；Symbol ": " table
Show that whole items of corresponding array, E [1] [:] indicate E [1] [1], E [1] [2] ... ..., E [1] [N]；E [2] [:] indicates E [2]
[1], [2] [2] E ... ..., E [2] [N]；E [3] [:] indicates E [3] [1], E [3] [2] ... ..., E [3] [N]；E [4] [:] indicates E
[4] [1], E [4] [2] ... ..., E [4] [N]；
Step 4: determining the boundary element of grid A according to non-directed graph TA and following boundary element method of discrimination, set corresponding E
[1] value of the item in [:] is 1；
Boundary element method of discrimination: if the adjacent unit number of grid cell is less than its face number, it is considered as boundary element；Net
The adjacent unit number of lattice unit is the number of edges of corresponding nonoriented graph；
Step 5: the affiliated subregion of grid cell after being divided according to Metis is loaded directly into the every value of E [2] [:]；According to
Respective grid points, are added corresponding grid point set by the affiliated subregion of mesh point after Metis division；
Step 6: set Ep, local number Ip is added in grid cell n；
Be arranged Ip=0, p=1,2 ..., P；
Step 7:n=1；
Step 8:Ip=Ip+1；Wherein p=E [2] [n]+1；
Step 9:E [3] [n]=Ip by the local number of all grid divisions and is stored in E [3] [:]；
Step 10: if n≤N meets, going to step 8, otherwise go to step 11；
Step 11: setting Ip=0, p=1,2 ..., P；
Step 12:m=1；
Step 13:Ip=Ip+1；Wherein the value of p is that the value of the affiliated subregion of mesh point after Metis is divided adds 1；
Step 14: set Gp, local number Ip is added in mesh point m；
Step 15: if m≤M meets, going to step 13, otherwise go to step 16；
Step 16:p=1；
Step 17: setting E [4] [:] is 0；
Step 18: pth is generated according to the low computation complexity generation method of single partition aerodynamics grid non-directed graph in step 2
The non-directed graph of a subregion (Gp, Ep)；
Step 19: the boundary element of multiblock technique p is determined according to the boundary element method of discrimination in non-directed graph and step 4,
Setting the entry value in corresponding E [4] [:] is 1；
Local grid element number is to the mapping between the grid grid element number of global grid A by E in multiblock technique p
[2] [:], E [3] [:] are obtained；
All entry value of step 20:E [4] [:] and E [1] [:] are subtracted each other, and obtained result is 1,0, -1 three kind；It as a result is 1
Grid cell be multiblock technique p inner boundary unit, local number is set as l1, l2 ..., lO, and overall situation number is g1,
G2 ..., gO；
Step 21: according to non-directed graph TA adjacent vertex, all adjoining grid cells of gi (1≤i≤O) are obtained, it is adjacent
The global number of grid cell is k1, k2 ..., kI；
According to E [2] [:], the adjoining grid cell for belonging to p subregion is deleted, remaining grid cell overall situation number is kj1,
Kj2 ..., kjJ；
According to E [2] [:], E [3] [:] obtains partition number zi, the local number ni of corresponding global number, compiles with the overall situation
Number correspond；
Then a series of triples (li, zi, ni) is obtained；If (li, zi, ni) is not repeated in set Bp, then
Set Bp is added in (li, zi, ni)；
Step 22:p=p+1；
Step 23: if p≤P meets, going to step 17, otherwise go to step 24；
Step 24: exporting grid the point set G1, G2 ... ..., GP of each subregion；The grid cell set of each subregion is respectively
E1, E2 ... ..., EP, inner boundary set B1, B2 ... ..., BP；
Step 25: post-processing is completed.
Wherein step 6-10 obtains the local number of all grid divisions and is stored in E [3] [:].Step 11-15 with
Step 6-10 is similar, it is therefore an objective to obtain each subregion local area network lattice point number.
In this embodiment, the data format for the aerodynamics grid that final subregion is completed is the data such as Tecplot
Format.Concrete operations process of the invention can realize using lightweight Python scripting language, the array E that size determines
[4] [N] available array defines, and set sizes are indefinite can be realized using list () dynamic object.
Claims (3)
1. a kind of post-processing approach of aerodynamics grid Metis auto-partition, it is characterised in that: the following steps are included:
Setting to the aerodynamics grid A of subregion includes M mesh point, N number of grid cell, number of partitions P；Metis divides automatically
The data of subregion belonging to N number of grid cell are generated behind area；
If the grid point set of each subregion is G1, G2 ... ..., GP；The grid cell set of each subregion is respectively E1, E2 ... ...,
EP；The inner boundary set of each subregion distinguishes B1, B2 ... ..., BP；
Either element includes three Data Labels (li, zi, ni) in inner boundary set: li indicates grid cell in this subregion
Number, zi indicate that the affiliated partition number of adjacent grid cell, ni indicate the number of adjacent grid cell；I=1~P；
Specific step is as follows:
Step 1: deleting the redundancy gridden data in aerodynamics grid A in N number of grid cell according to following methods；
Redundancy mesh point delet method: the mesh point in grid cell e is set as (e1,e2,Λ,eK), repeated grid point is found first
And it is set to -1, then delete the gridden data that value is -1, so that redundancy mesh point in grid cell be deleted；
Step 2: the non-directed graph TA of aerodynamics grid A is generated according to following methods；
The low computation complexity generation method of single partition aerodynamics grid non-directed graph: 1) the unduplicated grid of grid cell a is determined
Point set G；2) all grid cell set E comprising mesh point in G are obtained；3) a and element in E one by one compared with, obtain the institute of a
There are neighboring grid cells；Wherein the vertex of non-directed graph is grid cell, and side is the adjacent surface of neighboring grid cells；
Step 3: creation array E [4] [N]；N represents N number of grid cell, and E [1] [:] represents the grid list in aerodynamics grid A
Whether member is boundary element, and the value of the item in E [1] [:] is the 0 non-boundary element of expression, and the value of the item in E [1] [:] is 1 expression
For boundary element, it is defaulted as 0；E [2] [:] indicates which subregion the grid cell of reference numeral belongs to, by Metis partition data
It determines；E [3] [:] indicates the local number of each multiblock technique unit；E [4] [:] is to reuse part；Symbol ": " indicates phase
Whole items of array are answered, E [1] [:] indicates E [1] [1], E [1] [2] ... ..., E [1] [N]；E [2] [:] indicates E [2] [1], E
[2] [2] ... ..., E [2] [N]；E [3] [:] indicates E [3] [1], E [3] [2] ... ..., E [3] [N]；E [4] [:] indicates E [4]
[1], [4] [2] E ... ..., E [4] [N]；
Step 4: determining the boundary element of grid A according to non-directed graph TA and following boundary element method of discrimination, set corresponding E [1] [:]
In item value be 1；
Boundary element method of discrimination: if the adjacent unit number of grid cell is less than its face number, it is considered as boundary element；Grid list
The adjacent unit number of member is the number of edges of corresponding nonoriented graph；
Step 5: the affiliated subregion of grid cell after being divided according to Metis is loaded directly into the every value of E [2] [:]；According to Metis
Corresponding grid point set is added in respective grid points by the affiliated subregion of mesh point after division；
Step 6: set Ep, local number Ip is added in grid cell n；
Be arranged Ip=0, p=1,2 ..., P；
Step 7:n=1；
Step 8:Ip=Ip+1；Wherein p=E [2] [n]+1；
Step 9:E [3] [n]=Ip by the local number of all grid divisions and is stored in E [3] [:]；
Step 10: if n≤N meets, going to step 8, otherwise go to step 11；
Step 11: setting Ip=0, p=1,2 ..., P；
Step 12:m=1；
Step 13:Ip=Ip+1；Wherein the value of p is that the value of the affiliated subregion of mesh point after Metis is divided adds 1；
Step 14: set Gp, local number Ip is added in mesh point m；
Step 15: if m≤M meets, going to step 13, otherwise go to step 16；
Step 16:p=1；
Step 17: setting E [4] [:] is 0；
Step 18: generating p-th point according to the low computation complexity generation method of single partition aerodynamics grid non-directed graph in step 2
The non-directed graph in area (Gp, Ep)；
Step 19: determining the boundary element of p-th of subregion according to the boundary element method of discrimination in non-directed graph and step 4, set phase
Answering the entry value in E [4] [:] is 1；
Local grid element number is to the mapping between the grid grid element number of global grid A by E [2] in p-th of subregion
[:], E [3] [:] are obtained；
All entry value of step 20:E [4] [:] and E [1] [:] are subtracted each other, and obtained result is 1,0, -1 three kind；It as a result is 1 net
Lattice unit is the inner boundary unit of multiblock technique p, and local number is set as l1, l2 ..., lO, and overall situation number is g1, g2 ...,
gO；
Step 21: according to non-directed graph TA adjacent vertex, obtaining gi, 1≤i≤O, all adjoining grid cells, adjacent grid
The global number of unit is k1, k2 ..., kI；
According to E [2] [:], the adjoining grid cell for belonging to p subregion is deleted, remaining grid cell overall situation number is kj1,
Kj2 ..., kjJ；
According to E [2] [:], E [3] [:] obtains partition number zi, the local number ni of corresponding global number, with global number one
One is corresponding；
Then a series of triples (li, zi, ni) is obtained；If (li, zi, ni) is not repeated in set Bp, then (li, zi,
Ni set Bp) is added；
Step 22:p=p+1；
Step 23: if p≤P meets, going to step 17, otherwise go to step 24；
Step 24: exporting grid the point set G1, G2 ... ..., GP of each subregion；The grid cell set of each subregion is respectively E1,
E2 ... ..., EP, inner boundary set B1, B2 ... ..., BP；
Step 25: post-processing is completed.
2. a kind of post-processing approach of aerodynamics grid Metis auto-partition as described in claim 1, it is characterised in that:
The data format for the aerodynamics grid that final subregion is completed is Tecplot data format.
3. a kind of post-processing approach of aerodynamics grid Metis auto-partition as described in claim 1, it is characterised in that:
The concrete operations process of this method is realized using lightweight Python scripting language.
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