CN108197367A - A kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method based on flow field flux step - Google Patents
A kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method based on flow field flux step Download PDFInfo
- Publication number
- CN108197367A CN108197367A CN201711443613.2A CN201711443613A CN108197367A CN 108197367 A CN108197367 A CN 108197367A CN 201711443613 A CN201711443613 A CN 201711443613A CN 108197367 A CN108197367 A CN 108197367A
- Authority
- CN
- China
- Prior art keywords
- pseudo
- precision
- viscosity
- flow field
- equation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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]
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Complex Calculations (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing methods based on flow field flux step, subdivision is carried out to zoning using unstrctured grid, governing equation uses Euler equations, establish using basic function, test function, Gauss points as representative DG high-precision frames, new artificial viscous term is constructed based on the step of conservation variable in element interface in equation simultaneously, the convective term of equation uses the discrete solution of HLL forms, in the case of effective capturing shock, ensure robustness and computational accuracy；Even if the present invention is in the case of without Developing Shock-Capturing, flux at element interface is also the necessary intermediate variable of equation solution, the flux step at the element interface of flow field is selected to construct pseudo-viscosity, calculation amount can be reduced compared to other methods, so as to save the time of calculating.
Description
Technical field
Present document relates to Fluid Mechanics Computation technology basins, and in particular to a kind of high-precision interruption based on flow field flux step
Galerkin pseudo-viscosity Developing Shock-Capturing methods.
Background technology
The high-precision DG methods good characteristic in terms of numerical dissipation and dispersion at present is theoretically very suitable for solving fluid
Complicated Issues On Multi-scales in calculating, high-precision DG methods achieve certain achievement in the calculating of low speed incompressible fluid
And it is widely applied.But when high-precision DG methods are applied to the calculating of compressible fluid, shock wave can be generated in flow field,
According to Godunov principles, high-precision DG methods can generate Gibbs phenomenons near shock discontinuity, cause the generation of non-physical solution,
Cause to calculate and interrupt.Developing Shock-Capturing has become the main bottleneck that high-precision DG methods is hindered to calculate development in compressible fluid.
At present, high-precision DG Developing Shock-Capturings method is all not mature enough, and previous Developing Shock-Capturing method mainly includes limiter and reconstruct.This
A little methods are all that shock wave is captured by the way of post processing, when using these modes, can be drawn in entire solution procedure
Enter uncontrollable nonlinear terms, it can there are unmatched feelings due to the introducing of nonlinear terms, between physical process and governing equation
Condition, this, which will directly result in shock wave region, there is serious degradation, poor astringency, poor robustness, is susceptible to non-physical concussion, swashs
Wave captures the problems such as not enough " sharp ".
Invention content
The purpose of the present invention is to propose to a kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method, this method roots
According to the characteristic of shock wave and dimensional analysis principle, using the flux step in unit interface in flow field, construct a kind of new artificial
Viscous shock method for catching is mainly used for solving poor astringency, the robust that high-precision DG methods encounter during Developing Shock-Capturing
Property it is poor, be susceptible to non-physical concussion, Developing Shock-Capturing not enough " sharp " the problems such as.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method based on flow field flux step, including following
Step：
Step 1：High-precision DG frames are established, including the base letter in mesh generation, Euler governing equations, finite element method
The information such as number, test function, Gauss points；
Step 2：Using the flux step in element interface as the pseudo-viscosity coefficient in basic structural unit；
Step 3：Pseudo-viscosity coefficient is brought into Euler governing equations, solution obtains simulation result.
The present invention carries out zoning subdivision using unstrctured grid, and governing equation uses Euler equations, establishes with base
Function, test function, the DG high-precision frames that Gauss points are representative.Simultaneously with conservation in element interface in equation
New artificial viscous term is constructed based on the step of variable, the convective term of equation uses the discrete solution of HLL forms.Effectively capturing
In the case of shock wave, ensure robustness and computational accuracy.
Compared with existing means, the method have the characteristics that：
Even if the 1st, in the case of without Developing Shock-Capturing, the flux at element interface is also during equation solution is necessary
Between variable, the flux step at the element interface of flow field is selected to construct pseudo-viscosity, compared to other methods can reduce calculating
Amount, so as to save the time of calculating.
2nd, Developing Shock-Capturing, pressure distribution curve more " cutting edge of a knife or a sword near shock wave are carried out using flux step pseudo-viscosity method
Profit ", while convergence is better than other methods.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is the flow chart of the method for the present invention；
Fig. 2 is the one-dimensional sod problems calculated using the method for the present invention；
Fig. 3 is the comparison of convergence curve and other methods that NACA0012 aerofoil profiles are calculated using the method for the present invention.
Specific embodiment
All features or disclosed all methods disclosed in this specification or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
A kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing based on flow field flux step disclosed by the invention
Method, including three parts, as shown in Figure 1.
First part：High-precision DG frames are established, including the base in mesh generation, Euler governing equations, finite element method
The calculating and storage of the information such as function, test function, Gauss points.Include the following steps：
Step 101 carries out mesh generation using unstrctured grid to zoning, for two-dimentional computational domain, the net of subdivision
Lattice type includes triangle and quadrangle, and for three-dimensional computations domain, trellis-type includes tetrahedron, hexahedron, triangular prism and gold
Word tower shape.
Euler equations under step 102, structure differential form
Wherein U represents the conserved quantity in flow field, and U is a vector, U=(ρ, ρ u, ρ v, ρ w, ρ E)T,Represent conserved quantity
Relative to the partial derivative of time t, FcRepresent conservative flux,Represent the divergence of conservative flux.
Step 103 selects Taylor bases as basic function and test function, and the conserved quantity in flow field uses the line of basic function
Property combination representCalculating the volume under different type grid divides Gauss points and Line Integral Gauss to accumulate
Branch, and carry out storing in memory spare.
The linear combination of conserved quantity is brought into Euler governing equations (1), and equation is integrated by step 104, then
It is multiplied by basic function φ simultaneously on equation both sides, using Green's Gauss formula, the DG obtained under weak situation solves equation
Wherein, M=∫ΩφiφjRepresentation quality matrix, u represent the coefficient used during the basic function linear combination of conservation variable
Also known as degree of freedom,Represent derivative of the degree of freedom to the time.For element sides interface,Exterior normal side for element sides interface
To,Represent the gradient of basic function.
Second part：Using the flux step in element interface as the pseudo-viscosity coefficient in basic structural unit, packet
Include following steps：
Step 201, selection Laplce's pseudo-viscosity model bring formula (1) into and repeat step 103 and 104 and wrapped
DG containing artificial viscous term solves equation
Wherein, ε is artificial viscosity, the numerical value of pseudo-viscosity in determining means,Represent the gradient of degree of freedom.
Step 202 reconfigures pseudo-viscosity coefficient ε, the step of flux at selecting unit interface (WithAmount of flux at left and right sides of representative unit interface) and conservation variable average value (WithConservation variate-value at left and right sides of representative unit interface) linear combination is carried out, it constructs at interface
Intermediate step Ujump
Step 203, the intermediate step amount U that will be obtained in step 202jumpIt is integrated at element interface, Ran Houji
The gross area S of component divided by unit obtains the distribution U of step amount in cell cubecell
Step 204 utilizes the Step distribution U in cell cubecellWith the barometric gradient at unit body-centeredEmpirical parameter C∈
And the reference scale h of local grid unit, three are multiplied, then divided by the pressure p at unit body-centered, so as to construct unit
Interior pseudo-viscosity coefficient ε
Part III：Pseudo-viscosity coefficient is brought into governing equation, solution obtains simulation result；
Pseudo-viscosity coefficient ε in the unit obtained in step 204 is brought into comprising artificial viscous term by step 301
DG is solved in equation equation (3).
Step 302, to DG solve equation carry out it is discrete, by iterative calculation solve governing equation, what is emulated is pneumatic
And flow field as a result.
As shown in Fig. 2, for the one-dimensional sod problems calculated using the method for the present invention, it can be seen that the curve point near shock wave
Cloth more " sharp ", for shock wave region, pressure or density curve should be a vertical line in theory, if calculated
As a result it gets over " sharp ", result is just closer to theoretical value, it is clear from figure 2 that new method is in " sharp " degree
It is more superior than other methods, as a result closer to theoretical value.For the result of calculation of new method in Fig. 2, Fig. 3 is shown using this hair
The comparison of convergence curve and other methods that NACA0012 aerofoil profiles are calculated in bright method, it can clearly be seen that this method is being counted
It calculates and other methods is considerably less than on convergence time.
The invention is not limited in aforementioned specific embodiments.The present invention, which expands to, any in the present specification to be disclosed
The step of new feature or any new combination and any new method or process disclosed or any new combination.
Claims (5)
- A kind of 1. high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method based on flow field flux step, it is characterised in that Include the following steps：Step 1：Establish high-precision DG frames, including in mesh generation, Euler governing equations, finite element method basic function, The information such as test function, Gauss points；Step 2：Using the flux step in element interface as the pseudo-viscosity coefficient in basic structural unit；Step 3：Pseudo-viscosity coefficient is brought into Euler governing equations, solution obtains simulation result.
- 2. a kind of high-precision the discontinuous Galerkin pseudo-viscosity shock wave based on flow field flux step according to claim 1 Method for catching, it is characterised in that high-precision DG frames are established in the step 1 and are included the following steps：Step 1：Mesh generation is carried out to zoning using unstrctured grid；Step 2：Build the Euler equations under differential form；Step 3：Taylor bases are selected as basic function and test function, the conserved quantity in flow field uses linear group of basic function Close and represent, the volume calculated under different type grid divides Gauss points and Line Integral Gauss points, and in memory into Row storage is spare；Step 4：The linear combination of conserved quantity is brought into the Euler governing equations under differential form, and equation is integrated, Then it is multiplied by basic function simultaneously on equation both sides, using Green's Gauss formula, the DG obtained under weak situation solves equation.
- 3. a kind of high-precision the discontinuous Galerkin pseudo-viscosity shock wave based on flow field flux step according to claim 2 Method for catching, it is characterised in that in the step 1, for two-dimentional computational domain, the trellis-type of subdivision includes triangle and four sides Shape, for three-dimensional computations domain, the trellis-type of subdivision includes tetrahedron, hexahedron, triangular prism and pyramid shape.
- 4. a kind of high-precision the discontinuous Galerkin pseudo-viscosity shock wave based on flow field flux step according to claim 2 Method for catching, it is characterised in that using the flux step in element interface as the pseudo-viscosity coefficient packet in basic structural unit Include following steps：Step 1：Laplce's pseudo-viscosity model is selected, bring Euler equations under differential form into and repeats high-precision DG frames The step of establishing three and step 4 obtain the DG comprising artificial viscous term and solve equation；Step 2：Pseudo-viscosity coefficient is reconfigured, the step and conservation of conservation variable at selecting unit interface The average value of variable carries out linear combination, constructs the intermediate step at interface；Step 3：The intermediate step amount obtained in step 2 is integrated at element interface, then integration amount divided by list The gross area of member, obtains the distribution of step amount in cell cube；Step 4：Using the Step distribution in cell cube and the barometric gradient at unit body-centered, empirical parameter and local grid Then divided by the pressure at unit body-centered the reference scale of unit, three are multiplied, so as to construct the pseudo-viscosity system in unit Number.
- 5. a kind of high-precision the discontinuous Galerkin pseudo-viscosity shock wave based on flow field flux step according to claim 4 Method for catching, it is characterised in that the pseudo-viscosity coefficient calculated in step 4 is brought into the DG comprising artificial viscous term and is solved Equation, it is discrete to DG solution equation progress, governing equation, the aerodynamic consequence emulated and flow field are solved by iterative calculation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711443613.2A CN108197367B (en) | 2017-12-27 | 2017-12-27 | High-precision intermittent Galerkin artificial viscous shock wave capturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711443613.2A CN108197367B (en) | 2017-12-27 | 2017-12-27 | High-precision intermittent Galerkin artificial viscous shock wave capturing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108197367A true CN108197367A (en) | 2018-06-22 |
| CN108197367B CN108197367B (en) | 2021-07-27 |
Family
ID=62584442
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711443613.2A Active CN108197367B (en) | 2017-12-27 | 2017-12-27 | High-precision intermittent Galerkin artificial viscous shock wave capturing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108197367B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111159956A (en) * | 2019-12-10 | 2020-05-15 | 北京航空航天大学 | Feature-based flow field discontinuity capturing method |
| CN112665820A (en) * | 2021-03-15 | 2021-04-16 | 中国空气动力研究与发展中心计算空气动力研究所 | R-type grid self-adaptive moving method and device based on variable difference and relative displacement |
| CN113591417A (en) * | 2021-08-11 | 2021-11-02 | 中国空气动力研究与发展中心计算空气动力研究所 | Viscous item processing method applied to high-precision Galegac Liaojin fluid simulation |
| CN113656920A (en) * | 2021-10-20 | 2021-11-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Missile rudder surface hinge moment design method capable of reducing power redundancy of steering engine |
| CN113742967A (en) * | 2021-08-27 | 2021-12-03 | 北京航空航天大学 | Interrupted finite element artificial viscous shock wave processing method based on strong residual error |
| CN114091376A (en) * | 2022-01-21 | 2022-02-25 | 中国空气动力研究与发展中心计算空气动力研究所 | High-precision reconstruction correction shock wave capturing method based on subunit weighting format |
| CN114611421A (en) * | 2022-02-16 | 2022-06-10 | 上海机电工程研究所 | Artificial viscosity method and system based on modal attenuation |
| CN114638173A (en) * | 2022-01-25 | 2022-06-17 | 中国空气动力研究与发展中心计算空气动力研究所 | High-order nonlinear shock wave capturing space dispersion method |
| CN115238397A (en) * | 2022-09-15 | 2022-10-25 | 中国人民解放军国防科技大学 | Method and device for calculating thermal environment of hypersonic aircraft and computer equipment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002110807A (en) * | 2000-09-29 | 2002-04-12 | Fujitsu Ltd | Allotment method of timing limitation, and allotment device |
| CN1764917A (en) * | 2003-02-05 | 2006-04-26 | 莫尔德弗洛爱尔兰有限公司 | Apparatus and methods for performing process simulation using a hybrid model |
| CN102682146A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Method for simulating numerical value of compressible vortex flow field |
| CN104036095A (en) * | 2014-06-27 | 2014-09-10 | 北京航空航天大学 | Regional-decomposition based high-precision coupling fast-calculation method for complex-shape flow field |
| CN104298823A (en) * | 2014-10-09 | 2015-01-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Analysis method and system of high- and low-temperature balances |
| CN105893693A (en) * | 2016-04-21 | 2016-08-24 | 北京航空航天大学 | Compressible turbulence direct numerical simulation method based on compact type high resolution hybrid format |
| CN106682262A (en) * | 2016-11-21 | 2017-05-17 | 中国航天空气动力技术研究院 | Numerical simulation method for obtaining aircraft flow fields |
-
2017
- 2017-12-27 CN CN201711443613.2A patent/CN108197367B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002110807A (en) * | 2000-09-29 | 2002-04-12 | Fujitsu Ltd | Allotment method of timing limitation, and allotment device |
| CN1764917A (en) * | 2003-02-05 | 2006-04-26 | 莫尔德弗洛爱尔兰有限公司 | Apparatus and methods for performing process simulation using a hybrid model |
| CN102682146A (en) * | 2011-11-30 | 2012-09-19 | 天津空中代码工程应用软件开发有限公司 | Method for simulating numerical value of compressible vortex flow field |
| CN104036095A (en) * | 2014-06-27 | 2014-09-10 | 北京航空航天大学 | Regional-decomposition based high-precision coupling fast-calculation method for complex-shape flow field |
| CN104298823A (en) * | 2014-10-09 | 2015-01-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Analysis method and system of high- and low-temperature balances |
| CN105893693A (en) * | 2016-04-21 | 2016-08-24 | 北京航空航天大学 | Compressible turbulence direct numerical simulation method based on compact type high resolution hybrid format |
| CN106682262A (en) * | 2016-11-21 | 2017-05-17 | 中国航天空气动力技术研究院 | Numerical simulation method for obtaining aircraft flow fields |
Non-Patent Citations (3)
| Title |
|---|
| HUERTA A 第: "A simple shock‐capturing technique for high‐order discontinuous Galerkin methods", 《INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS》 * |
| 于剑，阎超: "基于人工粘性的间断Galerkin有限元方法", 《空气动力学学报》 * |
| 赵辉: "超声速不同介质横向喷流数值模拟", 《中国优秀硕士学位论文全文数据库（工程科技Ⅱ辑）》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111159956A (en) * | 2019-12-10 | 2020-05-15 | 北京航空航天大学 | Feature-based flow field discontinuity capturing method |
| CN111159956B (en) * | 2019-12-10 | 2021-10-26 | 北京航空航天大学 | Feature-based flow field discontinuity capturing method |
| CN112665820A (en) * | 2021-03-15 | 2021-04-16 | 中国空气动力研究与发展中心计算空气动力研究所 | R-type grid self-adaptive moving method and device based on variable difference and relative displacement |
| CN112665820B (en) * | 2021-03-15 | 2021-06-04 | 中国空气动力研究与发展中心计算空气动力研究所 | R-type grid self-adaptive moving method and device based on variable difference and relative displacement |
| CN113591417A (en) * | 2021-08-11 | 2021-11-02 | 中国空气动力研究与发展中心计算空气动力研究所 | Viscous item processing method applied to high-precision Galegac Liaojin fluid simulation |
| CN113591417B (en) * | 2021-08-11 | 2023-02-24 | 中国空气动力研究与发展中心计算空气动力研究所 | Viscous item processing method applied to high-precision Anzelia galamurensis fluid simulation |
| CN113742967A (en) * | 2021-08-27 | 2021-12-03 | 北京航空航天大学 | Interrupted finite element artificial viscous shock wave processing method based on strong residual error |
| CN113742967B (en) * | 2021-08-27 | 2023-10-31 | 北京航空航天大学 | Intermittent finite element artificial viscous shock wave processing method based on strong residual error |
| CN113656920A (en) * | 2021-10-20 | 2021-11-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Missile rudder surface hinge moment design method capable of reducing power redundancy of steering engine |
| CN114091376A (en) * | 2022-01-21 | 2022-02-25 | 中国空气动力研究与发展中心计算空气动力研究所 | High-precision reconstruction correction shock wave capturing method based on subunit weighting format |
| CN114638173A (en) * | 2022-01-25 | 2022-06-17 | 中国空气动力研究与发展中心计算空气动力研究所 | High-order nonlinear shock wave capturing space dispersion method |
| CN114638173B (en) * | 2022-01-25 | 2023-06-02 | 中国空气动力研究与发展中心计算空气动力研究所 | Space discrete method for capturing high-order nonlinear shock waves |
| CN114611421A (en) * | 2022-02-16 | 2022-06-10 | 上海机电工程研究所 | Artificial viscosity method and system based on modal attenuation |
| CN115238397A (en) * | 2022-09-15 | 2022-10-25 | 中国人民解放军国防科技大学 | Method and device for calculating thermal environment of hypersonic aircraft and computer equipment |
| CN115238397B (en) * | 2022-09-15 | 2022-12-02 | 中国人民解放军国防科技大学 | Method and device for calculating thermal environment of hypersonic aircraft and computer equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108197367B (en) | 2021-07-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108197367A (en) | A kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method based on flow field flux step | |
| CN110110413B (en) | Structural topology optimization method based on material field reduction progression expansion | |
| CN105118090B (en) | A kind of point cloud filtering method of adaptive complicated landform structure | |
| CN108197072A (en) | A kind of high-precision the discontinuous Galerkin pseudo-viscosity Developing Shock-Capturing method based on weighting conservation variable step | |
| CN108153984A (en) | A kind of high-precision interruption character used in proper names and in rendering some foreign names the Liao Dynasty people of the Jin Dynasty work Viscous shock method for catching based on flow field density step | |
| CN104318598B (en) | A kind of realization method and system of the solid unidirectional couplings of three-dimensional flow | |
| CN109871949A (en) | Convolutional neural networks accelerator and accelerated method | |
| CN106682262A (en) | Numerical simulation method for obtaining aircraft flow fields | |
| CN111046615B (en) | Riemann solver shock wave instability suppression method and system | |
| CN107038308B (en) | A kind of regular grid terrain modeling method based on linear interpolation | |
| CN102915560A (en) | Threshold-irrelative point cloud filtering method and device for airborne laser radar | |
| CN102163321B (en) | Image segmentation method based on lattice Boltzman model | |
| CN108959720A (en) | A kind of Fluid Mechanics Computation real time simulation method, electronic equipment, storage medium and system | |
| CN106446546B (en) | Meteorological data complementing method based on the automatic encoding and decoding algorithm of convolution | |
| CN111079326A (en) | Two-dimensional anisotropic grid unit measurement tensor field smoothing method | |
| Wilderotter | An adaptive numerical method for the Richards equation with root growth | |
| CN103065015A (en) | Internal force path geometrical morphology based low-carbon material-saving bearing structure design method | |
| CN102737378A (en) | Method and system for partitioning image by using geodesic active contour | |
| CN106844889A (en) | Quadrilateral structure Meshing Method based on the blocking principle of non-decile | |
| CN102663782B (en) | Painting rendering method based on stroke texture analysis | |
| CN106202522B (en) | A kind of multiplexing method and system of flow field integral curve | |
| CN108470208A (en) | It is a kind of based on be originally generated confrontation network model grouping convolution method | |
| CN104851082B (en) | A kind of mixed self-adapting image de-noising method based on gradient and Laplace operator | |
| CN115713008A (en) | Real-time correction method, system, device and medium for basin flood simulation calculation | |
| Maggioli et al. | A physically-inspired approach to the simulation of plant wilting |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhao Hui Inventor after: Ma Mingsheng Inventor after: Wu Xiaojun Inventor after: Zhang Yaobing Inventor after: Chen Jiangtao Inventor after: Liu Wei Inventor after: Zhang Peihong Inventor after: Gong Xiaoquan Inventor after: Yang Yueyue Inventor before: Zhao Hui Inventor before: Liu Wei Inventor before: Chen Jiangtao Inventor before: Ma Mingsheng |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |