CN114896710A - Contact collision analysis method for aviation structure impact analysis - Google Patents
Contact collision analysis method for aviation structure impact analysis Download PDFInfo
- Publication number
- CN114896710A CN114896710A CN202210829748.7A CN202210829748A CN114896710A CN 114896710 A CN114896710 A CN 114896710A CN 202210829748 A CN202210829748 A CN 202210829748A CN 114896710 A CN114896710 A CN 114896710A
- Authority
- CN
- China
- Prior art keywords
- slave node
- node
- contact
- main
- main unit
- 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
Images
Classifications
-
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
- G06F17/11—Complex mathematical operations for solving equations, e.g. nonlinear equations, general mathematical optimization problems
- G06F17/12—Simultaneous equations, e.g. systems of linear equations
-
- 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]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/28—Fuselage, exterior or interior
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Mathematical Physics (AREA)
- Pure & Applied Mathematics (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- Data Mining & Analysis (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Software Systems (AREA)
- Databases & Information Systems (AREA)
- Algebra (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Operations Research (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a contact collision analysis method for aviation structure impact analysis, which comprises the following steps: firstly, constructing a contact surface of a finite element model of an aeronautical structure; secondly, determining a main cell surface contacted by the slave node n; thirdly, calculating local coordinates of a projection point c of the slave node n on the main unit surface S; fourthly, judging whether the slave node n penetrates through the main unit surface S; and fifthly, applying a normal contact force and a friction force between the slave node n and the projection point c. All the main nodes on the contact surface are placed in each bucket in a classified mode, and then contact search is carried out, so that the calculation amount of contact search is greatly reduced, and the calculation speed and efficiency are improved; and then, the calculation formula of the local coordinates of the projection points is converted into a solution one-dimensional quadratic equation set, so that the traditional Newton-Laplacian iterative algorithm is replaced, the calculation speed and efficiency of the local coordinates of the projection points are greatly increased, a non-iterative calculation method is realized, and the robustness of the contact collision analysis method is improved.
Description
Technical Field
The invention belongs to the technical field of aviation structure impact analysis, and particularly relates to a contact collision analysis method for aviation structure impact analysis.
Background
In the field of aeronautics, discrete sources are intended to refer to foreign objects that may threaten the safety of aircraft structures, including birds, hail, broken engine blades, weapons debris, tire debris, runway debris, and other similar objects. The structure of the airplane in service often meets the impact threat of various discrete sources, and after the airplane is impacted, invisible damage, visible cracks and even penetrating damage are easy to occur inside the airplane, so that accidents are directly or indirectly caused. The existing regulations are as follows: in the event of structural damage from impact from a discrete source, the aircraft must be able to successfully complete the flight. Therefore, how to accurately describe the impact behavior of the discrete source has important theoretical significance and wide engineering application prospect in developing the numerical analysis of the impact of the discrete source.
Numerical simulation of the process of discrete source impingement is one of the important methods to recognize and explore the damage of deformation on the surface and inside of the structure. In the existing contact collision finite element analysis method, the determination of the contact interface and the contact state is very time-consuming, and the contact calculation usually accounts for more than half of the total solving time of the problem. Therefore, the development of a high-efficiency and high-precision contact collision analysis method is very urgent for practical engineering application.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a contact collision analysis method for aviation structure impact analysis aiming at the defects in the prior art, all main nodes on the contact surface are placed in each bucket in a classified manner, and then contact search is carried out on the bucket where the slave node n is located and the main nodes in the buckets adjacent to the bucket, so that the calculation amount in the existing global search method is greatly reduced, and the calculation speed and efficiency are improved; and then, a new solving method of the local coordinates of the projection points is adopted to replace the traditional Newton-Laplacian iterative algorithm, and the new solving method converts the calculation formula of the local coordinates of the projection points into a solution one-dimensional quadratic equation set, so that the calculation speed and efficiency of the local coordinates of the projection points are greatly increased, a non-iterative calculation method is realized, and the robustness of the contact collision analysis method is improved.
In order to solve the technical problems, the invention adopts the technical scheme that: a contact crash analysis method for aeronautical structure impact analysis, characterized in that it comprises the following steps:
step one, constructing a contact surface of a finite element model of an aeronautical structure;
establishing an aeronautical structure finite element model, carrying out grid division on the aeronautical structure finite element model, wherein the grids are hexahedral grids, classifying the surfaces of all the hexahedral grids in the aeronautical structure finite element model, and when one surface is only the surface of one hexahedral grid, the surface is an external surface, otherwise, the surface is an internal surface; joining all external surfaces together to form a contact surface;
step two, determining a main cell surface contacted by the slave node n:
step 201, recording any node in a given impact discrete source finite element node set as a slave node n, recording the external surface as a main unit surface, and recording the node forming the main unit surface as a main node; in LS-Dyna, a segment-based bucket classification searching method is adopted, all main nodes contacting the surface are placed in each bucket in a classification mode, and the bucket where a slave node n is located is determined according to the spatial position of the slave node n;
step 202, searching a bucket where the slave node n is located and a master node in a bucket adjacent to the bucket by using a local search algorithm, determining the master node closest to the slave node n, selecting a master unit surface contacted by the slave node n from all master unit surfaces related to the master node closest to the slave node n, and recording the master unit surface as a master unit surface S;
step three, calculating the local coordinates of the projection point c of the slave node n on the main unit surface S:
step 301, determining a plane with the smallest included angle with the main unit plane S in the XOY, XOZ and YOZ planes of the natural coordinate system as a target projection plane;
step 302, recording the coordinates of the projection point of the slave node n on the target projection plane as
The coordinates of the projection points of the four master nodes of the master unit plane S on the target projection plane are recorded as
Where i is the number of the four master nodes of the master unit plane S, i =1,2,3, 4;
303, according to the formula
Calculating local coordinates of a projected point c of the slave node n on the main unit plane S
(ii) a Wherein the content of the first and second substances,
is a two-dimensional geometric interpolation shape function,
coordinates of a main node with the number i on the main unit surface S in a natural coordinate system are set;
step four, judging whether the slave node n penetrates through the main unit surface S according to the distance vector from the slave node n to the projection point c:
when the distance vector from the node n to the projection point c is not less than 0, the slave node n does not penetrate the main cell plane S, that is, the slave node n does not generate a contact collision;
when the distance vector from the node n to the projection point c is less than 0, the slave node n penetrates through the main unit surface S, and step five is executed;
and fifthly, applying normal contact force and friction force between the slave node n and the projection point c by adopting a penalty function method, and carrying out dynamic analysis on the finite element model of the aeronautical structure.
The contact collision analysis method for the impact analysis of the aeronautical structure is characterized by comprising the following steps of: in step 201, in the segment-based bucket classification search method, the method for determining the length and the number of buckets is as follows:
s1, obtaining the diagonal lengths of all main cell faces of the contact surface, making the length of the pocket
1/2 which is the longest diagonal length among the diagonals of all the main unit faces;
s2, obtaining the coordinates of the center points of all the main unit surfaces of the touch surface, and screening to obtain the maximum value of the coordinates of the center points of all the main unit surfaces
、
、
And minimum value
、
、
；
According to the formula
Calculating the number of buckets
(ii) a Wherein the content of the first and second substances,
、
、
is bucket atAnd the number of the distributed seeds in three directions of the overall coordinate system.
Compared with the prior art, the invention has the distinguishing technical characteristics that: all the main nodes of the contact surface are placed in each bucket in a classified mode, then contact search is conducted on the bucket where the slave node n is located and the main nodes in the buckets adjacent to the bucket, the calculation amount in the existing global search method is greatly reduced, and the calculation speed and efficiency are improved; and then, a new solving method of the local coordinates of the projection points is adopted to replace the traditional Newton-Laplacian iterative algorithm, and the new solving method converts the calculation formula of the local coordinates of the projection points into a solution one-dimensional quadratic equation set, so that the calculation speed and efficiency of the local coordinates of the projection points are greatly increased, a non-iterative calculation method is realized, and the robustness of the contact collision analysis method is improved.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a block diagram of the process flow of the present invention.
Detailed Description
As shown in FIG. 1, the invention relates to a contact collision analysis method for aviation structure impact analysis, which comprises the following steps:
step one, constructing a contact surface of a finite element model of an aeronautical structure;
establishing an aeronautical structure finite element model, carrying out grid division on the aeronautical structure finite element model, wherein the grids are hexahedral grids, classifying the surfaces of all the hexahedral grids in the aeronautical structure finite element model, and when one surface is only the surface of one hexahedral grid, the surface is an external surface, otherwise, the surface is an internal surface; joining all external surfaces together to form a contact surface;
step two, determining a main cell surface contacted by the slave node n:
step 201, recording any node in a given impact discrete source finite element node set as a slave node n, recording the external surface as a main unit surface, and recording the node forming the main unit surface as a main node; in LS-Dyna, a segment-based bucket classification searching method is adopted, all main nodes contacting the surface are placed in each bucket in a classification mode, and the bucket where a slave node n is located is determined according to the spatial position of the slave node n;
step 202, searching a bucket where the slave node n is located and a master node in a bucket adjacent to the bucket by using a local search algorithm, determining the master node closest to the slave node n, selecting a master unit surface contacted by the slave node n from all master unit surfaces related to the master node closest to the slave node n, and recording the master unit surface as a master unit surface S;
in the present embodiment, the manner of selecting the main cell plane contacted by the slave node n is the same as the manner of selecting the main cell plane contacted by the slave node n in the symmetric penalty function method.
It should be noted that the main unit surface is a quadrilateral surface, and the main nodes are four corner points of the quadrilateral surface.
It should be noted that the contact search step in the second step is an improvement of the contact search step in a symmetric penalty function method, and the symmetric penalty function method needs to calculate the distances between the slave node n and all the master nodes in the contact surface, so as to select the master node closest to the slave node n, which is time-consuming; in the embodiment, a segment-based bucket classification search method is adopted, all nodes of a contact surface are placed in each bucket according to spatial positions, and for a slave node n in a two-dimensional bucket, only the current bucket and master nodes in 8 buckets around the current bucket are searched; three-dimensional, the current bucket and the main nodes in 26 buckets around the current bucket need to be searched, and the calculation amount is greatly reduced;
step three, calculating the local coordinates of the projection point c of the slave node n on the main unit surface S:
step 301, determining a plane with the smallest included angle with the main unit plane S in the XOY, XOZ and YOZ planes of the natural coordinate system as a target projection plane;
step 302, recording the coordinates of the projection point of the slave node n on the target projection plane as
The coordinates of the projection points of the four master nodes of the master unit plane S on the target projection plane are recorded as
Where i is the number of the four master nodes of the master unit plane S, i =1,2,3, 4;
303, according to the formula
Calculating local coordinates of a projected point c of the slave node n on the main unit plane S
(ii) a Wherein the content of the first and second substances,
is a two-dimensional geometric interpolation shape function,
coordinates of a main node with the number i on the main unit surface S in a natural coordinate system are set;
it should be noted that, in the existing symmetric penalty function method, a newton-raphson iteration method needs to be used for solving the local coordinates of the projection point c of the slave node n on the main unit plane S, but the newton-raphson iteration method needs to give a reasonable initial value, and a problem of non-convergence may occur when the newton-raphson iteration method is used for solving the coordinates of the projection point, that is, the coordinates of the projection point cannot be obtained; therefore, the problem is solved by adopting the calculation method in the third step, iteration is not needed, and the calculation time is greatly shortened.
It should be noted that, assuming that a plane having the smallest angle with respect to the main cell plane S is the plane XOY,
equation set of step 303
Can obtain a relation
A system of one-dimensional quadratic equations of (a),solving the system of quadratic equations in one unit based on
To obtain
The unique solution of (a) is determined,
the solution process of (2) is similar.
It should be noted that, in the following description,
step four, judging whether the slave node n penetrates through the main unit surface S according to the distance vector from the slave node n to the projection point c:
when the distance vector from the node n to the projection point c is not less than 0, the slave node n does not penetrate the main cell plane S, that is, the slave node n does not generate a contact collision;
when the distance vector from the node n to the projection point c is less than 0, the slave node n penetrates through the main unit surface S, and step five is executed;
and fifthly, applying normal contact force and friction force between the slave node n and the projection point c by adopting a penalty function method, and carrying out dynamic analysis on the finite element model of the aeronautical structure.
In the present embodiment, after determining that the slave node n does not penetrate the master cell plane S, the processing of the slave node n is ended, and search analysis of the next slave node is started;
in this embodiment, after the fifth step is performed, the finite element model of the aeronautical structure is changed, at this time, the original contact surface fails, and the contact surface needs to be reconstructed according to the first step, so as to implement periodic reconstruction of the contact surface.
All the main nodes of the contact surface are placed in each bucket in a classified mode, then contact search is conducted on the bucket where the slave node n is located and the main nodes in the buckets adjacent to the bucket, the calculation amount in the existing global search method is greatly reduced, and the calculation speed and efficiency are improved; and then, a new solution method of the local coordinates of the projection points is adopted to replace the traditional Newton-Lapson iterative algorithm, and the new solution method converts the calculation formula of the local coordinates of the projection points into a solution unitary quadratic equation set, so that the calculation speed and efficiency of the local coordinates of the projection points are greatly increased, a non-iterative calculation method is realized, and the robustness of the contact collision analysis method is improved.
In this embodiment, in step 201, in the segment-based bucket classification search method, the method for determining the length and the number of buckets is as follows:
s1, obtaining the diagonal length of all main unit faces of the contact surface, and making the length of the bucket
1/2 which is the longest diagonal length among the diagonals of all the main unit faces;
s2, obtaining the coordinates of the central points of all the main unit surfaces of the touch surface, and screening to obtain the maximum value of the coordinates of the central points of all the main unit surfaces
、
、
And minimum value
、
、
；
According to the formula
Calculating the number of buckets
(ii) a Wherein the content of the first and second substances,
、
、
the number of the pockets distributed in three directions of the overall coordinate system is shown.
Note that, by defining the length of the pocket, it is ensured that the number of the length of the pocket is more than 2 times the number of all the main cell faces of the contact surface.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (2)
1. A contact crash analysis method for aeronautical structure impact analysis, characterized in that it comprises the following steps:
step one, constructing a contact surface of a finite element model of an aeronautical structure;
establishing an aeronautical structure finite element model, carrying out grid division on the aeronautical structure finite element model, wherein the grids are hexahedral grids, classifying the surfaces of all the hexahedral grids in the aeronautical structure finite element model, and when one surface is only the surface of one hexahedral grid, the surface is an external surface, otherwise, the surface is an internal surface; joining all external surfaces together to form a contact surface;
step two, determining a main cell surface contacted by the slave node n:
step 201, recording any node in a given impact discrete source finite element node set as a slave node n, recording the external surface as a main unit surface, and recording the node forming the main unit surface as a main node; in LS-Dyna, a segment-based bucket classification searching method is adopted, all main nodes contacting the surface are placed in each bucket in a classification mode, and the bucket where a slave node n is located is determined according to the spatial position of the slave node n;
step 202, searching a bucket where the slave node n is located and a master node in a bucket adjacent to the bucket by using a local search algorithm, determining the master node closest to the slave node n, selecting a master unit surface contacted by the slave node n from all master unit surfaces related to the master node closest to the slave node n, and recording the master unit surface as a master unit surface S;
step three, calculating the local coordinates of the projection point c of the slave node n on the main unit surface S:
step 301, determining a plane with the smallest included angle with the main unit plane S in the XOY, XOZ and YOZ planes of the natural coordinate system as a target projection plane;
step 302, recording the coordinates of the projection point of the slave node n on the target projection plane as
The coordinates of the projection points of the four master nodes of the master unit plane S on the target projection plane are recorded as
Where i is the number of the four master nodes of the master unit plane S, i =1,2,3, 4;
303, according to the formula
Calculating local coordinates of a projected point c of the slave node n on the main unit plane S
(ii) a Wherein the content of the first and second substances,
is a two-dimensional geometric interpolation shape function,
coordinates of a main node with the number i on the main unit surface S in a natural coordinate system are set;
step four, judging whether the slave node n penetrates through the main unit surface S according to the distance vector from the slave node n to the projection point c:
when the distance vector from the node n to the projection point c is not less than 0, the slave node n does not penetrate the main cell plane S, that is, the slave node n does not generate a contact collision;
when the distance vector from the node n to the projection point c is less than 0, the slave node n penetrates through the main unit surface S, and step five is executed;
and fifthly, applying normal contact force and friction force between the slave node n and the projection point c by adopting a penalty function method, and carrying out dynamic analysis on the finite element model of the aeronautical structure.
2. The contact crash analysis method for aeronautical structural impact analysis according to claim 1, characterized in that: in step 201, in the segment-based bucket classification search method, the method for determining the length and the number of buckets is as follows:
s1, obtaining the diagonal lengths of all main cell faces of the contact surface, making the length of the pocket
1/2 which is the longest diagonal length among the diagonals of all the main unit faces;
s2, obtaining the coordinates of the center points of all the main unit surfaces of the touch surface, and screening to obtain the maximum value of the coordinates of the center points of all the main unit surfaces
、
、
And minimum value
、
、
；
According to the formula
Calculating the number of buckets
(ii) a Wherein the content of the first and second substances,
、
、
the number of the pockets distributed in three directions of the overall coordinate system is shown.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210829748.7A CN114896710B (en) | 2022-07-15 | 2022-07-15 | Contact collision analysis method for aviation structure impact analysis |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210829748.7A CN114896710B (en) | 2022-07-15 | 2022-07-15 | Contact collision analysis method for aviation structure impact analysis |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114896710A true CN114896710A (en) | 2022-08-12 |
| CN114896710B CN114896710B (en) | 2022-10-28 |
Family
ID=82729616
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210829748.7A Active CN114896710B (en) | 2022-07-15 | 2022-07-15 | Contact collision analysis method for aviation structure impact analysis |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114896710B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2007258684A1 (en) * | 2006-06-08 | 2007-12-21 | Ccc Information Services Inc. | Method and apparatus for obtaining photogrammetric data to estimate impact severity |
| CN101882168A (en) * | 2009-05-06 | 2010-11-10 | 利弗莫尔软件技术公司 | Be used at finite element analysis simulating beam and the surperficial method and system that contacts |
| CN107515982A (en) * | 2017-08-22 | 2017-12-26 | 电子科技大学 | A kind of contact analysis method in three-dimensional mechanical finite element modal analysis |
| US20180285502A1 (en) * | 2014-05-27 | 2018-10-04 | Livermore Software Technology Corporation | Dynamically-Positioned Search Domain Used In Numerical Simulation Of An Impact Event Between Two Objects |
| CN109726477A (en) * | 2018-12-29 | 2019-05-07 | 华中科技大学 | A kind of gap revolute pair finite element modeling and analysis method |
| US20210103685A1 (en) * | 2016-10-31 | 2021-04-08 | Siemens Product Lifecycle Management Software Inc. | System and method for element quality improvement in 3d quadrilateral-dominant surface meshes |
| CN112685942A (en) * | 2020-12-31 | 2021-04-20 | 华南理工大学 | Method for rapidly dividing finite element grids of complex tread patterns |
-
2022
- 2022-07-15 CN CN202210829748.7A patent/CN114896710B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2007258684A1 (en) * | 2006-06-08 | 2007-12-21 | Ccc Information Services Inc. | Method and apparatus for obtaining photogrammetric data to estimate impact severity |
| CN101882168A (en) * | 2009-05-06 | 2010-11-10 | 利弗莫尔软件技术公司 | Be used at finite element analysis simulating beam and the surperficial method and system that contacts |
| US20100286966A1 (en) * | 2009-05-06 | 2010-11-11 | Livermore Software Technology Corporation | methods and systems for simulating beam-to-surface contacts in finite element analysis |
| US20180285502A1 (en) * | 2014-05-27 | 2018-10-04 | Livermore Software Technology Corporation | Dynamically-Positioned Search Domain Used In Numerical Simulation Of An Impact Event Between Two Objects |
| US20210103685A1 (en) * | 2016-10-31 | 2021-04-08 | Siemens Product Lifecycle Management Software Inc. | System and method for element quality improvement in 3d quadrilateral-dominant surface meshes |
| CN107515982A (en) * | 2017-08-22 | 2017-12-26 | 电子科技大学 | A kind of contact analysis method in three-dimensional mechanical finite element modal analysis |
| CN109726477A (en) * | 2018-12-29 | 2019-05-07 | 华中科技大学 | A kind of gap revolute pair finite element modeling and analysis method |
| CN112685942A (en) * | 2020-12-31 | 2021-04-20 | 华南理工大学 | Method for rapidly dividing finite element grids of complex tread patterns |
Non-Patent Citations (5)
| Title |
|---|
| JINGJING XU 等: "A Pseudo-Distance Algorithm for Collision Detection of Manipulators Using Convex-Plane-Polygons-based Representation", 《ROBOTICS AND COMPUTER INTEGRATED MANUFACTURING》 * |
| 刁斌: "飞机风挡鸟撞有限元模拟及撞击影响分析", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 赵国群 等: "六面体网格自动划分和再划分算法", 《机械工程学报》 * |
| 赵海鸥 编: "《LS-DYNA动力分析指南》", 30 September 2003, 兵器工业出版社 * |
| 雷正保 编: "《汽车覆盖件冲压成形CAE技术》", 31 May 2003, 国防科技大学出版社 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114896710B (en) | 2022-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103020342B (en) | Method for extracting contour and corner of building from ground LiDAR data | |
| CN102306396B (en) | Three-dimensional entity model surface finite element mesh automatic generation method | |
| Sitaraman et al. | Parallel domain connectivity algorithm for unsteady flow computations using overlapping and adaptive grids | |
| AU2007208111B2 (en) | Sector meshing and neighbor searching for object interaction simulation | |
| CN113487730B (en) | Urban three-dimensional automatic modeling method based on laser radar point cloud data | |
| CN103871102B (en) | A kind of road three-dimensional fine modeling method based on elevational point and road profile face | |
| CN105022865A (en) | STL model Boolean calculation based method for extracting inner surface model of fuel tank in airplane | |
| CN103838852A (en) | Method for rapidly searching for multi-block structured grid docking relations | |
| CN108845358B (en) | Tomography and the recognition methods of structural anomaly body and device | |
| CN103439698A (en) | Method for obtaining radar scattering area | |
| Pandya et al. | Accuracy, Scalability, and Efficiency of Mixed-Element USM3D for Benchmark Three-Dimensional Flows | |
| AU2007208110B2 (en) | Object discretization to particles for computer simulation and analysis | |
| Ishikawa et al. | Near Field Sonic Boom Simulations for C608 Airplane of the Third AIAA SPW by Unstructured/Structured Overset Grid Method | |
| CN114896710B (en) | Contact collision analysis method for aviation structure impact analysis | |
| Ball | A free-Lagrange method for unsteady compressible flow: simulation of a confined cylindrical blast wave | |
| Saito et al. | Development and application of high-resolution adaptive numerical techniques in Shock Wave Research Center | |
| Langbein et al. | An efficient point location method for visualization in large unstructured grids. | |
| CN111046542B (en) | Method for evaluating LE grid computing characteristics of icosahedron and dispersion method | |
| Kirz | Surrogate-Based Low-Boom Low-Drag Nose Design for the JAXA S4 Supersonic Airliner | |
| Kirz et al. | DLR Simulations of the First AIAA Sonic Boom Prediction Workshop Cases | |
| Kang et al. | Research on constructing DEM with point cloud filtering algorithm considering special terrain | |
| Bedregal et al. | A study on size-optimal longest edge refinement algorithms | |
| Zhuo | Application of BIM technology in airport topographical design | |
| CN116882255B (en) | Method and system for randomly generating porous medium model based on Fourier series | |
| Qian et al. | Surface region recurrence pick-up algorithm research based on STL model |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |