CN107527385B - Automatic grid projection method - Google Patents
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- CN107527385B CN107527385B CN201710648144.1A CN201710648144A CN107527385B CN 107527385 B CN107527385 B CN 107527385B CN 201710648144 A CN201710648144 A CN 201710648144A CN 107527385 B CN107527385 B CN 107527385B
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- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
- G06T17/20—Finite element generation, e.g. wire-frame surface description, tesselation
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- G06F30/17—Mechanical parametric or variational design
Abstract
The invention mainly belongs to the technical field of aviation design, and particularly relates to an automatic grid projection method, which automatically projects grids of a slave component onto a geometric surface of a master component so as to capture the influence of a geometric boundary of the master component on a flow field of the slave component; the main components include a fuselage main component and a wing main component, and the wing main component includes a wing geometric upper surface and a wing geometric lower surface. The method can perform automatic grid projection aiming at the automatically generated nested structured grid, and the technology is closely dependent on the generated grid form, namely corresponding automatic grid projection modes are completely different aiming at different models and different grid generation methods.
Description
Technical Field
The invention mainly belongs to the technical field of aviation design, and particularly relates to an automatic grid projection method, which is an automatic projection technology suitable for a flow field computing grid, is an auxiliary technology for a nested grid technology, and can be applied to pneumatic optimization design.
Background
For the overall aerodynamic design of an airplane, one basic element is to perform rapid and accurate flow field characteristic analysis on various different configuration schemes of the airplane. With the continuous development of Computational Fluid Dynamics (CFD) technology, a plurality of commercial mature software are widely applied to the engineering practice of airplane design, but most of the software needs to read in a computational grid established by third-party grid generation software before flow field analysis, and the establishment of a set of high-quality grids usually takes a long time. In addition, deformation processing, such as pneumatic optimization design, aeroelastic analysis and the like, is often required for the grids in engineering applications, and the deformation of the grids often requires manual processing, and is complex in operation and low in automation degree. In addition, the grid deformation technology can cause phenomena such as grid distortion, grid shearing and the like, and the flow field calculation precision is seriously influenced.
In order to avoid these problems, a mesh automatic generation technology is developed, that is, a parameterization method is adopted to describe the geometric shape of the airplane, and then a flow field calculation mesh is automatically divided. Therefore, the grids of different airplane configurations can be established only by changing related grid parameters, and the method has the characteristic of high automation degree, which is very important for the field related to the optimization design. However, for complex aircraft, such as wing-body assemblies, it is difficult to automatically generate a grid in a uniform manner due to the disparate geometries of the various components. For structured grids, it is also necessary to ensure good fitness and orthogonality, otherwise flow field calculation accuracy is severely affected.
To address this problem, nested computational grids (e.g., fuselage and wing networks) can be generated relatively independently from the geometric features of the different components. However, the nested grid technology has a serious defect in processing the circumfluence of the intersected object, and the grid of the slave component and the object plane of the master component have a certain gap, so that the influence of the boundary of the object plane of the master component on the flow field of the slave component cannot be captured (as shown in fig. 1).
The existing methods for solving the problem of the geometric intersection of multiple parts of the nested grid can be divided into three categories:
the first type is that strictly orthogonal structured grids are directly generated aiming at the geometry of each part, sub-part grids are nested in the main part, projection processing is not carried out on a gap area, the grids do not have the body-attaching property and cannot reflect the influence of the object surface boundary of the main part on the flow field of the sub-part, and the flow field solving calculation accuracy is poor by adopting the grids.
The second type is to artificially divide the corresponding skin orthogonal structured grid according to the geometry of each part. And for the geometric connection area of the two components, projecting the grids of the slave components onto the geometric surface of the master component by adopting a manual dividing method. Such grids are good in quality, but low in automation degree and difficult in grid deformation.
And the third type is that a body-fitted orthogonal grid is automatically generated aiming at each part geometry, but the master part grid geometry is taken as a reference frame when the slave part grid is established, so that the established slave part grid is ensured to be directly fitted with the master part geometric surface. The grid has good quality and high automation degree, but has small application range, can not flexibly process various complex part connection relations, and the subordinate grids can not be independently established and must be supported by the main part.
Disclosure of Invention
In view of the above technical problems, the present invention provides an automatic mesh projection method, which can automatically project a mesh of a slave onto a geometric surface of a master to capture the influence of the geometric boundary of the master on the flow field of the slave.
The invention is realized by the following technical scheme:
a mesh auto-projection method that automatically projects a mesh of a slave component onto a master component geometric surface to capture the effect of master component geometric boundaries on a slave component flow field; the main components include a fuselage main component and a wing main component, and the wing main component includes a wing geometric upper surface and a wing geometric lower surface.
Further, the method specifically comprises the following steps:
judging the type of a main component corresponding to a slave component according to the position relation between the slave component and the main component and the grid form of the main component;
projecting the grid of slave components onto the geometric surface of their corresponding master component;
and checking the accuracy of the grid projection points.
Further, projecting the grid of the slave component onto the geometric surface of the corresponding master component specifically includes:
when the main component corresponding to the slave component is a main component of the machine body, transforming the slave component grid to a machine body grid coordinate system to obtain a slave component transformation grid, and projecting the slave component transformation grid to the geometric surface of the machine body of the main component;
when the main part corresponding to the slave part is the geometrical upper surface of the wing, projecting the slave part grid to the geometrical upper surface of the wing;
and when the main part corresponding to the slave part is the geometrical lower surface of the wing, projecting the slave part grid to the geometrical lower surface of the wing.
Further, when the master component corresponding to the slave component is the main component of the body, the method for transforming the slave component grid to the coordinate system of the body grid comprises the following steps:
(1) positioning a geometric section of the fuselage and a section origin position o corresponding to a point p according to an x coordinate value of any point p in the grid of the slave component;
(2) calculating an included angle phi between a connecting line of the point p and the point o and the horizontal axis;
(3) according to the position of the p point, finding out a geometric surface point s of the slave component corresponding to the p point according to the grid generation relation, and calculating the length r from the point s to the point o;
(4) using r as radius, positioning a point p on the connection line of point p and point o along the included angle phi direction0A 1 is to p0The point is taken as the coordinate position of the point p in the body coordinate system;
(5) and (4) repeating the steps (1) to (4), and transforming the slave component grids to the airframe grid coordinate system to obtain slave component transformation grids.
Further, when the main component corresponding to the slave component is a main component of the body, transforming the grid of the slave component into a coordinate system of the grid of the body, and then projecting the transformed grid of the slave component onto the geometric surface of the body of the main component, the method comprises the following steps:
(1) transforming any point p on the cross-section of the grid for the secondary part closest to the geometric surface of the main part of the fuselage1Find p1Adjacent grid points p in the direction of the fuselage geometry outside normal2；
(2) With p1And p2Two points are connected to search the intersecting position p of the connecting line and all the surface grid cells of the fuselage3Point;
(3) sequentially judging all intersecting positions p3Whether the point is located inside a quadrangle formed by four vertexes of the corresponding surface mesh unit; if a certain intersecting position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as a subordinate component to transform p on the grid1Point on the geometric surface of the main part bodyGrid projection points.
(4) And (4) repeating the steps (1) to (3), and projecting the transformation grids of the slave components transformed into the coordinate system of the airframe grid onto the geometric surface of the main component airframe.
Further, when the main component corresponding to the slave component is the geometrical upper surface of the wing, projecting the slave component mesh onto the geometrical upper surface of the wing, specifically:
(1) for any point p on the cross section of the grid of the secondary member closest to the geometric surface of the primary member of the wing1Find p1Points are adjacent grid points p along the direction of the outer normal of the geometrical surface of the wing2；
(2) With p1And p2Two points are connected, and the connection line is judged to be intersected with the geometric upper surface or the geometric lower surface of the wing;
(3) if the connection line intersects with the geometrical upper surface of the wing, searching the intersection position p of the connection line and all surface grid cells of the geometrical upper surface of the wing3Point;
(4) sequentially judging all cross positions p3Whether the point is positioned in a quadrangle formed by four vertexes formed by the corresponding surface mesh unit or not; if a certain cross-over position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as p on the grid of the subordinate component1Grid projection points which are points on the geometric upper surface of the wing;
(5) and (5) repeating the steps (1) to (4) to project the slave component grid to the geometrical upper surface of the wing.
Further, when the main component corresponding to the slave component is the geometrical lower surface of the wing, projecting the slave component mesh onto the geometrical upper surface of the wing, specifically:
(1) for any point p on the cross section of the grid of the secondary member closest to the geometric surface of the primary member of the wing1Find p1Points are adjacent grid points p along the direction of the outer normal of the geometrical surface of the wing2；
(2) With p1And p2Two points are connected to judge whether the connection line is intersected with the geometric upper surface or the geometric lower surface of the wing；
(3) If the connection line intersects with the lower geometric surface of the wing, searching the intersection position p of the connection line and all surface grid cells of the lower geometric surface of the wing3Point;
(4) sequentially judging all cross positions p3Whether the point is positioned in a quadrangle formed by four vertexes formed by the corresponding surface mesh unit or not; if a certain cross-over position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as p on the grid of the subordinate component1Grid projection points which are points on the geometric lower surface of the wing;
(5) and (4) repeating the steps (1) to (4) and projecting the slave component grids to the geometrical lower surface of the wing.
Further, the accuracy of the grid projection points is verified, and the method is suitable for verifying whether the projection points projected to the geometric surface of the corresponding main component by the slave component grids can be used as accurate grid projection points.
Further, the specific verification method comprises the following steps:
(1) calculating the quadrilateral area S formed by four vertexes of the surface mesh unit a, b, c and dabcd；
(2) Sequentially calculating the area S of a triangle formed by the projection point p and any two adjacent points of the quadrangleapb,Sbpc,Scpd,Sdpa；
(3) Judgment Sapb+Sbpc+Scpd+Sdpa-SabcdWhether the value of (d) is less than a threshold fractional amount;
(4) if Sapb+Sbpc+Scpd+Sdpa-SabcdIf the value of (2) is less than the threshold value, the point is determined to be an accurate grid projection point.
The specific checking method comprises the following steps:
(1) calculating the quadrilateral area S formed by four vertexes of the surface mesh unit a, b, c and dabcd；
(2) Sequentially calculating the area S of a triangle formed by the projection point p and any two adjacent points of the quadrangleapb,Sbpc,Scpd,Sdpa；
(3) Judgment Sapb+Sbpc+Scpd+Sdpa-SabcdWhether the value of (d) is less than a threshold fractional amount;
(4) if Sapb+Sbpc+Scpd+Sdpa-SabcdIf the value of (2) is less than the threshold value, the point is determined to be an accurate grid projection point.
The invention has the beneficial technical effects that:
the method can perform automatic grid projection aiming at the automatically generated nested structured grid, and the technology is closely dependent on the generated grid form, namely aiming at different models and different grid generation methods, the corresponding automatic grid projection modes are completely different.
Compared with the prior art which needs to manually divide the structured projection grid, the method can automatically project the slave component grid to the geometric surface of the master component.
Drawings
FIG. 1 is a schematic diagram of a slave component flow field failing to capture a master component object plane boundary condition in a prior art nested grid;
FIG. 2 is a flow chart of a method for automatic projection of a grid according to the present invention;
FIG. 3 is a schematic representation of transforming a grid of dependent components to a fuselage coordinate system;
FIG. 4 is a schematic illustration of a method of projecting a grid of secondary components onto a fuselage when the primary component is the fuselage;
FIG. 5 is a schematic illustration of a method of projecting a grid of secondary components onto a primary component of a wing when the primary component is a wing;
fig. 6 is a schematic diagram of a grid proxel verification method in the method of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
On the contrary, the invention is intended to cover alternatives, modifications, equivalents and alternatives which may be included within the spirit and scope of the invention as defined by the appended claims. Furthermore, in the following detailed description of the present invention, certain specific details are set forth in order to provide a better understanding of the present invention. It will be apparent to one skilled in the art that the present invention may be practiced without these specific details.
Examples
A mesh auto-projection method that automatically projects a mesh of a slave component onto a master component geometric surface to capture the effect of master component geometric boundaries on a slave component flow field; the main components include a fuselage main component and a wing main component, and the wing main component includes a wing geometric upper surface and a wing geometric lower surface.
The method specifically comprises the following steps (as shown in figure 2):
judging the type of a main component corresponding to a slave component according to the position relation between the slave component and the main component and the grid form of the main component;
projecting the grid of slave components onto the geometric surface of the master component to which it corresponds;
and checking the accuracy of the grid projection points.
Wherein, projecting the slave component mesh onto the geometric surface of the master component corresponding thereto specifically is:
1. when the main part corresponding to the slave part is a main part of the fuselage, considering that the form of the master part is composed of a series of similar-circle geometric sections from the nose to the tail, and has the characteristic of narrow and long, the grid is difficult to be directly projected on the geometric surface of the master part, therefore, before projection, the grid of the slave part needs to be converted into a coordinate system of the grid of the fuselage, and in this case, the slave part comprises a main wing, a canard wing, a horizontal tail wing, a vertical tail wing and the like.
The method for transforming the grid of the slave components to the coordinate system of the fuselage grid is as follows (as shown in fig. 3):
(1) positioning a geometric section of the fuselage and a section origin position o corresponding to a point p according to an x coordinate value of any point p in the grid of the slave component;
(2) calculating an included angle phi between a connecting line of the point p and the point o and the horizontal axis;
(3) according to the position of the p point, finding out a geometric surface point s of the slave component corresponding to the p point according to the grid generation relation, and calculating the length r from the point s to the point o;
(4) using r as radius, positioning a point p on the connection line of point p and point o along the included angle phi direction0A 1 is to p0The point is taken as the coordinate position of the point p in the body coordinate system;
(5) and (4) repeating the steps (1) to (4), and transforming the slave component grids to the airframe grid coordinate system to obtain slave component transformation grids.
When the main component corresponding to the slave component is a main component of the body, transforming the slave component grid into a body grid coordinate system to obtain a slave component transformation grid, and then projecting the slave component transformation grid onto the geometric surface of the body of the main component (as shown in fig. 4):
(1) transforming any point p on the cross-section of the grid for the secondary part closest to the geometric surface of the main part of the fuselage1Find p1Adjacent grid points p in the direction of the fuselage geometry outside normal2；
(2) With p1And p2Two points are connected to search the intersecting position p of the connecting line and all the surface grid cells of the fuselage3Point;
(3) sequentially judging all intersecting positions p3Whether the point is located inside a quadrangle formed by four vertexes of the corresponding surface mesh unit; if a certain intersecting position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as a subordinate component to transform p on the grid1The points are projected as a grid on the geometric surface of the main part body.
(4) And (4) repeating the steps (1) to (3), and projecting the transformation grids of the slave components transformed into the coordinate system of the airframe grid onto the geometric surface of the main component airframe.
2. When the main part is a wing, because the shape is prolate, firstly, the projection position needs to be judged on the geometrical upper surface or the geometrical lower surface of the wing, and then, the grid projection is carried out, and the specific method is as follows (fig. 5):
when the main part corresponding to the slave part is the geometrical upper surface of the wing, projecting the slave part grid to the geometrical upper surface of the wing; in this case, the subordinate components include a vertical tail, a wing body fusion layout veener, a pylon, and the like.
The method specifically comprises the following steps:
(1) for any point p on the cross section of the grid of the secondary member closest to the geometric surface of the primary member of the wing1Find p1Points are adjacent grid points p along the direction of the outer normal of the geometrical surface of the wing2；
(2) With p1And p2Two points are connected, and the connection line is judged to be intersected with the geometric upper surface or the geometric lower surface of the wing;
(3) if the connection line intersects with the geometrical upper surface of the wing, searching the intersection position p of the connection line and all surface grid cells of the geometrical upper surface of the wing3Point;
(4) sequentially judging all cross positions p3Whether the point is positioned in a quadrangle formed by four vertexes formed by the corresponding surface mesh unit or not; if a certain cross-over position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as p on the grid of the subordinate component1Grid projection points which are points on the geometric upper surface of the wing;
(5) and (5) repeating the steps (1) to (4) to project the slave component grid to the geometrical upper surface of the wing.
And when the main part corresponding to the slave part is the geometrical lower surface of the wing, projecting the slave part grid to the geometrical lower surface of the wing, wherein the slave part comprises a tail fin, a pylon and the like. The method specifically comprises the following steps:
(1) for any point p on the cross section of the grid of the secondary member closest to the geometric surface of the primary member of the wing1Find p1Points are adjacent grid points p along the direction of the outer normal of the geometrical surface of the wing2；
(2) With p1And p2Two points are connected, and the connection line is judged to be intersected with the geometric upper surface or the geometric lower surface of the wing;
(3) if the connection line intersects with the lower geometric surface of the wing, searching the intersection position p of the connection line and all surface grid cells of the lower geometric surface of the wing3Point;
(4) sequentially judging all cross positions p3Whether the point is positioned in a quadrangle formed by four vertexes formed by the corresponding surface mesh unit or not; if a certain cross-over position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as p on the grid of the subordinate component1Grid projection points which are points on the geometric lower surface of the wing;
(5) and (4) repeating the steps (1) to (4) and projecting the slave component grids to the geometrical lower surface of the wing.
In addition, in this embodiment, the accuracy of the grid projection points is verified, and the method is suitable for verifying whether the projection points of the slave component grid projected onto the geometric surface of the corresponding master component can be used as accurate grid projection points;
the specific checking method comprises the following steps:
(1) calculating the quadrilateral area S formed by four vertexes of the surface mesh unit a, b, c and dabcd；
(2) Sequentially calculating the area S of a triangle formed by the projection point p and any two adjacent points of the quadrangleapb,Sbpc,Scpd,Sdpa；
(3) Judgment Sapb+Sbpc+Scpd+Sdpa-SabcdWhether the value of (d) is less than a threshold fractional amount;
(4) if Sapb+Sbpc+Scpd+Sdpa-SabcdIf the value of (2) is less than the threshold value, the point is determined to be an accurate grid projection point.
Claims (5)
1. A mesh automatic projection method is characterized in that the method automatically projects a slave component mesh onto a master component geometric surface to capture the influence of a master component geometric boundary on a slave component flow field; the main components comprise a fuselage main component and a wing main component, the wing main component comprises a wing geometric upper surface and a wing geometric lower surface, and the method specifically comprises the following steps:
judging the type of a main component corresponding to a slave component according to the position relation between the slave component and the main component and the grid form of the main component;
automatically projecting the grid of slave components onto the geometric surface of their corresponding master component;
the accuracy of the grid projection points is verified, the method is suitable for verifying whether the projection points projected to the geometric surface of the corresponding main component by the slave component grids can be used as accurate grid projection points,
the automatic projection of the slave component mesh onto the geometric surface of the corresponding master component is specifically as follows:
when the main component corresponding to the slave component is a main component of the machine body, transforming the slave component grid to a machine body grid coordinate system to obtain a slave component transformation grid, and projecting the slave component transformation grid to the geometric surface of the machine body of the main component;
when the main part corresponding to the slave part is the geometrical upper surface of the wing, projecting the slave part grid to the geometrical upper surface of the wing;
when the main part corresponding to the slave part is the geometrical lower surface of the wing, projecting the slave part grid to the geometrical lower surface of the wing,
the specific method for verifying the accuracy of the grid projection points comprises the following steps:
(1) calculating the quadrilateral area S formed by four vertexes of the surface mesh unit a, b, c and dabcd；
(2) Sequentially calculating the area S of a triangle formed by the projection point p and any two adjacent points of the quadrangleapb,Sbpc,Scpd,Sdpa；
(3) Judgment Sapb+Sbpc+Scpd+Sdpa-SabcdWhether the value of (d) is less than a threshold;
(4) if Sapb+Sbpc+Scpd+Sdpa-SabcdIf the value of (2) is less than the threshold value, the point is determined to be an accurate grid projection point.
2. The grid automatic projection method according to claim 1, wherein when the master component corresponding to the slave component is the main component of the body, the method for transforming the slave component grid to the coordinate system of the body grid comprises:
(1) positioning a geometric section of the fuselage and a section origin position o corresponding to a point p according to an x coordinate value of any point p in the grid of the slave component;
(2) calculating an included angle phi between a connecting line of the point p and the point o and the horizontal axis;
(3) according to the position of the p point, finding out a geometric surface point s of the slave component corresponding to the p point according to the grid generation relation, and calculating the length r from the point s to the point o;
(4) using r as radius, positioning a point p on the connection line of point p and point o along the included angle phi direction0A 1 is to p0The point is taken as the coordinate position of the point p in the body coordinate system;
(5) and (4) repeating the steps (1) to (4), and transforming the slave component grids to the airframe grid coordinate system to obtain slave component transformation grids.
3. The grid automatic projection method according to claim 1, wherein when the master component corresponding to the slave component is a main component of the body, the method for projecting the slave component transformation grid onto the geometric surface of the body of the master component after transforming the slave component grid into the coordinate system of the body grid comprises the following steps:
(1) transforming any point p on the cross-section of the grid for the secondary part closest to the geometric surface of the main part of the fuselage1Find p1Adjacent grid points p in the direction of the fuselage geometry outside normal2；
(2) With p1And p2Two points are connected to search the intersecting position p of the connecting line and all the surface grid cells of the fuselage3Point;
(3) sequentially judging all intersecting positions p3Whether the point is located inside a quadrangle formed by four vertexes of the corresponding surface mesh unit; if a certain intersecting position p3' Point is located in its corresponding tableWithin a quadrangle formed by four vertexes of a surface mesh unit, p3' Point as a subordinate component to transform p on the grid1Grid projection points of points on the geometric surface of the main part body;
(4) and (4) repeating the steps (1) to (3), and projecting the transformation grids of the slave components transformed into the coordinate system of the airframe grid onto the geometric surface of the main component airframe.
4. The method according to claim 1, wherein when the main component corresponding to the slave component is the geometrical upper surface of the airfoil, the projecting the slave component mesh onto the geometrical upper surface of the airfoil specifically comprises:
(1) for any point p on the grid section of the slave part closest to the geometric surface of the main part of the wing1Find p1Points are adjacent grid points p along the direction of the outer normal of the geometrical surface of the wing2；
(2) With p1And p2Two points are connected, and the connection line is judged to be intersected with the geometric upper surface or the geometric lower surface of the wing;
(3) if the connection line intersects with the geometrical upper surface of the wing, searching the intersection position p of the connection line and all surface grid cells of the geometrical upper surface of the wing3Point;
(4) sequentially judging all cross positions p3Whether the point is positioned in a quadrangle formed by four vertexes formed by the corresponding surface mesh unit or not; if a certain cross-over position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as p on the grid of the subordinate component1Grid projection points which are points on the geometric upper surface of the wing;
(5) and (5) repeating the steps (1) to (4) to project the slave component grid to the geometrical upper surface of the wing.
5. The method according to claim 1, wherein when the main component corresponding to the slave component is the lower geometrical surface of the airfoil, the method for projecting the slave component mesh onto the upper geometrical surface of the airfoil comprises:
(1) for any point p on the grid section of the slave part closest to the geometric surface of the main part of the wing1Find p1Points are adjacent grid points p along the direction of the outer normal of the geometrical surface of the wing2；
(2) With p1And p2Two points are connected, and the connection line is judged to be intersected with the geometric upper surface or the geometric lower surface of the wing;
(3) if the connection line intersects with the lower geometric surface of the wing, searching the intersection position p of the connection line and all surface grid cells of the lower geometric surface of the wing3Point;
(4) sequentially judging all cross positions p3Whether the point is positioned in a quadrangle formed by four vertexes formed by the corresponding surface mesh unit or not; if a certain cross-over position p3' points are located inside the quadrilateral formed by the four vertices of their corresponding surface mesh cells, p3' Point as p on the grid of the subordinate component1Grid projection points which are points on the geometric lower surface of the wing;
(5) and (4) repeating the steps (1) to (4) and projecting the slave component grids to the geometrical lower surface of the wing.
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| CN112231846B (en) * | 2020-11-04 | 2024-04-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Method, device, equipment and storage medium for generating and projecting airplane pylon grid |
| CN112347561A (en) * | 2020-11-10 | 2021-02-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Static aeroelasticity analysis method, device, equipment and storage medium of aircraft |
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| CN102306396A (en) * | 2011-09-15 | 2012-01-04 | 山东大学 | Three-dimensional entity model surface finite element mesh automatic generation method |
| CN104331584A (en) * | 2014-11-28 | 2015-02-04 | 北京航空航天大学 | Automatic boundary layer calculation-orientated two-dimensional hybrid grid generating method |
| CN106971043A (en) * | 2017-03-31 | 2017-07-21 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The method for building up and device of a kind of nested grid |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102306396A (en) * | 2011-09-15 | 2012-01-04 | 山东大学 | Three-dimensional entity model surface finite element mesh automatic generation method |
| CN104331584A (en) * | 2014-11-28 | 2015-02-04 | 北京航空航天大学 | Automatic boundary layer calculation-orientated two-dimensional hybrid grid generating method |
| CN106971043A (en) * | 2017-03-31 | 2017-07-21 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The method for building up and device of a kind of nested grid |
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