CN113849913B - Method and device for generating three-dimensional grid of axisymmetric vectoring nozzle - Google Patents
Method and device for generating three-dimensional grid of axisymmetric vectoring nozzle Download PDFInfo
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Abstract
The invention provides a method and a device for generating a three-dimensional grid of an axisymmetric vectoring nozzle, wherein the method comprises the following steps: determining geometric characteristics of the axisymmetric vectoring nozzle, and determining a control curve expression for restricting a calculation domain according to the geometric characteristics of the axisymmetric vectoring nozzle; determining a current vector deflection angle of the axisymmetric vector nozzle; determining a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression; and generating a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the three-dimensional grid distribution characteristics according to the preset three-dimensional grid distribution characteristics. According to the scheme, repeated calculation is not needed, and calculation is only needed by substituting the control curve expression, so that the generation speed is high, and the calculated amount is reduced.
Description
Technical Field
The embodiment of the invention relates to the technical field of vector propulsion, in particular to a method and a device for generating a three-dimensional grid of an axisymmetric vector spray pipe.
Background
The vector propulsion technology can provide good maneuvering performance for the fighter, so that the fighter is guaranteed to have stronger survivability in fight in the air and fight against, the vector propulsion technology is applied to four generations of machines such as F-22 and F-35 at present, and particularly F-35B has the capability of vertical lifting and hovering after being compatible with the vector propulsion technology, so that the fighter capability is greatly improved. The jet flow direction and the thrust of the engine can be dynamically and continuously adjusted by adopting vector thrust, so that the thrust requirement of the fighter plane can be flexibly met.
In the prior art, for simulating three-dimensional grids of the axisymmetric vectoring nozzle under different vectoring thrust states, for each deflection vector deflection angle of the axisymmetric vectoring nozzle, geometric model generating software of the axisymmetric vectoring nozzle is utilized to generate a geometric model of the axisymmetric vectoring nozzle corresponding to the vector deflection angle, and then grid generating software is utilized to generate corresponding three-dimensional grids for the geometric model.
The geometric model generation process and the three-dimensional grid generation process are repeated every time deflection, so that the repeated calculation amount is more.
Disclosure of Invention
The embodiment of the invention provides a method and a device for generating a three-dimensional grid of an axisymmetric vectoring nozzle, which can improve the generation speed of the three-dimensional grid and reduce the calculated amount in the generation process of the three-dimensional grid.
In a first aspect, an embodiment of the present invention provides a method for generating a three-dimensional grid of an axisymmetric vectoring nozzle, including:
determining geometric characteristics of the axisymmetric vectoring nozzle, and determining a control curve expression for restricting a calculation domain according to the geometric characteristics of the axisymmetric vectoring nozzle;
Determining a current vector deflection angle of the axisymmetric vector nozzle;
determining a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression;
And generating a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the three-dimensional grid distribution characteristics according to the preset three-dimensional grid distribution characteristics.
Preferably, the computational domain constrained by the control curve expression includes at least one of the following regions: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle, a first airflow flowing area, a second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle, a first air area of the outer wall surface of the axisymmetric vectoring nozzle and a second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle; the first airflow flow region is a region of the axisymmetric vectoring nozzle other than the boundary layer.
Preferably, the method comprises the steps of,
The computational domain constrained by the control curve expression includes: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle comprise: setting the number of layers of grid nodes of the boundary layer in the radial direction, the thickness of each layer of grid nodes, the number of each layer of grid nodes in the axial direction and the number of each layer of grid nodes in the circumferential direction; wherein the thickness of the boundary layer in the radial direction of the grid node gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second airflow flowing area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: stretching the distribution of the grid nodes on the second airflow flowing area along the vector deflection angle of the axisymmetric vector spray pipe, setting the extension distance in the direction of the vector deflection angle, wherein the extension distance is a set multiple of the outlet diameter of the axisymmetric vector spray pipe, and setting the number of the grid nodes in the direction of the vector deflection angle; the mesh nodes arranged on the second airflow flowing area are gradually increased in size in the circumferential direction, the radial direction and the axial direction in the stretching process;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: a first air region on the outer wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics set in advance on the first air area of the outer wall surface of the axisymmetric vectoring nozzle include: setting the number of the circumferential and axial three-dimensional grid nodes on the first air area to be the same as the number of the circumferential and axial three-dimensional grid nodes on the first air flow area; setting the number of grid nodes in the radial direction on the first air area, wherein the thickness of the grid nodes in the radial direction gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second air area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: setting the number of circumferential and axial grid nodes on the second air area to be the same as the number of circumferential and axial grid nodes on the second airflow flowing area; the number of grid nodes in the radial direction on the second air area is set, and the thickness of the grid nodes in the radial direction is gradually increased layer by layer.
Preferably, the method comprises the steps of,
The computational domain constrained by the control curve expression includes: the first airflow zone; the cross section of the first airflow flowing area is circular;
The three-dimensional grid distribution features previously set on the first airflow region include: dividing the first airflow zone into an inner zone including an axial center and an outer zone other than the inner zone; the cross section corresponding to the inner area is a polygon positioned in the circle; the grid nodes in the inner area and the outer area are evenly distributed.
Preferably, the polygon is square; and connecting the equally-divided points of the four equally-divided circumferences of the circles with the centers of the circles respectively to form line segments, and connecting the midpoints of the four line segments to obtain the square.
Preferably, the number of grid nodes on each side of the polygon is the same as the number of grid nodes on the boundary layer circumferential direction arc corresponding to the side.
Preferably, after generating the three-dimensional grid corresponding to the current vector deflection angle according to the three-dimensional grid distribution characteristics in the target computing domain, the method further comprises:
And generating a grid file corresponding to the current vector deflection angle according to coordinates of the vertex corresponding to each grid node in the generated three-dimensional grid.
In a second aspect, an embodiment of the present invention further provides a device for generating a three-dimensional grid of an axisymmetric vectoring nozzle, including:
The constraint unit is used for determining the geometric characteristics of the axisymmetric vectoring nozzle and determining a control curve expression for constraining a calculation domain according to the geometric characteristics of the axisymmetric vectoring nozzle;
the angle determining unit is used for determining the current vector deflection angle of the axisymmetric vector spray pipe;
A calculation domain determining unit, configured to determine a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression;
The three-dimensional grid generating unit is used for generating a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the three-dimensional grid distribution characteristics according to the preset three-dimensional grid distribution characteristics.
In a third aspect, an embodiment of the present invention further provides a computing device, including a memory and a processor, where the memory stores a computer program, and the processor implements a method according to any embodiment of the present specification when executing the computer program.
In a fourth aspect, embodiments of the present invention also provide a computer-readable storage medium having stored thereon a computer program which, when executed in a computer, causes the computer to perform a method according to any of the embodiments of the present specification.
The embodiment of the invention provides a method and a device for generating a three-dimensional grid of an axisymmetric vector spray pipe, wherein the axisymmetric vector spray pipe is in a working state, only the vector deflection angle is required to be adjusted, and other parameters are not changed, so that a control curve expression for restraining a calculation domain can be obtained according to the geometric characteristics of the axisymmetric vector spray pipe, the control curve expression is related to the vector deflection angle of the axisymmetric vector spray pipe, when the current vector deflection angle of the axisymmetric vector spray pipe is determined, the control curve expression is substituted, the target calculation domain of the three-dimensional grid required to be generated can be determined, and then the three-dimensional grid corresponding to the current vector deflection angle can be generated in the target calculation domain according to the preset three-dimensional grid distribution characteristics. Therefore, the scheme does not need repeated calculation, only needs substituting the control curve expression to calculate, and has the advantages of high generation speed and reduced calculation amount.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for generating a three-dimensional grid of an axisymmetric vectoring nozzle according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of a longitudinal section of an axisymmetric vectoring nozzle according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a computing domain according to an embodiment of the present invention;
FIG. 4 is a schematic illustration of a cross-section of an axisymmetric vectoring nozzle according to an embodiment of the present invention;
FIG. 5 is a schematic illustration of a cross-section of another axisymmetric vectoring nozzle provided in accordance with an embodiment of the present invention;
FIG. 6 is a schematic view of a three-dimensional grid provided in accordance with one embodiment of the present invention;
FIG. 7 is a hardware architecture diagram of a computing device according to one embodiment of the invention;
FIG. 8 is a schematic diagram of an apparatus for generating a three-dimensional grid of axisymmetric vectoring nozzles according to an embodiment of the present invention;
FIG. 9 is a block diagram of another apparatus for generating a three-dimensional grid of axisymmetric vectoring nozzles according to an embodiment of the present invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present invention are within the scope of protection of the present invention.
For the axisymmetric vectoring nozzle, the flow field in the working state of the axisymmetric vectoring nozzle can be simulated through a three-dimensional grid, and when the vectoring deflection angles of the axisymmetric vectoring nozzle are different, different vectoring thrust can be generated. The geometric shape of the axisymmetric vectoring nozzle changes every time the axisymmetric vectoring nozzle deflects by a different angle, and the flowing area of the ejected high-temperature airflow also changes, so that the calculation domain changes and the three-dimensional grid of the calculation domain also changes. In the prior art, each time the axisymmetric vectoring nozzle deflects, the geometric model of the axisymmetric vectoring nozzle needs to be regenerated, the three-dimensional grid is recalculated, and the repeated calculation amount is more.
Based on the method, if the geometric characteristics of the axisymmetric vectoring nozzle can be expressed in an expression mode, when the axisymmetric vectoring nozzle deflects by a vectoring deflection angle, the vectoring deflection angle is input into the expression to determine a calculation domain, and then a corresponding three-dimensional grid is generated in the calculation domain through a preset three-dimensional grid distribution rule, so that the geometric model of the axisymmetric vectoring nozzle does not need to be repeatedly generated, the calculation amount is greatly reduced, and the generation speed of the three-dimensional grid is improved.
Specific implementations of the above concepts are described below.
Referring to fig. 1, an embodiment of the present invention provides a method for generating a three-dimensional grid of an axisymmetric vectoring nozzle, which includes:
Step 100, determining geometric characteristics of the axisymmetric vectoring nozzle, and determining a control curve expression for restricting a calculation domain according to the geometric characteristics of the axisymmetric vectoring nozzle.
Step 102, determining the current vector deflection angle of the axisymmetric vector nozzle.
And 104, determining a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression.
And 106, generating a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the preset three-dimensional grid distribution characteristics and the three-dimensional grid distribution characteristics.
In the embodiment of the invention, as the axisymmetric vector spray pipe is only required to adjust the vector deflection angle in the working state, other parameters are not changed, a control curve expression for restraining a calculation domain can be obtained according to the geometric characteristics of the axisymmetric vector spray pipe, the control curve expression is related to the vector deflection angle of the axisymmetric vector spray pipe, when the current vector deflection angle of the axisymmetric vector spray pipe is determined, the control curve expression is substituted, the target calculation domain of a three-dimensional grid to be generated can be determined, and then the three-dimensional grid corresponding to the current vector deflection angle can be generated in the target calculation domain according to the preset three-dimensional grid distribution characteristics. Therefore, the scheme does not need repeated calculation, only needs substituting the control curve expression to calculate, and has the advantages of high generation speed and reduced calculation amount.
The manner in which the individual steps shown in fig. 1 are performed is described below.
Firstly, the geometric characteristics of the axisymmetric vectoring nozzle are determined according to the step 100 ', the control curve expression for restraining the calculation domain is determined according to the geometric characteristics of the axisymmetric vectoring nozzle, the current vector deflection angle of the axisymmetric vectoring nozzle is determined according to the step 102', and the target calculation domain corresponding to the current vector deflection angle is determined according to the current vector deflection angle and the control curve expression according to the step 104.
Referring to fig. 2, a schematic view of a longitudinal section of the axisymmetric vectoring nozzle is shown. Wherein, the axisymmetric vectoring nozzle comprises a straight section (with the length of A1 in fig. 2), a contracted section (with the length of A2 in fig. 2) and an expanded section (with the length of A3 in fig. 2), after determining the model of the axisymmetric vectoring nozzle, the geometric characteristics of the axisymmetric vectoring nozzle can be determined, and the geometric characteristics comprise: the cross-sectional areas at the inlet (diameter B1 in fig. 2), throat (diameter B2 in fig. 2) and outlet (diameter B2 in fig. 2), the lengths of the straight, converging and diverging sections, and the vector deflection angle of the diverging sections.
For example, the lengths of the straight section, the contracted section and the expanded section are respectively 0.7m, 0.6m and 0.5m, and the cross-sectional areas at the inlet, the throat and the outlet are respectively 0.8m 2、0.35m2、0.59m2.
Since the geometric characteristics are constant except for the change of the vector deflection angle (variable) of the expansion section, the geometric constraint of each region in the calculation domain can be controlled by adopting a corresponding mathematical function, so that a control curve expression for constraining the calculation domain is obtained. The control curve expression is related to the vector deflection angle of the expansion section, and after the vector deflection angle is determined, the vector deflection angle is substituted into the control area expression, so that a calculation domain corresponding to the vector deflection angle can be obtained.
It should be noted that, the control curve expression for constraining the calculation domain is a prior art, and is not described herein in detail.
Wherein the computational domain is the area where a three-dimensional mesh needs to be generated. The geometric characteristics of the axisymmetric vectoring nozzle determine the expansion state of the high-temperature airflow in the axisymmetric vectoring nozzle, and different expansion states correspond to different Mach numbers and boundary layer thicknesses.
In one embodiment of the invention, the computational domain constrained by the control curve expression may include at least one of the following regions: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle, the first airflow flowing area, the second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle, the first air area of the outer wall surface of the axisymmetric vectoring nozzle and the second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle; the first airflow flow region is a region of the axisymmetric vectoring nozzle other than the boundary layer.
Referring to fig. 3, a schematic diagram of a calculation domain is shown, in fig. 3, a solid line is a schematic longitudinal section of an axisymmetric vectoring nozzle, a region C1 formed by a dotted line and a solid line is a boundary layer of an inner wall surface of the axisymmetric vectoring nozzle, a region C2 formed by a dotted line is a first airflow flowing region, a region C3 formed by a dotted line is a second airflow flowing region corresponding to an outlet direction of the axisymmetric vectoring nozzle, a region C4 formed by a dotted line is a first air region of an outer wall surface of the axisymmetric vectoring nozzle, and a region C5 formed by a dotted line is a second air region corresponding to an outlet direction of the axisymmetric vectoring nozzle. The area D0 formed by the broken line and the solid line is a non-calculation domain.
In one embodiment of the present invention, in order to be able to generate a three-dimensional grid, three-dimensional grid distribution characteristics in the calculation domain need to be set in advance. For each region, since the airflow distribution rules corresponding to different regions are different, different three-dimensional grid distribution characteristics need to be set for each region.
The three-dimensional grid distribution characteristics set in each region are described below.
1. Boundary layer of inner wall surface of axisymmetric vectoring nozzle.
Since the true high temperature air stream has a non-negligible viscosity, there is a significant boundary layer phenomenon on the area near the inner wall of the axisymmetric vectoring nozzle. In order to accurately describe the gradient change of parameters such as the speed, the pressure and the like of the high-temperature air flow in the boundary layer, grid nodes in the boundary layer need to be set.
According to the distribution rule of the air flow in the boundary layer, the number of layers N 0 of grid nodes in the radial direction of the boundary layer, the thickness of each layer of grid nodes, the number of each layer of grid nodes in the axial direction N 1 and the number of each layer of grid nodes in the circumferential direction N 2 can be set; wherein the thickness of the boundary layer in the radial direction of the grid node increases layer by layer.
Preferably, in order to reduce the calculation amount, it is possible to set the thickness of the nth layer mesh node of the boundary layer in the radial direction to be a first multiple of the thickness of the (N-1) th layer mesh node, the first multiple being a value greater than 1; n is an integer greater than 1. It should be noted that, one layer of the boundary layer close to the inner wall of the axisymmetric vectoring nozzle is the first layer, and one layer of the boundary layer far away from the inner wall of the axisymmetric vectoring nozzle is the nth 0 layer.
The setting of the parameter values can be performed according to the parameter values in the geometric characteristics of the axisymmetric vectoring nozzle. Taking the above example of the values of the parameters in the axisymmetric vectoring nozzle geometry, then N 0 =10, and the thickness of the boundary layer at the first layer mesh node in the radial direction, H 1＝0.001m,N1＝100,N2 =80. The first multiple is 1.1 times.
The above-mentioned setting method of the thickness of each layer of mesh nodes is a preferable method, and other methods may be set besides the above-mentioned setting method, for example, the thickness of the second layer of mesh nodes is 1.1 times that of the first layer of mesh nodes, and the thickness of the third layer of mesh nodes is 1.2 times that of the second layer of mesh nodes, … …. It is only necessary to ensure that the thickness of the mesh nodes from the first layer to the N 0 th layer is gradually increased.
Referring to fig. 4, a left view is shown, the left view is a cross section of the axisymmetric vectoring nozzle, and since the axisymmetric vectoring nozzle is cylindrical, the cross section of the axisymmetric vectoring nozzle is circular, a circular area C1 in fig. 4 is a boundary layer, a square grid formed by dotted lines in the boundary layer is a filled grid, a circular area C2 is a first airflow flowing area, a solid double arrow E in fig. 4 is a circumferential direction, a solid double arrow F in fig. 4 is a radial direction, and a solid single arrow G in fig. 3 is an axial direction. The number of grid nodes in the circumferential direction is the number of grid nodes in the circumferential direction in fig. 4, and the number of grid nodes in the axial direction is the number of grid nodes in the length of A1+A2+A3 in fig. 2.
2. A first airflow flow region.
The distribution of grid nodes on the first airflow flow region needs to be set on the basis of the distribution of grid nodes of the boundary layer.
The inlet cross section (i.e., cross section) of the axisymmetric vectoring nozzle is circular and the cross section of the first airflow flow zone is circular after the boundary layer is removed in the torus region, please refer to the C2 region in fig. 4.
In one embodiment of the present invention, the three-dimensional grid distribution feature previously set on the first airflow zone includes: the grid nodes on the first airflow flowing region are uniformly distributed, and the number of the grid nodes of the first airflow flowing region in the circumferential direction/axial direction is consistent with the number of the grid nodes of the boundary layer in the circumferential direction/axial direction.
In order to increase the generation speed of the grid node in the first airflow flowing region, the first airflow flowing region may be divided into an inner region including the axis and an outer region other than the inner region; wherein the cross section corresponding to the inner area is a polygon positioned in the circle; the grid nodes in the inner and outer regions are evenly distributed. Since the cross section corresponding to the inner region is a polygon, when filling the mesh nodes into the polygonal region, the shape of the filled mesh nodes can be determined according to the shape of the polygon. For example, the polygon may be a triangle, and the filled mesh node may be a triangular prism; when the polygon is square, the filled grid node may be a cuboid (or cube). The filling speed of the grid nodes can be improved when the grid nodes such as polyhedrons are filled.
Since the first airflow zone is circular in cross-section, dividing the first airflow zone into an inner zone and an outer zone, it may be more convenient to fill this circular zone with a quadrilateral mesh. If the inner and outer regions are not divided, the square filling is directly used, and gaps are easily left between the grids when the circular region is filled. By dividing into two areas, the control of the target area is facilitated.
In view of the fact that one rectangular parallelepiped may be composed of two triangular prisms, the number of fills is smaller when the filled mesh node is a rectangular parallelepiped than when the triangular prisms are filled, and therefore, it is preferable that the polygon be a long square. More preferably, the polygon is square, and the cross section of the filled triangular prism is isosceles right triangle, so that the filled grid nodes are distributed more uniformly than the rectangle.
In one embodiment of the present invention, referring to fig. 5, the square can be formed at least by one of the following ways: the circle center O of the circle is connected with the equal dividing points (G11, G21, G31 and G41) of the four equal dividing points of the circle to form line segments, and the midpoints (G12, G22, G32 and G42) of the four line segments are connected to obtain the square. Wherein C21 is an inner region formed by a square, and C22 is an outer region. By connecting the midpoints of the four line segments to form the square, it is ensured that the filled grid nodes are distributed more uniformly when the grid nodes are filled in the first airflow flowing area.
In one embodiment of the invention, the number of mesh nodes on each side of the polygon is the same as the number of mesh nodes on the boundary layer circumferential direction arcs corresponding to that side. Referring to fig. 5, the number of grid nodes on one edge G12-G22 of the quadrangle is the same as the number of grid nodes on the boundary layer circumferential direction arcs G11-G21 corresponding to the edge.
It should be noted that, the square may be formed by other ways besides the above way, for example, by connecting points at 2/3 positions (or other identical corresponding positions) of four line segments.
3. And the second airflow flowing area corresponds to the outlet direction of the axisymmetric vectoring nozzle.
In one embodiment of the present invention, in order to describe a distribution rule of the high-temperature air flow in the second air flow area, the three-dimensional grid distribution feature set in advance on the second air flow area corresponding to the outlet direction of the axisymmetric vectoring nozzle may specifically include: stretching the distribution of the grid nodes on the second airflow flowing area along the vector deflection angle of the axisymmetric vector spray pipe, setting the extension distance in the direction of the vector deflection angle, wherein the extension distance is a set multiple of the outlet diameter of the axisymmetric vector spray pipe, and setting the number of the grid nodes in the direction of the vector deflection angle; the mesh nodes arranged on the second airflow flowing area are gradually increased in size in the circumferential direction, the radial direction and the axial direction in the stretching process.
The set multiple is set according to an empirical value, typically 20-50 times, such as 30 times. Because the high-temperature air flow gradually diffuses in the air, in order to meet the rule, the grid node distribution in the circumferential direction and the radial direction can be properly sparse in the stretching process, so that the sizes of the grid nodes in the circumferential direction, the radial direction and the axial direction are gradually increased layer by layer. For example, the size of the grid nodes in the circumferential direction, the radial direction and the axial direction is enlarged by 1.1 times compared with the previous layer of grid.
4. A first air region of the outer wall surface of the axisymmetric vectoring nozzle.
In one embodiment of the present invention, the air flowing through the outer wall surface of the axisymmetric vectoring nozzle needs to be described by using grid nodes, and the three-dimensional grid distribution characteristics set on the first air area of the outer wall surface of the axisymmetric vectoring nozzle may include: setting the number of the circumferential and axial three-dimensional grid nodes on the first air area to be the same as the number of the circumferential and axial three-dimensional grid nodes on the first airflow flowing area; the number of grid nodes in the radial direction on the first air area is set, and the thickness of the grid nodes in the radial direction is gradually increased layer by layer.
The cross section of the first air region is circular. Since the flow of the external air is relatively stable, a change rule from radial dense to sparse of the radial grid nodes, that is, the thickness of the grid nodes in the radial direction is gradually increased layer by layer, can be set. For example, the thickness of each layer of grid nodes is increased by 1.2 times compared with the thickness of the previous layer of grid nodes.
5. And a second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle.
In one embodiment of the present invention, the three-dimensional grid distribution feature may be preset on the second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle, and may specifically include: setting the number of circumferential and axial grid nodes on the second air area to be the same as the number of circumferential and axial grid nodes on the second airflow flowing area; the number of grid nodes in the radial direction on the second air area is set, and the thickness of the grid nodes in the radial direction is gradually increased layer by layer.
The cross section of the second air region is circular. Since the flow of the external air is relatively stable, a change rule from radial dense to sparse of the radial grid nodes, that is, the thickness of the grid nodes in the radial direction is gradually increased layer by layer, can be set.
It should be noted that, since the grid distribution rules of the first air region and the second air region are similar, the thickness increasing rule of the grid node of the first air region in the radial direction is the same as the thickness increasing rule of the grid node of the second air region in the radial direction.
The above completes the explanation of the three-dimensional mesh distribution characteristics set for each region.
Aiming at step 106, according to the preset three-dimensional grid distribution characteristics, generating a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the three-dimensional grid distribution characteristics.
In this step, after the target calculation domain is determined in step 104, a three-dimensional mesh corresponding to the current vector deflection angle may be generated according to a preset three-dimensional mesh distribution feature. Please refer to fig. 6, which is a schematic diagram of a three-dimensional grid.
In one embodiment of the present invention, steps 100-106 generate discrete grid nodes, and in order to enable the three-dimensional grid data corresponding to different vector deflection angles to be utilized, the three-dimensional grid corresponding to each vector deflection angle may be generated into a usable grid file, and specifically, after step 106, may include: and generating a grid file corresponding to the current vector deflection angle according to coordinates of the vertex corresponding to each grid node in the generated three-dimensional grid.
Further, the discrete grid nodes may be combined into available hexahedral grid cells according to a general format, and then coordinates of eight vertices of the hexahedron corresponding to each grid cell may be recorded.
Wherein, the format of the grid file can adopt tecplot format, and the grid file can comprise three parts: header description, grid node coordinates, and a combination of corresponding grid node sequence numbers for each grid cell.
As shown in fig. 7 and 8, the embodiment of the invention provides a three-dimensional grid generating device of an axisymmetric vectoring nozzle. The apparatus embodiments may be implemented by software, or may be implemented by hardware or a combination of hardware and software. In terms of hardware, as shown in fig. 7, a hardware architecture diagram of a computing device where an axisymmetric vector nozzle three-dimensional grid generating apparatus provided by an embodiment of the present invention is located, where in addition to a processor, a memory, a network interface, and a nonvolatile memory shown in fig. 7, the computing device where the embodiment is located may generally include other hardware, such as a forwarding chip responsible for processing a packet, and so on. Taking a software implementation as an example, as shown in fig. 8, as a device in a logic sense, the device is formed by reading a corresponding computer program in a nonvolatile memory into a memory by a CPU of a computing device where the device is located. The three-dimensional grid generating device of axisymmetric vectoring nozzle provided in this embodiment includes:
a constraint unit 801, configured to determine geometric features of an axisymmetric vectoring nozzle, and determine a control curve expression for constraining a computational domain according to the geometric features of the axisymmetric vectoring nozzle;
An angle determining unit 802 for determining a current vectoring deflection angle of the axisymmetric vectoring nozzle;
A calculation domain determining unit 803 for determining a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression;
A three-dimensional grid generating unit 804, configured to generate a three-dimensional grid corresponding to the current vector deflection angle in the target computing domain according to the three-dimensional grid distribution feature according to a preset three-dimensional grid distribution feature.
In one embodiment of the present invention, the computational domain constrained by the control curve expression includes at least one of the following regions: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle, a first airflow flowing area, a second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle, a first air area of the outer wall surface of the axisymmetric vectoring nozzle and a second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle; the first airflow flow region is a region of the axisymmetric vectoring nozzle other than the boundary layer.
In one embodiment of the present invention, the computational domain constrained by the control curve expression includes: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle comprise: setting the number of layers of grid nodes of the boundary layer in the radial direction, the thickness of each layer of grid nodes, the number of each layer of grid nodes in the axial direction and the number of each layer of grid nodes in the circumferential direction; wherein the thickness of the boundary layer in the radial direction of the grid node gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second airflow flowing area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: stretching the distribution of the grid nodes on the second airflow flowing area along the vector deflection angle of the axisymmetric vector spray pipe, setting the extension distance in the direction of the vector deflection angle, wherein the extension distance is a set multiple of the outlet diameter of the axisymmetric vector spray pipe, and setting the number of the grid nodes in the direction of the vector deflection angle; the mesh nodes arranged on the second airflow flowing area are gradually increased in size in the circumferential direction, the radial direction and the axial direction in the stretching process;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: a first air region on the outer wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics set in advance on the first air area of the outer wall surface of the axisymmetric vectoring nozzle include: setting the number of the circumferential and axial three-dimensional grid nodes on the first air area to be the same as the number of the circumferential and axial three-dimensional grid nodes on the first air flow area; setting the number of grid nodes in the radial direction on the first air area, wherein the thickness of the grid nodes in the radial direction gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second air area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: setting the number of circumferential and axial grid nodes on the second air area to be the same as the number of circumferential and axial grid nodes on the second airflow flowing area; the number of grid nodes in the radial direction on the second air area is set, and the thickness of the grid nodes in the radial direction is gradually increased layer by layer.
In one embodiment of the present invention, the computational domain constrained by the control curve expression includes: the first airflow zone; the cross section of the first airflow flowing area is circular;
The three-dimensional grid distribution features previously set on the first airflow region include: dividing the first airflow zone into an inner zone including an axial center and an outer zone other than the inner zone; the cross section corresponding to the inner area is a polygon positioned in the circle; the grid nodes in the inner area and the outer area are evenly distributed.
In one embodiment of the invention, the polygon is a square; and connecting the equally-divided points of the four equally-divided circumferences of the circles with the centers of the circles respectively to form line segments, and connecting the midpoints of the four line segments to obtain the square.
In one embodiment of the present invention, the number of grid nodes on each side of the polygon is the same as the number of grid nodes on the boundary layer circumferential direction arc corresponding to the side.
In one embodiment of the present invention, referring to fig. 9, the axisymmetric vectoring nozzle three-dimensional grid generating apparatus may further include:
And a grid file generating unit 805, configured to generate, for coordinates of vertices corresponding to each grid node in the generated three-dimensional grid, a grid file corresponding to the current vector deflection angle.
It should be understood that the structure illustrated in the embodiments of the present invention is not limited to a specific embodiment of an axisymmetric vectoring nozzle three-dimensional grid generating device. In other embodiments of the invention, an axisymmetric vectoring nozzle three-dimensional mesh generation device may include more or fewer components than shown, or may combine certain components, or split certain components, or a different arrangement of components. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.
The content of information interaction and execution process between the modules in the device is based on the same conception as the embodiment of the method of the present invention, and specific content can be referred to the description in the embodiment of the method of the present invention, which is not repeated here.
The embodiment of the invention also provides a computing device, which comprises a memory and a processor, wherein the memory stores a computer program, and the processor realizes the method for generating the axisymmetric vector nozzle three-dimensional grid in any embodiment of the invention when executing the computer program.
The embodiment of the invention also provides a computer readable storage medium, and the computer readable storage medium stores a computer program, and when the computer program is executed by a processor, the processor is caused to execute the method for generating the axisymmetric vector nozzle three-dimensional grid in any embodiment of the invention.
Specifically, a system or apparatus provided with a storage medium on which a software program code realizing the functions of any of the above embodiments is stored, and a computer (or CPU or MPU) of the system or apparatus may be caused to read out and execute the program code stored in the storage medium.
In this case, the program code itself read from the storage medium may realize the functions of any of the above-described embodiments, and thus the program code and the storage medium storing the program code form part of the present invention.
Examples of storage media for providing program code include floppy disks, hard disks, magneto-optical disks, optical disks (e.g., CD-ROMs, CD-R, CD-RWs, DVD-ROMs, DVD-RAMs, DVD-RWs, DVD+RWs), magnetic tapes, nonvolatile memory cards, and ROMs. Alternatively, the program code may be downloaded from a server computer by a communication network.
Further, it should be apparent that the functions of any of the above-described embodiments may be implemented not only by executing the program code read out by the computer, but also by causing an operating system or the like operating on the computer to perform part or all of the actual operations based on the instructions of the program code.
Further, it is understood that the program code read out by the storage medium is written into a memory provided in an expansion board inserted into a computer or into a memory provided in an expansion module connected to the computer, and then a CPU or the like mounted on the expansion board or the expansion module is caused to perform part and all of actual operations based on instructions of the program code, thereby realizing the functions of any of the above embodiments.
It is noted that relational terms such as first and second, and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Those of ordinary skill in the art will appreciate that: all or part of the steps for implementing the above method embodiments may be implemented by hardware related to program instructions, and the foregoing program may be stored in a computer readable storage medium, where the program, when executed, performs steps including the above method embodiments; and the aforementioned storage medium includes: various media in which program code may be stored, such as ROM, RAM, magnetic or optical disks.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (12)
1. The method for generating the three-dimensional grid of the axisymmetric vectoring nozzle is characterized by comprising the following steps of:
determining geometric characteristics of the axisymmetric vectoring nozzle, and determining a control curve expression for restricting a calculation domain according to the geometric characteristics of the axisymmetric vectoring nozzle;
Determining a current vector deflection angle of the axisymmetric vector nozzle;
determining a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression;
Generating a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the three-dimensional grid distribution characteristics according to the preset three-dimensional grid distribution characteristics;
The computational domain constrained by the control curve expression includes at least one of the following regions: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle, a first airflow flowing area, a second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle, a first air area of the outer wall surface of the axisymmetric vectoring nozzle and a second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle; the first airflow flowing area is an area except a boundary layer in the axisymmetric vectoring nozzle;
The computational domain constrained by the control curve expression includes: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle comprise: setting the number of layers of grid nodes of the boundary layer in the radial direction, the thickness of each layer of grid nodes, the number of each layer of grid nodes in the axial direction and the number of each layer of grid nodes in the circumferential direction; wherein the thickness of the boundary layer in the radial direction of the grid node gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second airflow flowing area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: stretching the distribution of the grid nodes on the second airflow flowing area along the vector deflection angle of the axisymmetric vector spray pipe, setting the extension distance in the direction of the vector deflection angle, wherein the extension distance is a set multiple of the outlet diameter of the axisymmetric vector spray pipe, and setting the number of the grid nodes in the direction of the vector deflection angle; the mesh nodes arranged on the second airflow flowing area are gradually increased in size in the circumferential direction, the radial direction and the axial direction in the stretching process;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: a first air region on the outer wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics set in advance on the first air area of the outer wall surface of the axisymmetric vectoring nozzle include: setting the number of the circumferential and axial three-dimensional grid nodes on the first air area to be the same as the number of the circumferential and axial three-dimensional grid nodes on the first air flow area; setting the number of grid nodes in the radial direction on the first air area, wherein the thickness of the grid nodes in the radial direction gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second air area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: setting the number of circumferential and axial grid nodes on the second air area to be the same as the number of circumferential and axial grid nodes on the second airflow flowing area; the number of grid nodes in the radial direction on the second air area is set, and the thickness of the grid nodes in the radial direction is gradually increased layer by layer.
2. The method of claim 1, wherein the step of determining the position of the substrate comprises,
The computational domain constrained by the control curve expression includes: the first airflow zone; the cross section of the first airflow flowing area is circular;
The three-dimensional grid distribution features previously set on the first airflow region include: dividing the first airflow zone into an inner zone including an axial center and an outer zone other than the inner zone; the cross section corresponding to the inner area is a polygon positioned in the circle; the grid nodes in the inner area and the outer area are evenly distributed.
3. The method of claim 2, wherein the polygon is a square; and connecting the equally-divided points of the four equally-divided circumferences of the circles with the centers of the circles respectively to form line segments, and connecting the midpoints of the four line segments to obtain the square.
4. A method according to claim 2 or 3, wherein the number of mesh nodes on each side of the polygon is the same as the number of mesh nodes on the boundary layer circumferential direction arc corresponding to that side.
5. The method of claim 1, further comprising, after generating a three-dimensional grid corresponding to the current vector deflection angle according to the three-dimensional grid distribution characteristics within the target computing domain:
And generating a grid file corresponding to the current vector deflection angle according to coordinates of the vertex corresponding to each grid node in the generated three-dimensional grid.
6. An axisymmetric vectoring nozzle three-dimensional grid generating device, comprising:
The constraint unit is used for determining the geometric characteristics of the axisymmetric vectoring nozzle and determining a control curve expression for constraining a calculation domain according to the geometric characteristics of the axisymmetric vectoring nozzle;
the angle determining unit is used for determining the current vector deflection angle of the axisymmetric vector spray pipe;
A calculation domain determining unit, configured to determine a target calculation domain corresponding to the current vector deflection angle according to the current vector deflection angle and the control curve expression;
A three-dimensional grid generating unit, configured to generate a three-dimensional grid corresponding to the current vector deflection angle in the target calculation domain according to the three-dimensional grid distribution feature according to a preset three-dimensional grid distribution feature;
The computational domain constrained by the control curve expression includes at least one of the following regions: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle, a first airflow flowing area, a second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle, a first air area of the outer wall surface of the axisymmetric vectoring nozzle and a second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle; the first airflow flowing area is an area except a boundary layer in the axisymmetric vectoring nozzle;
The computational domain constrained by the control curve expression includes: the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the boundary layer of the inner wall surface of the axisymmetric vectoring nozzle comprise: setting the number of layers of grid nodes of the boundary layer in the radial direction, the thickness of each layer of grid nodes, the number of each layer of grid nodes in the axial direction and the number of each layer of grid nodes in the circumferential direction; wherein the thickness of the boundary layer in the radial direction of the grid node gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second airflow flowing area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second airflow flowing area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: stretching the distribution of the grid nodes on the second airflow flowing area along the vector deflection angle of the axisymmetric vector spray pipe, setting the extension distance in the direction of the vector deflection angle, wherein the extension distance is a set multiple of the outlet diameter of the axisymmetric vector spray pipe, and setting the number of the grid nodes in the direction of the vector deflection angle; the mesh nodes arranged on the second airflow flowing area are gradually increased in size in the circumferential direction, the radial direction and the axial direction in the stretching process;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: a first air region on the outer wall surface of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics set in advance on the first air area of the outer wall surface of the axisymmetric vectoring nozzle include: setting the number of the circumferential and axial three-dimensional grid nodes on the first air area to be the same as the number of the circumferential and axial three-dimensional grid nodes on the first air flow area; setting the number of grid nodes in the radial direction on the first air area, wherein the thickness of the grid nodes in the radial direction gradually increases layer by layer;
and/or the number of the groups of groups,
The computational domain constrained by the control curve expression includes: the second air area corresponds to the outlet direction of the axisymmetric vectoring nozzle;
The three-dimensional grid distribution characteristics preset on the second air area corresponding to the outlet direction of the axisymmetric vectoring nozzle comprise: setting the number of circumferential and axial grid nodes on the second air area to be the same as the number of circumferential and axial grid nodes on the second airflow flowing area; the number of grid nodes in the radial direction on the second air area is set, and the thickness of the grid nodes in the radial direction is gradually increased layer by layer.
7. The apparatus of claim 6, wherein the computational domain constrained by the control curve expression comprises: the first airflow zone; the cross section of the first airflow flowing area is circular;
The three-dimensional grid distribution features previously set on the first airflow region include: dividing the first airflow zone into an inner zone including an axial center and an outer zone other than the inner zone; the cross section corresponding to the inner area is a polygon positioned in the circle; the grid nodes in the inner area and the outer area are evenly distributed.
8. The apparatus of claim 7, wherein the polygon is a square; and connecting the equally-divided points of the four equally-divided circumferences of the circles with the centers of the circles respectively to form line segments, and connecting the midpoints of the four line segments to obtain the square.
9. The apparatus of claim 7 or 8, wherein the number of mesh nodes on each side of the polygon is the same as the number of mesh nodes on the boundary layer circumferential direction arc corresponding to that side.
10. The apparatus of claim 6, wherein the apparatus further comprises:
And the grid file generating unit is used for generating a grid file corresponding to the current vector deflection angle according to the coordinates of the vertex corresponding to each grid node in the generated three-dimensional grid.
11. A computing device comprising a memory and a processor, the memory having stored therein a computer program, the processor implementing the method of any of claims 1-5 when the computer program is executed.
12. A computer readable storage medium having stored thereon a computer program which, when executed in a computer, causes the computer to perform the method of any of claims 1-5.
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