CN110457830A - A kind of automatic trim method of three-dimensional full machine numerical simulation - Google Patents
A kind of automatic trim method of three-dimensional full machine numerical simulation Download PDFInfo
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- CN110457830A CN110457830A CN201910752403.4A CN201910752403A CN110457830A CN 110457830 A CN110457830 A CN 110457830A CN 201910752403 A CN201910752403 A CN 201910752403A CN 110457830 A CN110457830 A CN 110457830A
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- G—PHYSICS
- 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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The invention discloses a kind of automatic trim methods of three-dimensional full machine numerical simulation, include the following steps: S1, generate the original calculation grid of three-dimensional full machine；The original calculation grid includes splicing operator block；S2 reads the spatial point coordinate and boundary condition of original calculation grid, and carries out numerical simulation to splicing operator block according to the spatial point coordinate of reading and boundary condition, obtains the pitching moment coefficient under current lifting rudder face drift angle；S3 judges whether lifting rudder face reaches trim condition according to the pitching moment coefficient under current lifting rudder face drift angle, if lifting rudder face is not up to trim condition, adjusts the drift angle of lifting rudder face, and repeat step S2~S3 until reaching trim condition.The present invention carries out numerical simulation by the splicing operator block to three-dimensional full machine, realizes the automatic trim of lifting rudder face drift angle, whole process is not necessarily to manual intervention, convenient and efficient.
Description
Technical field
The present invention relates to the surface and space lattice generation field in computational fluid dynamics, especially a kind of full machines of three-dimensional
The automatic trim method of numerical simulation.
Background technique
Currently, single in order to meet design in computation fluid dynamics (Computational Fluid Dynamics)
Position needs, and is often required to obtain the gas of full machine shape trim condition (pitching moment zero) under different Mach number and the different angles of attack
Dynamic characteristic.It is zero that full machine shape, which can keep full machine pitching moment by going up and down the deflection of rudder face in horizontal tail, but in difference
Under Mach number and the different angles of attack, the lifting control surface deflection angle for meeting full machine trim condition is different, needs the numerical value in CFD
It is determined in iterative process.This just needs a kind of quick three-dimensional object plane to deform and automatically generates the method for calculating grid to simulate
The different lifting rudder face drift angles of full machine shape, at the same in calculating iterative process according to practical flow field situation to lifting rudder face drift angle
It is automatically adjusted, and finally obtains lifting angle of rudder reflection and the final flow field of full machine of trim condition.For the structured grid of mainstream
For method, due to the intrinsic geometric attribute for being difficult to automatically generate of structured grid itself, so there is no go out in the field CFD
Existing relevant full machine automatic trim technology.
Summary of the invention
The technical problems to be solved by the present invention are: in view of the above problems, providing a kind of three-dimensional full machine Numerical-Mode
Quasi- automatic trim method.
The technical solution adopted by the invention is as follows:
A kind of automatic trim method of three-dimensional full machine numerical simulation, includes the following steps:
S1 generates the original calculation grid of three-dimensional full machine；The original calculation grid includes splicing operator block；
S2 reads the spatial point coordinate and boundary condition of original calculation grid, and according to the spatial point coordinate of reading and side
Boundary's condition carries out numerical simulation to splicing operator block, obtains the pitching moment coefficient under current lifting rudder face drift angle；
S3 judges whether lifting rudder face reaches trim condition according to the pitching moment coefficient under current lifting rudder face drift angle,
If lifting rudder face is not up to trim condition, the drift angle of lifting rudder face is adjusted, and repeats step S2~S3 and matches until reaching
Level state.
Further, the splicing operator block includes 4 splicing sections connected by exhibition to crest line, is respectively as follows: close
The Mosaic face of wingtip side, the rudder face side close to wingtip side, the rudder face side close to wing root and the Mosaic face close to wing root；Each
The splicing section includes: the tail block for going up and down rudder face tail portion, space block, transition block, the wall of covering lifting rudder face upper surface
Face block and tail portion link block, and space block, transition block, wall surface block and the tail portion link block of covering lifting rudder face lower surface；Its
In, transition block, wall surface block and the tail portion link block of covering lifting rudder face upper surface are set gradually, covering lifting rudder face lower surface
Transition block, wall surface block and tail portion link block are set gradually, and splicing operator block is made to form opening along lifting rudder face.
Further, in step S3, the method for the drift angle of adjustment lifting rudder face are as follows:
S3.1 adjusts the mark in each splicing section in splicing operator block according to the drift angle of the lifting rudder face of required adjustment
Will line segment obtains new line segment distribution；
S3.2 reconstructs each splicing section according to the distribution of new line segment；
S3.3, the exhibition in each splicing section after connection reconstruct obtain the grid of the lifting rudder face under new drift angle to crest line
File.
Further, in step S3.1, the method for the drift angle of the lifting rudder face adjusted required for determining are as follows: work as pitching moment
Coefficient is greater than zero, then makes to obtain nose-down pitching moment partially under lifting rudder face；When pitching moment coefficient is less than zero, then make to go up and down on rudder face partially
Obtain nose-up pitching moment；When pitching moment coefficient be equal to zero, then determine go up and down rudder face reach trim condition.
Further, in step 3.1, the mark line segment in each splicing section in splicing operator block is adjusted, new line segment is obtained
The method of distribution are as follows:
(1) transition block, wall surface block and tail portion link block is rotated to be close to lifting rudder face upper surface and go up and down rudder face lower surface
Line segment obtains the lifting rudder face shape under new drift angle；
(2) translation wall surface block is close to the position of the lifting rudder face shape under the line segment to new drift angle of transition block and tail portion link block
It sets；
(3) line segment between transition block is kept, space block and transition block are at the line segment of opening direction and the bottom of space block
Sideline fragment position is constant；
(4) remaining line segment keeps its regularity of distribution to be redistributed.
Further, in step S3.1, the mark line segment of splicing operator block is adjusted, during obtaining new line segment distribution,
Keep boundary condition constant.
Further, it in step S3.2, is transfinited according to the process in each splicing section of new line segment distribution reconstruct using two dimension
Interpolation method and sciagraphy are realized.
Further, in step S3.3, the exhibition in each splicing section after connection reconstruct is to the process of crest line using three-dimensional
Transfinite interpolation method and sciagraphy are realized.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
The present invention carries out numerical simulation by the splicing operator block to three-dimensional full machine, realizes the automatic of lifting rudder face drift angle
Trim, whole process is not necessarily to manual intervention, convenient and efficient.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below will be to needed in the embodiment attached
Figure is briefly described, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not construed as pair
The restriction of range for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 is the flow diagram of the automatic trim method of the full machine numerical simulation of three-dimensional of the invention.
Fig. 2 is the topological diagram of original calculation grid of the invention.
Fig. 3 is the schematic diagram of the splicing operator block in original calculation grid of the invention.
Fig. 4 is the schematic diagram in the splicing section in splicing operator block of the invention.
Fig. 5 is the mark line segment schematic diagram of splicing operator block of the invention.
Fig. 6 a is the schematic diagram in the splicing section before going up and down the adjustment of rudder face drift angle.
Fig. 6 b is the schematic diagram for going up and down rudder face drift angle splicing section adjusted.
Fig. 7 a is the schematic diagram for going up and down the splicing operator block before the adjustment of rudder face drift angle.
Fig. 7 b is the schematic diagram for going up and down rudder face drift angle splicing operator block adjusted.
Fig. 8 a is the calculating grid schematic diagram gone up and down before the adjustment of rudder face drift angle.
Fig. 8 b is lifting rudder face drift angle calculating grid schematic diagram adjusted.
Fig. 9 a is the schematic diagram for going up and down the object shape before the adjustment of rudder face drift angle.
Fig. 9 b is the schematic diagram for going up and down rudder face drift angle object shape adjusted.
Appended drawing reference: 1- goes up and down the space block of rudder face upper surface, and 2- goes up and down the transition block of rudder face upper surface, 3- elevator
The wall surface block of face upper surface, 4- go up and down the tail portion link block of rudder face upper surface, and 5- goes up and down the tail block of rudder face tail portion, 6- lifting
The space block of rudder face lower surface, 7- go up and down the wall surface block of the transition block of rudder face lower surface, 8- lifting rudder face lower surface, 9- elevator
The tail portion link block of face lower surface, 10- splicing operator block, Mosaic face of the 11- close to wingtip side, rudder face of the 12- close to wingtip side
Side, 13- is close to the rudder face side of wing root, Mosaic face of the 14- close to wing root.
Specific embodiment
Feature and performance of the invention are described in further detail with reference to embodiments.
As shown in Figure 1, a kind of automatic trim method of three-dimensional full machine numerical simulation provided in this embodiment, including walk as follows
It is rapid:
S1 generates the original calculation grid of three-dimensional full machine；As shown in Fig. 2, the original calculation grid includes splicing operator
Block 10；The original calculation grid further includes full machine external mesh, i.e., remaining grid other than splicing operator block 10 is
Full machine external mesh；Splicing operator block 10 is spliced with full machine external mesh with connecting method, and full machine external mesh can be by user
It voluntarily determines, is not limited in the present invention.
As the preferred of the present embodiment, connected by exhibition to crest line as shown in figure 3, the splicing operator block includes 4
Splice section, from wingtip to wing root direction be respectively as follows: close to wingtip side Mosaic face 11, close to wingtip side rudder face side 12,
Rudder face side 13 close to wing root and the Mosaic face 14 close to wing root；Due to the rotary gap between lifting rudder face and tailplane
Very little, therefore between the Mosaic face 11 of wingtip side and the rudder face side 12 of close wingtip side, and close to the rudder face of wing root
Side 13 and the spacing very little between the Mosaic face 14 of wing root.
As shown in figure 4, each splicing section includes: the tail block 5 for going up and down rudder face tail portion, covering is gone up and down on rudder face
Space block 1, transition block 2, wall surface block 3 and the tail portion link block 4 on surface, and space block 7, the mistake of covering lifting rudder face lower surface
Cross block 6, wall surface block 9 and tail portion link block 8；Wherein, the transition block 2 of covering lifting rudder face upper surface, wall surface block 3 are connected with tail portion
Block 4 is set gradually, and transition block 6, wall surface block 9 and the tail portion link block 8 of covering lifting rudder face lower surface are set gradually, and makes to splice net
Lattice block 10 forms opening along lifting rudder face.That is, lifting rudder face upper surface and lifting rudder face lower surface are symmetrical arranged and have time
Between block 7, transition block 6, wall surface block 3 and tail portion link block 4, splicing operator block 10 along lifting rudder face formed opening be close to elevator
Face.
S2 reads the spatial point coordinate and boundary condition of original calculation grid, and according to the spatial point coordinate of reading and side
Boundary's condition carries out numerical simulation to splicing operator block 10, obtains the pitching moment coefficient under current lifting rudder face drift angle；In this reality
It applies in example, the spatial point coordinate and boundary condition of original calculation grid can be read using CFD software for calculation, wherein perimeter strip
Part includes the splicing boundary condition of given splicing operator block 10.Wherein, according to the spatial point coordinate and boundary condition pair of reading
The method that splicing operator block 10 carries out numerical simulation can be using the conventional Calculation Method in CFD software for calculation.
S3 judges whether lifting rudder face reaches trim condition according to the pitching moment coefficient under current lifting rudder face drift angle,
If lifting rudder face is not up to trim condition, the drift angle of lifting rudder face is adjusted, and repeats step S2~S3 and matches until reaching
Level state.Specifically, the method for the drift angle of adjustment lifting rudder face are as follows:
S3.1 adjusts each splicing section in splicing operator block 10 according to the drift angle of the lifting rudder face of required adjustment
Indicate line segment, obtains new line segment distribution；
Wherein it is determined that required adjustment lifting rudder face drift angle method are as follows: when pitching moment coefficient be greater than zero, then make
Nose-down pitching moment is obtained partially under lifting rudder face；When pitching moment coefficient is less than zero, then makes to go up and down on rudder face and obtain nose-up pitching moment partially；When
Pitching moment coefficient is equal to zero, then determines that going up and down rudder face reaches trim condition.In practical applications, it needs by multiple trim
Trim condition can be reached, then can realize the automatic trim of lifting rudder face by repeating step S2~S3.
It wherein, for convenience of explanation, is as shown in Figure 5 by the markings segment number for splicing section in splicing operator block 10The mark line segment for then adjusting splicing operator block 10, the method for obtaining new line segment distribution are as follows:
(1) transition block 2,6 is rotated, wall surface block 3,9 and tail portion link block 4,8 are close to lifting rudder face upper surface and lifting
The line segment of rudder face lower surfaceObtain the lifting rudder face shape under new drift angle；
(2) translation wall surface block 3,9 be close to transition block 2,6 and tail portion link block 4,8 line segment (8., 9.,) extremely
The position of lifting rudder face shape under new drift angle；
(3) line segment between transition block 2 and transition block 6 is keptSpace block 1,7 and transition block 2,6 are in opening side
To line segment (1., 7.,) and space block 1,7 bottom edge line segment (2.,) position is constant；
(4) remaining line segment (3., 4., 5., 6., 10., ) its regularity of distribution is kept to be redistributed.
Wherein, the mark line segment for adjusting splicing operator block 10 keeps boundary condition not during obtaining new line segment distribution
Become.
S3.2 reconstructs each splicing section according to the distribution of new line segment；In the present embodiment, every according to the distribution reconstruct of new line segment
The process in a splicing section can be realized using two-dimentional transfinite interpolation method and sciagraphy.
S3.3, the exhibition in each splicing section after connection reconstruct obtain the grid of the lifting rudder face under new drift angle to crest line
File.In the present embodiment, the exhibition in each splicing section after connection reconstruct can be transfinited slotting to the process of crest line using three-dimensional
Value method and sciagraphy are realized.
Using the above-mentioned full machine numerical simulation of three-dimensional of the invention automatic trim method into three-dimensional full machine lifting rudder face
Drift angle adjustment:
The comparison diagram in the splicing section of lifting rudder face drift angle adjustment front and back as shown in Fig. 6 a-6b.
The comparison diagram of the splicing operator block of lifting rudder face drift angle adjustment front and back as shown in Fig. 7 a-7b.
The comparison diagram of the calculating grid of lifting rudder face drift angle adjustment front and back as shown in Figure 8 a-8b.
The comparison diagram of the object shape of lifting rudder face drift angle adjustment front and back as shown in Fig. 9 a-9b.
It can see after going up and down control surface deflection, object shape and calculating grid including three-dimensional full machine can be completed certainly
Dynamic deformation and reconstruct.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (8)
1. a kind of automatic trim method of three-dimensional full machine numerical simulation, which comprises the steps of:
S1 generates the original calculation grid of three-dimensional full machine；The original calculation grid includes splicing operator block；
S2 reads the spatial point coordinate and boundary condition of original calculation grid, and according to the spatial point coordinate and perimeter strip of reading
Part carries out numerical simulation to splicing operator block, obtains the pitching moment coefficient under current lifting rudder face drift angle；
S3 judges to go up and down whether rudder face reaches trim condition according to the pitching moment coefficient under current lifting rudder face drift angle, if rising
Drop rudder face is not up to trim condition, then adjusts the drift angle of lifting rudder face, and repeats step S2~S3 until reaching with flat-shaped
State.
2. the automatic trim method of three-dimensional full machine numerical simulation according to claim 1, which is characterized in that the splicing net
Lattice block includes 4 splicing sections connected by exhibition to crest line, is respectively as follows: the Mosaic face close to wingtip side, close to wingtip side
Rudder face side, the rudder face side close to wing root and the Mosaic face close to wing root；Each splicing section includes: lifting rudder face tail
The tail block in portion, space block, transition block, wall surface block and the tail portion link block of covering lifting rudder face upper surface, and covering rise
Space block, transition block, wall surface block and the tail portion link block of rudder face lower surface drop；Wherein, the transition of covering lifting rudder face upper surface
Block, wall surface block and tail portion link block are set gradually, covering lifting rudder face lower surface transition block, wall surface block and tail portion link block according to
Secondary setting makes splicing operator block form opening along lifting rudder face.
3. the automatic trim method of three-dimensional full machine numerical simulation according to claim 2, which is characterized in that in step S3,
The method of the drift angle of adjustment lifting rudder face are as follows:
S3.1 adjusts the markings in each splicing section in splicing operator block according to the drift angle of the lifting rudder face of required adjustment
Section obtains new line segment distribution；
S3.2 reconstructs each splicing section according to the distribution of new line segment；
S3.3, the exhibition in each splicing section after connection reconstruct obtain the grid file of the lifting rudder face under new drift angle to crest line.
4. the automatic trim method of three-dimensional full machine numerical simulation according to claim 3, which is characterized in that step S3.1
In, determine required for adjust lifting rudder face drift angle method are as follows: when pitching moment coefficient be greater than zero, then make go up and down rudder face under
Nose-down pitching moment is obtained partially；When pitching moment coefficient is less than zero, then makes to go up and down on rudder face and obtain nose-up pitching moment partially；When pitching moment system
Number is equal to zero, then determines that going up and down rudder face reaches trim condition.
5. the automatic trim method of three-dimensional full machine numerical simulation according to claim 3, which is characterized in that in step 3.1,
The mark line segment for adjusting each splicing section in splicing operator block, the method for obtaining new line segment distribution are as follows:
(1) transition block, wall surface block and tail portion link block is rotated to be close to lifting rudder face upper surface and go up and down the line segment of rudder face lower surface,
Obtain the lifting rudder face shape under new drift angle；
(2) translation wall surface block is close to the position of the lifting rudder face shape under the line segment to new drift angle of transition block and tail portion link block；
(3) line segment between transition block is kept, space block and transition block are in the line segment of opening direction and the hemline of space block
Fragment position is constant；
(4) remaining line segment keeps its regularity of distribution to be redistributed.
6. the automatic trim method of three-dimensional full machine numerical simulation according to claim 5, which is characterized in that step S3.1
In, the mark line segment of splicing operator block is adjusted, during obtaining new line segment distribution, keeps boundary condition constant.
7. the automatic trim method of three-dimensional full machine numerical simulation according to claim 3, which is characterized in that step S3.2
In, it is realized according to the process in each splicing section of new line segment distribution reconstruct using two-dimentional transfinite interpolation method and sciagraphy.
8. the automatic trim method of three-dimensional full machine numerical simulation according to claim 3, which is characterized in that step S3.3
In, the exhibition in each splicing section after connection reconstruct is realized to the process of crest line using three-dimensional transfinite interpolation method and sciagraphy.
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| CN116266238A (en) * | 2022-12-28 | 2023-06-20 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Supersonic near-ground parallel interstage separation method with preset rudder deflection characteristics |
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| CN110457830B (en) | 2022-08-09 |
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