CN115057001A - Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method - Google Patents
Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method Download PDFInfo
- Publication number
- CN115057001A CN115057001A CN202210984504.6A CN202210984504A CN115057001A CN 115057001 A CN115057001 A CN 115057001A CN 202210984504 A CN202210984504 A CN 202210984504A CN 115057001 A CN115057001 A CN 115057001A
- Authority
- CN
- China
- Prior art keywords
- grid
- control surface
- control
- point
- line
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Numerical Control (AREA)
Abstract
The invention discloses a grid-based airfoil trailing edge control surface rapid generation and control efficiency evaluation method, which relates to the technical field of aircraft design and comprises the following steps: s1, analyzing the airfoil structure grid of the control surface to be generated, and determining the connection relation between grid surfaces; s2, longitudinally dividing the grid surface according to the given control surface position coordinates; s3, transversely dividing the grid surface according to the given length of the control surface; s4, zooming the rear edge dividing surface to leave a control surface gap; s5, deflecting the control surface by a designated angle; s6, filling the gap in a point-line-surface mode to form a closed surface; and S7, the grid is handed to a CFD program to calculate aerodynamic force, and full automation of airfoil profile-control surface parameter-aerodynamic force calculation is formed. The invention can realize the rapid generation of the control surface at the trailing edge of the airfoil, obtain the surface structure grid after the control surface deflects, and directly send the grid to a CFD program for calculation to form the full automation of airfoil appearance-control surface parameter-aerodynamic force calculation.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to a grid-based method for quickly generating a control surface at the trailing edge of an airfoil and evaluating the control efficiency.
Background
In the design of an aircraft, the arrangement of control surfaces is a very important work, and the control surface design not only relates to the stability control performance of the whole aircraft, but also is sometimes used for determining whether the aircraft scheme is qualitative. The adoption of a pneumatic-operating-stability integrated design method is an important aspect of exploiting the performance potential of an aircraft. However, the key point of the aerodynamic stability integrated design method lies in the rapid generation and performance evaluation of the control surface, whether the control surface can be automatically generated or not, and the grid required by the control efficiency evaluation is automatically generated, which is the most important step.
At present, most of the rapid modeling methods of the control surface are based on CAD, accurate control efficiency evaluation needs to manually grid a CAD model and send the CAD model to a CFD program for aerodynamic force calculation, an input part of an intermediate grid needs to be intervened by people, automation is difficult to realize, and integrated optimization of pneumatics and stability control is difficult to realize.
Therefore, the invention aims to provide a grid-based method for quickly generating the control surface of the trailing edge of the airfoil and evaluating the control efficiency so as to solve the problems.
Disclosure of Invention
The invention aims to solve the problems and provides a method for quickly generating the trailing edge control surface and evaluating the control efficiency of the airfoil based on grids.
In order to achieve the purpose, the technical scheme of the invention is as follows: a grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method comprises the following steps:
s1, analyzing the airfoil structure grid of the control surface to be generated, and determining the connection relation between grid surfaces;
s2, longitudinally dividing the grid surface according to the given control surface position coordinates;
s3, transversely dividing the grid surface according to the given length of the control surface;
s4, zooming the rear edge dividing surface to leave a control surface gap;
s5, deflecting the control surface by a designated angle;
s6, filling the gap in a point-line-surface mode to form a closed surface;
and S7, the grid is handed to a CFD program to calculate aerodynamic force, and full automation of airfoil profile-control surface parameter-aerodynamic force calculation is formed.
Further, step S1 is specifically:
giving an initial appearance of the aircraft wing surface, and drawing a surface structure grid by using grid division software; in the grid division, the direction i is along a flow field, the direction j is along the spanwise direction of the aircraft, the aircraft is divided into an upper surface part and a lower surface part by adopting a front edge line, the upper surface part and the lower surface part are used as two areas to respectively draw grids, the distribution of front edge rear points is similar, and the output grid is a plot3d format file; and establishing a grid surface as a starting surface of the left grid surface, and sequentially constructing three grid surface connecting links of an upper surface, a lower surface and a rear edge surface according to the condition that the head and the tail of the grid surface are the same as the adjacent surfaces.
Further, in step S2, the position of the control surface is determined by the spanwise coordinates of the left and right sides, a plane perpendicular to the symmetry plane is constructed according to the coordinates, and a grid plane is cut;
the grid surface consists of grid lines in a spanwise j direction and grid lines in a chordwise i direction; firstly, finding a grid surface intersected with a cutting surface, then solving an intersection point of a first j-direction line and the grid surface, and taking a j serial number of a point closest to the intersection point as a reference serial number; then, aiming at each j-direction grid line, solving an intersection point of the grid line and a cutting surface, moving points of the reference sequence to the intersection point position along the j line, and moving the points on the left side and the right side by corresponding amount according to a proportional coefficient method; thus, a new grid with the basic serial number i as an intersection line is obtained, and the grid surface is divided into a left grid and a right grid at the position of the reference serial number.
Further, in step S3, two points of the transverse cut are found from the grid surface trailing edge point and the control surface left-right length, and the two points are extended in the Z direction to obtain a transverse cut frame. Solving the intersection point of the first i-direction line of the cut grid surface and the transverse cutting frame, and finding the i-direction sequence number of the point closest to the intersection point on the line as a basic sequence number; and sequentially solving the intersection point of each i-direction line and the transverse cutting frame, moving the corresponding point of the basic serial number to the intersection point position, moving the upper point and the lower point by corresponding amount according to a proportional coefficient method to form a new grid with the j-direction line of the basic serial number as the intersection line, and dividing the grid into an upper part and a lower part.
Further, in step S4, the upper and lower grid surfaces obtained in step S3, the upper grid surface being a main wing surface and the rear grid surface being a control surface, are scaled according to a certain ratio by the main method: sequentially moving the head point and the tail point of each i-direction line along the line direction, and moving the internal points by corresponding amounts according to the distance proportionality coefficient; and moving the head point and the tail point of each j-direction line along the line direction, and moving the internal points by corresponding amount according to the distance scale coefficient.
Further, in step S5, the control surface mesh surfaces are defined as a control surface upper mesh, a control surface lower mesh and a control surface trailing edge mesh; and (3) taking the connecting line of the middle point of the connecting line of the upper grid (i 0, j 0) point and the lower grid (i 0, j 0) point and the middle point of the connecting line of the upper grid (i 0, j-1) point and the lower grid (i 0, j-1) point as a rotating shaft, and deflecting the three grid surfaces according to the given deflection angle of the control surface.
Further, in step S6, after the control surface mesh plane is scaled and deflected, according to the gap existing between the main wing surface and the control surface mesh plane, a point generating line and a plane formed by four line overrun interpolations are filled in the gap, and a surface mesh closed after the control surface is deflected is obtained.
Further, in step S7, directly subjecting the closed surface grid obtained in step S6 to aerodynamic force calculation by an euler equation solver based on a space cartesian grid, so as to obtain the aerodynamic force after the control surface deflects; the control efficiency of the control surface can be obtained by the aerodynamic force difference of different rudder deflections.
Compared with the prior art, the beneficial effect of this scheme: the method can realize the rapid generation of the control surface of the trailing edge of the airfoil, directly obtain the surface structure grid after the control surface deflects, directly send the grid to a CFD program for calculation, form the full automation of airfoil appearance, control surface parameters, aerodynamic force calculation and control effect evaluation, and can be used for supporting the aerodynamic-operational stability integrated design of an aircraft.
Drawings
FIG. 1 is a flow chart of a method for rapidly generating a control surface of a trailing edge of an airfoil based on a grid and evaluating a control efficiency according to an embodiment of the invention;
FIG. 2 is an example of an airfoil surface structure grid in an embodiment of the present invention;
FIG. 3 is a cross-sectional view of a grid face after longitudinal cutting in an embodiment of the present invention;
FIG. 4 is a schematic view of a transverse cutting box determined by the left and right length of the control surface and the position of the trailing edge in an embodiment of the invention;
FIG. 5 is a cross-cut mesh side of an embodiment of the present invention;
FIG. 6 is a mesh plane after scaling of the trailing edge mesh in an embodiment of the present invention;
FIG. 7 is a grid after deflection of the control surface in an embodiment of the invention;
FIG. 8 is a grid after gap filling in an embodiment of the present invention;
fig. 9 is a grid global schematic diagram of the control surface automatic generation in the embodiment of the present invention.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions of the present invention will be described in further detail below with reference to the embodiments of the present invention and the accompanying drawings. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict. The present invention will be described in detail with reference to examples.
Example (b):
as shown in FIG. 1, a method for rapidly generating a control surface of a trailing edge of an airfoil based on a grid and evaluating a control effect comprises the following steps:
step 1, drawing a surface structure grid of the airfoil, and analyzing a connection relation;
given the initial profile of the aircraft airfoil, a surface structure grid is drawn using meshing software. The grid division has certain requirements, the direction i is along the flow field, the direction j is along the spanwise direction of the aircraft, the aircraft is divided into an upper surface part and a lower surface part by a front edge line, the upper surface and the lower surface are used as two areas to respectively draw grids, the distribution of front edges and rear points is similar, and the output grid is a plot3d format file. And establishing a grid surface as a starting surface of the left grid surface, and sequentially constructing three grid surface connecting links of an upper surface, a lower surface and a rear edge surface according to the condition that the head and the tail of the grid surface are the same as the adjacent surfaces.
Step 2, giving the left and right spread positions of the control surface, and cutting a grid surface;
the position of the control surface is determined by the spanwise coordinates of the left side and the right side, a plane perpendicular to the symmetrical plane is constructed according to the coordinates, and a grid plane is cut. The grid surface is composed of grid lines along the spanwise j direction and grid lines along the chordwise i direction. Firstly, finding a grid surface intersected with a cutting surface, then solving an intersection point of the grid surface and a first j-direction line, taking a j serial number of a point closest to the intersection point as a reference serial number, thirdly, solving the intersection point of each j-direction grid line and the cutting surface, moving the point of a reference sequence to the intersection point position along the j line, and moving the points on the left side and the right side by a corresponding amount according to a proportional coefficient method. Thus, a new grid with the basic serial number i as an intersection line is obtained, and the grid surface is divided into a left grid and a right grid at the position of the reference serial number.
Step 3, transversely cutting the grid surface according to the left and right length of the control surface
And finding two points for transverse cutting according to the rear edge point of the grid surface and the left and right lengths of the control surface, and extending the two points to the Z direction to obtain a transverse cutting frame. Solving the intersection point of the first i-direction line of the cut grid surface and the transverse cutting frame, and finding the i-direction sequence number of the point closest to the intersection point on the line as a basic sequence number; and sequentially solving the intersection point of each i-direction line and the transverse cutting frame, moving the corresponding point of the basic serial number to the intersection point position, moving the upper point and the lower point by corresponding amount according to a proportional coefficient method to form a new grid with the j-direction line of the basic serial number as the intersection line, and dividing the grid into an upper part and a lower part.
And 4, step 4: the trailing edge grid surface is zoomed to form the gap of the main airfoil surface of the control surface.
And (3) scaling the rear grid surface according to a certain proportion by using the upper grid surface and the lower grid surface obtained in the step (3) as main wing surfaces and the rear grid surface as a control surface, wherein the main method comprises the following steps: sequentially moving the head point and the tail point of each i-direction line along the line direction, and moving the internal points by corresponding amounts according to the distance proportionality coefficient; and moving the head point and the tail point of each j-direction line along the line direction, and moving the internal points by corresponding amount according to the distance scale coefficient.
And 5: and deflecting the control surface angle.
To this end, the control surface grid surface comprises a control surface upper grid, a control surface lower grid and a control surface trailing edge grid. And the middle point of the connecting line of the points of the upper grid (i 0, j 0) and the lower grid (i 0, j 0), the middle point of the connecting line of the points of the upper grid (i 0, j-1) and the lower grid (i 0, j-1), and the connecting line of the two points are rotating shafts, so that three grid surfaces are deflected according to the given deflection angle of the control surface.
Step 6: the gap is filled and closed.
After the grid surface of the control surface is zoomed and deflected, a gap exists between the main wing surface and the grid surface of the control surface, the gap is filled by a point generating line and a surface formed by four line overrun interpolation. Thus, a closed surface grid after deflection of the control surface is obtained.
And 7: aerodynamic calculations were performed based on a CFD program of cartesian grid.
And 6, directly handing the surface closed grid obtained in the step 6 to an Euler equation solver based on a space Cartesian grid to calculate aerodynamic force, so as to obtain the aerodynamic force after the control surface deflects. The control efficiency of the control surface can be obtained by the aerodynamic force difference of different rudder deflections.
In the present embodiment, as shown in fig. 2, it is an example of a surface structure grid of an airfoil, and shows that a grid of a conventional wing structure is divided into an i direction as a longitudinal direction and a j direction as a transverse direction; as shown in fig. 3, which is a grid face after longitudinal cutting, showing the right side wing grid cut into 3 pieces by two longitudinal sections; FIG. 4 is a schematic view of a transverse cutting box defined by the left and right length of the control surface and the position of the trailing edge, wherein the rectangular area is a cutting box; as shown in fig. 5, the grid surface after the transverse cutting is divided into an upper part and a lower part by the cutting frame; as shown in fig. 6, it is the scaled grid surface of the grid at the rear edge, and the scaled grid surface below the middle forms gaps with the grid surfaces above and right and left; as shown in fig. 7, the grid is the grid after the control surface is deflected, and the grid surface below the middle is the grid of the control surface after deflection; as shown in fig. 8, the gap is filled in the mesh after gap filling by using a reconstruction method to form a closed surface; as shown in fig. 9, it is a global grid diagram for the control surface automatic generation, which is a closed grid overview of the control surface generated rear wing.
In the embodiments of the invention, the grid-based airfoil trailing edge control surface rapid generation and control efficiency evaluation method can realize rapid generation of the airfoil trailing edge control surface, obtain the surface structure grid after the control surface is deflected, and directly send the grid to a CFD program for calculation, so as to form full automation of airfoil shape-control surface parameter-aerodynamic force calculation.
The above embodiments are merely illustrative and not restrictive, and those skilled in the art can modify the embodiments without inventive contribution as required after reading this specification, but the invention is protected by the claims only.
Claims (8)
1. A grid-based airfoil trailing edge control surface rapid generation and control efficiency evaluation method is characterized by comprising the following steps: the method comprises the following steps:
s1, analyzing the airfoil structure grid of the control surface to be generated, and determining the connection relation between grid surfaces;
s2, longitudinally dividing the grid surface according to the given control surface position coordinates;
s3, transversely dividing the grid surface according to the given length of the control surface;
s4, zooming the rear edge dividing surface to leave a control surface gap;
s5, deflecting the control surface by a designated angle;
s6, filling the gap in a point-line-surface mode to form a closed surface;
and S7, the grid is handed to a CFD program to calculate aerodynamic force, and full automation of airfoil profile-control surface parameter-aerodynamic force calculation is formed.
2. The method for rapidly generating the control surface of the trailing edge of the airfoil based on the grid and evaluating the control efficiency as claimed in claim 1, wherein the method comprises the following steps: step S1 specifically includes:
giving an initial appearance of the aircraft wing surface, and drawing a surface structure grid by using grid division software; in the grid division, the direction i is along a flow field, the direction j is along the spanwise direction of the aircraft, the aircraft is divided into an upper surface part and a lower surface part by adopting a front edge line, the upper surface part and the lower surface part are used as two areas to respectively draw grids, the distribution of front edge rear points is similar, and the output grid is a plot3d format file; and establishing a grid surface as the initial surface of the left grid surface, and sequentially constructing three grid surface connecting links of an upper surface, a lower surface and a rear edge surface according to the condition that the head and the tail of the three grid surfaces are the same and are adjacent surfaces.
3. The method for rapidly generating the control surface of the trailing edge of the airfoil based on the grid and evaluating the control efficiency as claimed in claim 1, wherein the method comprises the following steps: in the step S2, the position of the control surface is determined by the spanwise coordinates of the left side and the right side, a plane perpendicular to the symmetrical plane is constructed according to the coordinates, and a grid surface is cut; the grid surface consists of grid lines in a spanwise j direction and grid lines in a chordwise i direction; firstly, finding a grid surface intersected with a cutting surface, then solving an intersection point of a first j-direction line and the grid surface, and taking a j serial number of a point closest to the intersection point as a reference serial number; then, aiming at each j-direction grid line, solving an intersection point of the grid line and a cutting surface, moving points of the reference sequence to the intersection point position along the j line, and moving the points on the left side and the right side by corresponding amount according to a proportional coefficient method; thus, a new grid with the basic serial number i as an intersection line is obtained, and the grid surface is divided into a left grid and a right grid at the position of the reference serial number.
4. The method for rapidly generating the control surface of the trailing edge of the airfoil based on the grid and evaluating the control efficiency as claimed in claim 1, wherein the method comprises the following steps: in the step S3, two points of transverse cutting are found according to the grid surface trailing edge point and the control surface left and right length, and the two points are extended towards the Z direction to obtain a transverse cutting frame; solving the intersection point of the first i-direction line of the cut grid surface and the transverse cutting frame, and finding the i-direction sequence number of the point closest to the intersection point on the line as a basic sequence number; and sequentially solving the intersection point of each i-direction line and the transverse cutting frame, moving the corresponding point of the basic serial number to the intersection point position, moving the upper point and the lower point by corresponding amount according to a proportional coefficient method to form a new grid with the j-direction line of the basic serial number as the intersection line, and dividing the grid into an upper part and a lower part.
5. The method for rapidly generating the control surface of the trailing edge of the airfoil based on the grid and evaluating the control efficiency as claimed in claim 4, wherein: in step S4, the upper and lower mesh surfaces obtained in step 3, the upper mesh surface being a main wing surface and the rear mesh surface being a control surface, are scaled according to a certain proportion, the main method being: sequentially moving the head point and the tail point of each i-direction line along the line direction, and moving the internal points by corresponding amounts according to the distance proportionality coefficient; and moving the head point and the tail point of each j-direction line along the line direction, and moving the internal points by corresponding amount according to the distance scale coefficient.
6. The method for rapidly generating the control surface of the trailing edge of the airfoil based on the grid and evaluating the control efficiency as claimed in claim 1, wherein the method comprises the following steps: in step S5, the control surface grid surfaces are defined as control surface upper grid, control surface lower grid and control surface trailing edge grid; and (3) taking the connecting line of the middle point of the connecting line of the upper grid (i 0, j 0) point and the lower grid (i 0, j 0) point and the middle point of the connecting line of the upper grid (i 0, j-1) point and the lower grid (i 0, j-1) point as a rotating shaft, and deflecting the three grid surfaces according to the given deflection angle of the control surface.
7. The method for rapidly generating the trailing edge control surface and evaluating the rudder efficiency of the airfoil based on the grids as claimed in claim 1, wherein the method comprises the following steps: in step S6, after the control surface grid surface is scaled and deflected, according to the gap existing between the main wing surface and the control surface grid, a point generating line and a surface formed by four line overrun interpolations are filled in the gap to obtain a surface grid closed after the control surface is deflected.
8. The method for rapidly generating the control surface of the trailing edge of the airfoil based on the grid and evaluating the control efficiency as claimed in claim 7, wherein: in step S7, directly handing the closed surface grid obtained in step S6 to an Euler equation solver based on a space Cartesian grid to calculate aerodynamic force, so as to obtain aerodynamic force after the control surface deflects; the control efficiency of the control surface can be obtained by the aerodynamic force difference of different rudder deflections.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210984504.6A CN115057001B (en) | 2022-08-17 | 2022-08-17 | Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210984504.6A CN115057001B (en) | 2022-08-17 | 2022-08-17 | Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115057001A true CN115057001A (en) | 2022-09-16 |
| CN115057001B CN115057001B (en) | 2023-03-24 |
Family
ID=83207266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210984504.6A Active CN115057001B (en) | 2022-08-17 | 2022-08-17 | Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115057001B (en) |
Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090112502A1 (en) * | 2007-10-31 | 2009-04-30 | Airbus España, S.L. | Methods and systems for assisting in the design of mobile surfaces of objects |
| US20100250212A1 (en) * | 2009-03-31 | 2010-09-30 | Airbus Espana, S.L. | Computer-aided method for a cost-optimized calculation of variable distributions over an aerodynamic surface |
| WO2011119278A2 (en) * | 2010-03-24 | 2011-09-29 | The Boeing Company | Advancing layer surface grid generation |
| EP2600263A2 (en) * | 2011-12-02 | 2013-06-05 | Airbus Engineering Centre India | System and method for simulating aerodynamics over an aircraft for a deflected position of a movable aircraft control surface using a structured chimera mesh |
| CN107451354A (en) * | 2017-07-27 | 2017-12-08 | 中国人民解放军军械工程学院 | A kind of emulation mode and terminal device of canard configuration rudders pneumatic power parameter |
| CN107491616A (en) * | 2017-08-24 | 2017-12-19 | 北京航空航天大学 | A kind of structure finite element parametric modeling method suitable for grid configuration rudder face |
| US20190005185A1 (en) * | 2017-06-30 | 2019-01-03 | Aerion Corporation | Computing Techniques for Three-Dimensional Modeling and Design Analysis |
| CN109492234A (en) * | 2017-09-11 | 2019-03-19 | 北京机电工程研究所 | A kind of improved fluid structurecoupling interpolation method |
| CN109515739A (en) * | 2018-11-21 | 2019-03-26 | 中国航天空气动力技术研究院 | A kind of Quick prediction method for aerodynamic property |
| CN110457830A (en) * | 2019-08-15 | 2019-11-15 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of automatic trim method of three-dimensional full machine numerical simulation |
| CN110472333A (en) * | 2019-08-15 | 2019-11-19 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of automatic trim method of dimensional airfoil numerical simulation |
| CN110550226A (en) * | 2019-09-17 | 2019-12-10 | 南京林业大学 | Structure optimization design method for small multi-rotor-wing plant protection unmanned aerial vehicle |
| CN111611652A (en) * | 2020-06-04 | 2020-09-01 | 电子科技大学 | Flapping wing aerodynamic characteristic analysis method based on active flexible deformation |
| CN112364442A (en) * | 2020-12-22 | 2021-02-12 | 北京机电工程研究所 | Bidirectional intelligent selection fluid-solid coupling analysis method |
| CN112572822A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Method for determining spanwise gap of trailing edge control surface of high-aspect-ratio wing |
| CN114444214A (en) * | 2022-04-07 | 2022-05-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Aircraft control method based on control surface efficiency |
| CN114611420A (en) * | 2022-02-10 | 2022-06-10 | 北京机电工程研究所 | Unsteady aerodynamic force calculation precision evaluation and correction method |
-
2022
- 2022-08-17 CN CN202210984504.6A patent/CN115057001B/en active Active
Patent Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090112502A1 (en) * | 2007-10-31 | 2009-04-30 | Airbus España, S.L. | Methods and systems for assisting in the design of mobile surfaces of objects |
| US20100250212A1 (en) * | 2009-03-31 | 2010-09-30 | Airbus Espana, S.L. | Computer-aided method for a cost-optimized calculation of variable distributions over an aerodynamic surface |
| WO2011119278A2 (en) * | 2010-03-24 | 2011-09-29 | The Boeing Company | Advancing layer surface grid generation |
| EP2600263A2 (en) * | 2011-12-02 | 2013-06-05 | Airbus Engineering Centre India | System and method for simulating aerodynamics over an aircraft for a deflected position of a movable aircraft control surface using a structured chimera mesh |
| US20190005185A1 (en) * | 2017-06-30 | 2019-01-03 | Aerion Corporation | Computing Techniques for Three-Dimensional Modeling and Design Analysis |
| CN107451354A (en) * | 2017-07-27 | 2017-12-08 | 中国人民解放军军械工程学院 | A kind of emulation mode and terminal device of canard configuration rudders pneumatic power parameter |
| CN107491616A (en) * | 2017-08-24 | 2017-12-19 | 北京航空航天大学 | A kind of structure finite element parametric modeling method suitable for grid configuration rudder face |
| CN109492234A (en) * | 2017-09-11 | 2019-03-19 | 北京机电工程研究所 | A kind of improved fluid structurecoupling interpolation method |
| CN109515739A (en) * | 2018-11-21 | 2019-03-26 | 中国航天空气动力技术研究院 | A kind of Quick prediction method for aerodynamic property |
| CN110457830A (en) * | 2019-08-15 | 2019-11-15 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of automatic trim method of three-dimensional full machine numerical simulation |
| CN110472333A (en) * | 2019-08-15 | 2019-11-19 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of automatic trim method of dimensional airfoil numerical simulation |
| CN110550226A (en) * | 2019-09-17 | 2019-12-10 | 南京林业大学 | Structure optimization design method for small multi-rotor-wing plant protection unmanned aerial vehicle |
| CN111611652A (en) * | 2020-06-04 | 2020-09-01 | 电子科技大学 | Flapping wing aerodynamic characteristic analysis method based on active flexible deformation |
| CN112572822A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Method for determining spanwise gap of trailing edge control surface of high-aspect-ratio wing |
| CN112364442A (en) * | 2020-12-22 | 2021-02-12 | 北京机电工程研究所 | Bidirectional intelligent selection fluid-solid coupling analysis method |
| CN114611420A (en) * | 2022-02-10 | 2022-06-10 | 北京机电工程研究所 | Unsteady aerodynamic force calculation precision evaluation and correction method |
| CN114444214A (en) * | 2022-04-07 | 2022-05-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Aircraft control method based on control surface efficiency |
Non-Patent Citations (8)
| Title |
|---|
| 余永刚等: "飞翼布局气动外形设计", 《空气动力学学报》 * |
| 刘刚等: "混合网格方法在栅格翼数值模拟中的应用研究", 《空气动力学学报》 * |
| 宋晨等: "舵面结构参数化建模方法及气动弹性应用", 《飞机设计》 * |
| 李盾等: "带偏舵航天飞机的网格生成及流场数值模拟", 《舰船电子工程》 * |
| 王刚等: "非结构混合网格下的三维舵面流动计算研究", 《西北工业大学学报》 * |
| 王立强等: "战术导弹组合舵效数值仿真研究", 《弹箭与制导学报》 * |
| 袁武: "结构重叠网格方法在航天气动问题中的应用", 《系统仿真学报》 * |
| 贾忠湖等: "基于CFD的机翼损伤飞机再平衡问题研究", 《飞行力学》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115057001B (en) | 2023-03-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110727995B (en) | Blade shape construction method, blade, and computer device | |
| CN104881540B (en) | A kind of turbine air cooling accurate wall thickness control modeling method of blade and blade body inner mold | |
| CN108875177B (en) | Method for creating inland waterway dredging graph under single beam measuring point based on BIM model | |
| CN102446241B (en) | Wing surface structural rigidity simulation method | |
| US20100280802A1 (en) | Method of predicting the aerodynamic behavior of an aircraft element | |
| CN110188423A (en) | A kind of linear engineering structure fast B IM modeling method based on FEM meshing | |
| KR101730821B1 (en) | Modeling method for wind blade and apparatus using thereof | |
| CN112395794B (en) | Automatic parameterized slope model construction method based on subdivision technology | |
| CN109977526B (en) | Method for adjusting finite element model of wing based on three-dimensional CST technology | |
| CN108121837A (en) | A kind of 3-dimensional object formation of through-flow turbine runner blade | |
| Oliviu et al. | Analysis of the aerodynamic performance of a morphing wing-tip demonstrator using a novel nonlinear vortex lattice method | |
| CN115358001A (en) | Aerodynamic stealth comprehensive optimization method for front edge radius of flying wing layout aircraft | |
| CN115057001B (en) | Grid-based airfoil trailing edge control surface rapid generation and control effect evaluation method | |
| CN117473655A (en) | Aircraft simulation driving design method and device based on edge collapse grid optimization | |
| CN112199777A (en) | Method suitable for modeling bionic leading edge flow field characteristics | |
| Luers et al. | Adjoint-based volumetric shape optimization of turbine blades | |
| CN103608737A (en) | Adaptive machining method for smelted blades | |
| Chung et al. | Using additive manufactured parametric models for wind tunnel test-based aerodynamic shape optimization | |
| CN113626935B (en) | Design method of transonic moon-shaped wing with high cruising efficiency | |
| Iljaszewicz et al. | Aerodynamic analysis of the aircraft model made with the 3D printing method | |
| CN213180614U (en) | Flutter wind tunnel model of airplane winglet | |
| CN111079239B (en) | Bionic compressor blade grid modeling method | |
| Sóbester et al. | Airfoil design via cubic splines-Ferguson's curves revisited | |
| CN116702327A (en) | Pneumatic model partition grid construction method based on wing finite element grid model | |
| Lynch | Recent applications of advanced computational methods in the aerodynamic design of transport aircraft configurations |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |