CN-122020836-A - Control surface deflection method, system, equipment and medium based on structural grid

CN122020836ACN 122020836 ACN122020836 ACN 122020836ACN-122020836-A

Abstract

The embodiment of the specification provides a control surface deflection method, a system, equipment and a medium based on a structural grid, wherein the method comprises the steps of dividing an original structural grid for the appearance of an aircraft, reserving enough grid space near the control surface, simultaneously removing a rudder shaft connected with the control surface and the surface of the aircraft to separate the control surface from the surface of the aircraft, naming the structural grid near the control surface according to a preset naming rule, identifying the position and the boundary of the control surface based on naming information and face information in a grid file, establishing a three-dimensional Cartesian rectangular coordinate system, determining the rotation center, a rotation shaft, the rotation direction and the rotation angle of the deflection of a control surface grid node before and after the deflection, and reconstructing the spatial grid near the control surface according to the deflection deformation of the control surface grid node based on an overrun interpolation method to obtain the structural grid after the deflection of the control surface.

Inventors

LI KANGKANG
LIU YUWEI
LIU YAOFENG
MA JIKUI

Assignees

中国航天空气动力技术研究院

Dates

Publication Date: 20260512
Application Date: 20251224

Claims (10)

1. The control surface deflection method based on the structural grid is characterized by comprising the following steps of: S1, dividing an original structural grid aiming at the appearance of an aircraft, reserving enough grid space near a control surface, and simultaneously removing a rudder shaft connected with the control surface and the surface of the aircraft to separate the control surface from the surface of the aircraft; S2, naming the structural grids near the control surface according to a preset naming rule, and identifying the position and boundary of the control surface based on naming information and face information in a grid file; s3, establishing a three-dimensional Cartesian rectangular coordinate system, determining a rotation center, a rotation shaft, a rotation direction and a rotation angle of deflection of the control surface, and calculating deflection deformation of grid nodes of the control surface before and after deflection; s4, reconstructing a space grid near the control surface according to deflection deformation of the control surface grid nodes based on an overrun interpolation method to obtain a structural grid after the control surface is deflected.
2. The method of claim 1, wherein the specific requirement for reserving sufficient grid space near the control surface is to ensure that the control surface does not exceed the wrapping range of the grid near the control surface within the maximum deflection range.
3. The method of claim 1, wherein the three-dimensional cartesian coordinate system has an aircraft leading edge cusp as a coordinate origin O, an x-axis along a model flow direction, a y-axis along a normal direction, and a z-axis along a circumferential direction.
4. The method of claim 1, wherein the calculating deflection deformation of the control surface grid nodes before and after deflection specifically comprises: In the established coordinate system, a rotation center coordinate P1 (X1, Y1, Z1) of the deflection of the control surface is defined, according to a given rotation axis, rotation direction and rotation angle of the control surface, the anticlockwise rotation angle of the control surface around the Z axis is defined as theta 1, the coordinate of a certain grid node on the control surface before rotation is defined as P2 (X2, Y2, Z2), and the coordinate after anticlockwise rotation around the Z axis passing through the rotation center coordinate (X1, Y1, Z1) is defined as P3 (X3, Y3, Z3) after anticlockwise rotation angle of the control surface around the Z axis is defined as theta 1, and the calculation method is as follows: X3=(X2-X1)*COS(θ1)-(Y2-Y1)*SIN(θ1)+X1; Y3=(Y2-Y1)*COS(θ1)+(X2-X1)*SIN(θ1)+Y1; Z3=Z2; The deformation amount of the grid point before and after the deflection of the control surface at the point P2 is obtained by the following calculation: DX3= X3-X2; DY3= Y3-Y2; DZ3= Z3- Z2。
5. the method of claim 1, wherein the over-interpolation method comprises: determining the position of the control surface node in the structural grid according to IJK information corresponding to the control surface node; calculating the grid distance between the node and the corresponding boundary plane node; and calculating the deformation of the node and other nodes in the grid block where the node is positioned based on the distance proportion, and updating the coordinates of the node.
6. The method of claim 5, wherein the grid distance calculation formula is: ; wherein, (X4, Y4, Z4) is the boundary plane node coordinates, and (X5, Y5, Z5) is the node coordinates to be interpolated.
7. The method of claim 1, wherein the method for reconstructing the spatial grid near the control surface according to the deflection deformation of the control surface grid node based on the overrun interpolation method comprises the following specific steps of: according to the overrun method, the calculation method for obtaining the deflection grid variation (DX 5, DY5, DZ 5) corresponding to the P5 point is as follows: ; The same processing mode is carried out on the control surface position in any IJK direction, the processing is carried out according to the sequence, the grid variation (DX 5, DY5, DZ 5) of any point P5 (X5, Y5, Z5) in all control surfaces and control surface corresponding grid blocks is obtained, and then grid coordinate point information P6 (X6, Y6, Z6) after deflection deformation is obtained, wherein the calculation method is as follows: X6= X5+DX5; Y6= Y5+DY5; Z6= Z5+DZ5。
8. a structural grid-based control surface deflection system, comprising: The grid division module is used for dividing an original structural grid aiming at the appearance of the aircraft, reserving enough grid space near the control surface, and removing a rudder shaft connected with the control surface and the surface of the aircraft to separate the control surface from the surface of the aircraft; The control surface identification module is used for naming the structural grids near the control surface according to a preset naming rule and identifying the position and boundary of the control surface based on naming information and face information in the grid file; The deflection amount calculation module is used for establishing a three-dimensional Cartesian rectangular coordinate system, determining the rotation center, the rotation shaft, the rotation direction and the rotation angle of the deflection of the control surface, and calculating the deflection deformation amount of grid nodes of the control surface before and after the deflection; and the grid reconstruction module is used for reconstructing the space grid near the control surface according to the deflection deformation of the grid nodes of the control surface based on the overrun interpolation method to obtain the structural grid after the deflection of the control surface.
9. An electronic device, comprising: Processor, and A memory arranged to store computer executable instructions which when executed cause the processor to implement the steps of the structural grid-based control surface deflection method according to any one of claims 1 to 7.
10. A storage medium storing computer-executable instructions which, when executed, implement the steps of the structural grid-based control surface deflection method of any one of claims 1 to 7.

Description

Control surface deflection method, system, equipment and medium based on structural grid Technical Field The present document relates to the field of computational fluid technologies, and in particular, to a control surface deflection method, system, device, and medium based on a structural grid. Background With the development of computational fluid dynamics (Computation of Fluid Dynamics CFD for short), numerical simulation has been used in aspects of complex flow mechanism research, aerodynamic characteristics analysis, and the like. Structural grid motion techniques have evolved over decades in numerical simulations to form a number of effective solutions, among which: The rigid moving grid technology is the simplest structural grid movement mode, the whole calculation area grid moves rigidly along with the object, the grid does not need to be regenerated, the calculation amount of the method is small, the initial grid quality can be perfectly maintained, the method is only suitable for the integral movement of single rigid movement, in addition, the whole grid comprises far field boundaries which are all moving, so that the far field boundaries are difficult to process, and the application of the method in the unsteady simulation of simple shapes is limited. The overlapped grid technology, also called as 'nested grid', is a new method for processing complex motion problems, and is characterized in that a calculation domain is decomposed into a plurality of subdomains, each subdomain independently generates a structural grid, and the subdomains realize integral solution through information exchange of an overlapped area, however, the overlapped grids need to update interpolation relation and process flux conservation at each time step, so that the calculated amount is large, and interpolation errors are possibly introduced. The overrun interpolation dynamic grid technology provides a flexible algebraic grid generation path when the boundary motion is complex, and can directly generate full-field grid point coordinates through interpolation functions according to new positions of motion boundaries, so that the calculation amount is small, and complex boundary motion can be processed. Based on the technical research, in combination with a laboratory self-research program, it is expected to develop a control surface deflection grid strategy based on a structural grid, and a numerical simulation convergence result of the problem can be obtained in a more convenient and efficient calculation mode. Disclosure of Invention One or more embodiments of the present disclosure provide a control surface deflection method based on a structural grid, including: S1, dividing an original structural grid aiming at the appearance of an aircraft, reserving enough grid space near a control surface, and simultaneously removing a rudder shaft connected with the control surface and the surface of the aircraft to separate the control surface from the surface of the aircraft; S2, naming the structural grids near the control surface according to a preset naming rule, and identifying the position and boundary of the control surface based on naming information and face information in a grid file; s3, establishing a three-dimensional Cartesian rectangular coordinate system, determining a rotation center, a rotation shaft, a rotation direction and a rotation angle of deflection of the control surface, and calculating deflection deformation of grid nodes of the control surface before and after deflection; s4, reconstructing a space grid near the control surface according to deflection deformation of the control surface grid nodes based on an overrun interpolation method to obtain a structural grid after the control surface is deflected. Further, the specific requirement of reserving enough grid space near the control surface is that the control surface does not exceed the wrapping range of grids near the control surface within the maximum deflection range. Further, the three-dimensional Cartesian rectangular coordinate system takes the sharp point of the front edge of the aircraft as the origin of coordinates O, the x axis is along the flow direction of the model, the y axis is along the normal direction, and the z axis is along the circumferential direction. Further, the deflection deformation of the control surface grid nodes before and after deflection is calculated specifically as follows: In the established coordinate system, a rotation center coordinate P1 (X1, Y1, Z1) of the deflection of the control surface is defined, according to a given rotation axis, rotation direction and rotation angle of the control surface, the anticlockwise rotation angle of the control surface around the Z axis is defined as theta 1, the coordinate of a certain grid node on the control surface before rotation is defined as P2 (X2, Y2, Z2), and the coordinate after anticlockwise rotation around the Z axis passing through the rotation center coordinate