Aerodynamic configuration design optimization method and device based on geometric material mechanical deformation

Abstract

The present application relates to a method and device for optimizing aerodynamic configuration design based on the mechanical deformation of geometric materials. The method comprises: constructing a simply supported beam system based on the busbar of the original aerodynamic configuration and performing a force analysis on any deformed microelement in the simply supported beam system after deformation, obtaining the moment, shear force, normal stress and uniformly distributed load applied to the deformed microelement, and jointly solving the equilibrium equation, geometric equation and physical equation to obtain the displacement field function of the deformed microelement, and adjusting at least one variable in the displacement field function to produce continuous geometric changes, thereby obtaining a new simply supported beam system, and using the new simply supported beam system as a new busbar to obtain a new aerodynamic configuration. This method can affect the deformation of the global aerodynamic configuration according to the changes in a certain local microelement, and can achieve complex deformation and optimization of the aerodynamic configuration by adjusting fewer variables.

Description

Technical Field

[0001] The present application relates to the technical field of aerodynamic configuration design, and in particular to a method and device for optimizing aerodynamic configuration design based on the mechanical deformation of geometric materials. Background Art

[0002] In aerodynamics, aerodynamic configuration determines the aerodynamic performance of a geometric body. For example, in the external flow domain, the shape of a missile's warhead, interstage, body, wings, and other structures directly influences the lift-to-drag ratio of the entire missile. Geometric aerodynamic configuration is equally important for internal flow. For example, in the design of an air-breathing engine, the geometry of the inlet, the configuration of the isolating section, the shape of the engine blades including the turbomachinery, the layout of the combustion chamber, and the control lines of the tail nozzle all rely on geometric modeling.

[0003] Existing aerodynamic configuration design often uses parametric methods. For the shaping of complex surfaces, multiple cross-sections can be combined according to certain control rules. Parametric methods can be further divided into line parameterization and surface parameterization. Commonly used parametric methods include Ferguson parametric cubic curves, Ferguson spline surfaces, tensor product surfaces, parametric polynomial interpolation surfaces, parametric bicubic patches, Coons bicubic spline surfaces, parametric bicubic spline surfaces, Bezier curves and surfaces, B-spline curves and surfaces (including uniform B-splines, quasi-uniform B-splines, and non-uniform B-splines), rational Bezier curves and surfaces, rational B-spline curves and surfaces, and many other forms. In addition, there are free-form deformation methods (FFD). The basic idea is to achieve deformation by manipulating a spatial parallel lattice containing the object. The manipulated spatial lattice determines the object's deformation function, which specifies the new position of each point on the object. However, it is difficult for FFD to accurately complete the deformation according to the designer's intention. For example, it is difficult to use FFD to achieve the accurate movement of a point from its original position to its designed position.

[0004] Existing aerodynamic configuration design techniques require more control variables to achieve configurations with high design freedom. The more control variables there are, the more complex and computationally intensive the optimization process becomes, and even unreasonable configurations may result. In addition, the constraint changes between control points need to be given separately, which cannot meet the needs of practical applications. Summary of the Invention

[0005] Based on this, it is necessary to provide an aerodynamic configuration design optimization method and device based on the mechanical deformation of geometric materials to address the above technical problems.

[0006] A method for optimizing aerodynamic configuration design based on mechanical deformation of geometric materials, the method comprising:

[0007] A simply supported beam system is constructed based on the busbar of the original aerodynamic configuration. One end of the simply supported beam system is clamped, and the other end of the simply supported beam system is deformed by external forces.

[0008] Perform force analysis on any deformed microelement in the simply supported beam system to obtain the moment, shear force, normal stress and uniform load applied to the deformed microelement. Describe the relationship between the moment, shear force, normal stress and uniform load based on the equilibrium equation.

[0009] The strain of the deformed element is calculated based on the geometric equation and the deformation geometric relationship and curvature of the deformed element. The relationship between the uniformly distributed load and the deflection function of the deformed element is calculated based on the strain and the physical equation. The displacement field function of the deformed element is calculated based on the relationship between the strain and the uniformly distributed load and the deflection function of the deformed element. The displacement field function refers to the displacement of the deformed element in the vertical direction when it is affected by an external force.

[0010] A new simply supported beam system is obtained by adjusting at least one variable in the displacement field function to generate continuous geometric changes. The new simply supported beam system is used as a new busbar to obtain a new aerodynamic configuration.

[0011] In one embodiment, the external force acting on the simply supported beam system includes at least concentrated force, uniform force and non-uniform force.

[0012] In one embodiment, a force analysis is performed on any deformed microelement in the deformed simply supported beam system to obtain the moment, shear force, normal stress, and uniformly distributed load applied to the deformed microelement. The relationship between the moment, shear force, normal stress, and uniformly distributed load is described according to the equilibrium equation, including:

[0013] According to the classical plate theory and small deformation theory, an arbitrary deformed microelement with a length of dx in the deformed simply supported beam system is selected for force analysis to obtain the moment, shear force, normal stress and uniformly distributed load applied to the deformed microelement.

[0014] The equilibrium equation is used to describe the relationship between moment, shear force, normal stress and uniform load, which is expressed as

[0015]

[0016] dQ+p(x)·dx=0

[0017] dM-Qdx=0

[0018] Where M represents the moment, Q represents the shear force, and σ xrepresents the normal stress in the horizontal direction, p(x) represents the uniform load, dQ represents the increase in shear force, and dM represents the increase in moment. represents the deflection, and dA represents the infinitesimal area in the deflection direction of the neutral layer.

[0019] In one embodiment, the strain of the deformed micro-element is obtained by calculating according to the geometric equation and the deformation geometric relationship and curvature of the deformed micro-element, including:

[0020] According to the deformation direction and coordinate position of the deformed microelement, the layer with a deformation variable of 0 in the deformed microelement is defined as the neutral layer. According to the geometric equation and the deformation geometric relationship of the neutral layer, the strain expression of the neutral layer is obtained, which is expressed as

[0021]

[0022] Where R represents the radius of curvature of the neutral layer, and dθ represents the arc value corresponding to the neutral layer;

[0023] According to the curvature radius R of the neutral layer and the deflection function of the neutral layer Calculation is performed to obtain the curvature of the neutral layer, which is expressed as

[0024]

[0025] Where dS represents the length of the neutral layer, Respectively The corresponding first-order derivative and second-order derivative, v represents the deflection function of the deformed microelement;

[0026] According to the strain expression and curvature, the strain of the deformed microelement is obtained, which is expressed as

[0027]

[0028] In one embodiment, the relationship between the uniformly distributed load and the elastic modulus of the deformed microelement is obtained by calculation based on the strain and the physical equation, including:

[0029] According to the strain of the deformed microelement and the physical equation, the normal stress σ in the horizontal direction is obtained. x The relationship between the deflection function v of the deformed microelement is expressed as

[0030]

[0031] Where E represents the elastic modulus of the deformed microelement;

[0032] According to σ xThe relationship between the uniform load and the deflection function of the deformed microelement is calculated by the simultaneous equilibrium equations of the moment of inertia of the cross section of the deformed microelement, which is expressed as

[0033]

[0034] in, Represents the moment of inertia of the cross section of the deformed element.

[0035] In one embodiment, the displacement field function of the deformed micro-element is obtained by calculating the relationship between the strain, the uniformly distributed load, and the deflection function of the deformed micro-element, including:

[0036] According to the simultaneous equilibrium equations of the strain variables of the deformed micro-element, the relationship between the moment and the deflection function of the deformed micro-element is obtained, which is expressed as

[0037]

[0038] The displacement field function of the deformed micro-element is obtained by calculating the relationship between the moment and the deflection function of the deformed micro-element and the relationship between the uniformly distributed load and the deflection function of the deformed micro-element.

[0039] In one embodiment, the displacement field function of the deformed micro-element is obtained by calculating the relationship between the moment and the deflection function of the deformed micro-element in combination with the relationship between the uniformly distributed load and the deflection function of the deformed micro-element, including:

[0040] According to the relationship between the moment and the deflection function of the deformed microelement, combined with the relationship between the uniformly distributed load and the deflection function of the deformed microelement, the displacement field function to be solved is obtained, which is expressed as

[0041]

[0042] Among them, c0, c1, c1, c3 represent the coefficients to be determined, p0 represents the load, and x represents the abscissa of the deformed microelement;

[0043] According to the boundary conditions of the simply supported beam system, the coefficients to be solved are determined, and the displacement field function of the deformed microelement is obtained, which is expressed as

[0044]

[0045] Where l is the length of the simply supported beam system.

[0046] In one embodiment, the boundary conditions of the simply supported beam system are expressed as

[0047] v| x＝0 =0

[0048] v|x＝l =0

[0049] M| x＝0 =0

[0050] M| x＝l =0

[0051] Among them, v| x＝0 = 0 represents the deflection function of the simply supported beam system at x = 0, v| x＝l = 0 represents the deflection function of the simply supported beam system at x = l, M| x＝0 = 0 represents the moment at x = 0 of the simply supported beam system, M| x＝l =0 represents the moment at x=l in the simply supported beam system.

[0052] An aerodynamic configuration design optimization device based on the mechanical deformation of geometric materials, the device comprising:

[0053] The simply supported beam system construction module is used to construct a simply supported beam system based on the busbar of the original aerodynamic configuration. One end of the simply supported beam system is clamped, and the other end of the simply supported beam system is deformed by external forces.

[0054] The force analysis module is used to perform force analysis on any deformed microelement in the deformed simply supported beam system, obtain the moment, shear force, normal stress and uniform load applied to the deformed microelement, and describe the relationship between the moment, shear force, normal stress and uniform load according to the equilibrium equation;

[0055] The displacement field function calculation module is used to calculate the strain of the deformed microelement based on the geometric equation and the deformation geometric relationship and curvature of the deformed microelement; the relationship between the uniformly distributed load and the deflection function of the deformed microelement is calculated based on the strain and physical equation; and the displacement field function of the deformed microelement is calculated based on the relationship between the strain and the uniformly distributed load and the deflection function of the deformed microelement; wherein the displacement field function refers to the displacement of the deformed microelement in the vertical direction when the deformed microelement is affected by an external force;

[0056] The aerodynamic configuration generation module is used to generate continuous geometric changes by adjusting at least one variable in the displacement field function to obtain a new simply supported beam system, and use the new simply supported beam system as a new busbar to obtain a new aerodynamic configuration.

[0057] The above-mentioned aerodynamic configuration design optimization method and device based on the mechanical deformation of geometric materials constructs a simply supported beam system based on the generatrix of the original aerodynamic configuration and performs a force analysis on any deformed microelement in the deformed simply supported beam system to obtain the moment, shear force, normal stress and uniformly distributed load applied to the deformed microelement. The displacement field function of the deformed microelement is obtained by jointly solving the equilibrium equation, geometric equation and physical equation. The displacement field function represents the vertical displacement of the deformed microelement when affected by an external force. By adjusting at least one variable in the displacement field function to produce continuous geometric changes, a new simply supported beam system is obtained. The new simply supported beam system is used as a new generatrix to obtain a new aerodynamic configuration. Compared with the existing technology, the method proposed by the present invention does not require the aerodynamic configuration to be geometrically parameterized in advance, thus avoiding the errors caused by traditional parameterization methods in the process of reconstructing the optimization object. It also does not require additional constraints and breaks away from the many limitations of structural parameterization.

[0058] Through the aerodynamic configuration design optimization method proposed in the present invention, the change of the global aerodynamic configuration can be affected by the change of a certain local microelement, and the curvature continuity is always satisfied and many interfering shapes are eliminated. In addition, when generating a new simply supported beam system, there are fewer variables that need to be adjusted and controlled in the displacement field function. When it comes to the aerodynamic configuration of complex structures, the advantages are more obvious. BRIEF DESCRIPTION OF THE DRAWINGS

[0059] Figure 1 is a schematic diagram of a deformation body in one embodiment;

[0060] Figure 2 1 is a flow chart of an aerodynamic configuration design optimization method based on geometric material mechanical deformation in one embodiment;

[0061] Figure 3 Schematic diagram of force analysis of any deformed microelement of a plane pure bending simply supported beam system according to one embodiment: (a) is the plane pure bending simply supported beam system, (b) is the deformed microelement for force analysis;

[0062] Figure 4 is a simplified diagram of a deformable microelement used for displacement analysis in one embodiment;

[0063] Figure 5 Schematic diagram comparing the impeller geometry before and after deformation in one embodiment;

[0064] Figure 6 Schematic diagram of blade profile comparison in different blade height directions in one embodiment;

[0065] Figure 7 Schematic diagram of a turbine blade cascade using the "FAITH" end wall forming method in one embodiment;

[0066] Figure 8 A hub surface diagram parameterized by a cubic B-spline curve in one embodiment;

[0067] Figure 9 Schematic diagram of the geometric modeling area in one embodiment. DETAILED DESCRIPTION

[0068] In order to make the purpose, technical solutions and advantages of this application more clear, the following further describes this application in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this application and are not intended to limit this application.

[0069] The present invention provides an aerodynamic configuration design optimization method based on the mechanical deformation of geometric materials, the principle of which is as follows: Figure 1 As shown, it is assumed that curve 0 is the original aerodynamic configuration busbar of a certain optimization object. The busbar of the original aerodynamic configuration is adjusted and optimized. It is known that the performance of the optimization object can be improved by bending the busbar downward to a certain extent, and the busbar after adjustment needs to maintain curvature continuity. The technical method proposed in the present invention converts the optimization problem of the aerodynamic configuration into a problem of geometric mechanics of a deformable body. The busbar of the original aerodynamic configuration is regarded as a simply supported beam, and a fixed constraint is adopted on one end face. The new configuration applies a certain amount of force on its upper surface or end point, and the simply supported beam will produce a certain deformation. The deformed shape structure is used as the new busbar of the optimization object to obtain the geometric configuration under the expected local change. Different expected shape structures can be obtained by different magnitudes and directions of the loading force. In the problem exemplified in this example, the generation of the new busbar of the optimization object only requires adjusting a single variable F to obtain different families of curves, such as Figure 1 Curve 1 and Curve 2 in .

[0070] In one embodiment, Figure 2 As shown, a method for aerodynamic configuration design optimization based on the mechanical deformation of geometric materials is provided, comprising the following steps:

[0071] Step 202 : constructing a simply supported beam system based on the busbar of the original aerodynamic configuration; wherein one end face of the simply supported beam system is fixedly constrained, and the other end of the simply supported beam system is deformed by an external force.

[0072] It can be understood that different shapes are achieved by selecting different constraint methods for the end face of one end of the simply supported beam system, and the other end of the simply supported beam system is deformed by different external forces. The loading method of the external force is not limited, such as concentrated force, uniform force, non-uniform force, etc., and the magnitude of the external force and the point of action applied to the simply supported beam system are not limited.

[0073] Step 204, perform a force analysis on any deformed element in the deformed simply supported beam system to obtain the moment, shear force, normal stress and uniform load applied to the deformed element, and describe the relationship between the moment, shear force, normal stress and uniform load according to the equilibrium equation.

[0074] Step 206, calculate based on the geometric equation and the deformation geometric relationship and curvature of the deformed microelement to obtain the strain of the deformed microelement; calculate based on the strain and the physical equation to obtain the relationship between the uniformly distributed load and the deflection function of the deformed microelement; calculate based on the relationship between the strain and the uniformly distributed load and the deflection function of the deformed microelement to obtain the displacement field function of the deformed microelement; wherein the displacement field function refers to the displacement of the deformed microelement in the vertical direction when the deformed microelement is affected by an external force.

[0075] It can be understood that the displacement field function is a "deformation" function that affects the deformation of the simply supported beam system. By analyzing the loaded geometric body and using equilibrium equations, physical equations, and geometric equations, the displacement field function of the geometric body can be solved. This is equivalent to solving the change amount given to the geometric body by adjusting the parameters in the parametric modeling process to achieve the deformation of the geometric body.

[0076] Step 208 : A new simply supported beam system is obtained by adjusting at least one variable in the displacement field function to generate a continuous geometric change. The new simply supported beam system is used as a new busbar to obtain a new aerodynamic configuration.

[0077] The above-mentioned aerodynamic configuration design optimization method based on the mechanical deformation of geometric materials can affect the change of the global aerodynamic configuration according to the change of a local microelement through the aerodynamic configuration design optimization method proposed by the present invention, and always meets the curvature continuity and eliminates many interfering shapes. In addition, when generating a new simply supported beam system, there are fewer variables that need to be adjusted and controlled in the displacement field function. When it comes to the aerodynamic configuration of complex structures, the advantages are more obvious.

[0078] In one embodiment, a plane pure bending simply supported beam system is constructed based on the busbar of a certain original aerodynamic configuration. One end face of the simply supported beam system is fixedly constrained, and the other end of the simply supported beam system is deformed by an external force, such as Figure 3 As shown in (a), the length, width and height of the simply supported beam system are l, b, and h respectively, and the uniformly distributed load it receives is p(x). Figure 3As shown in Figure (b), based on classical plate theory (Kirchhoff-Love) and small deformation theory, a deformed element "dx-bh" with a length of dx, a width of b, and a height of h in the deformed simply supported beam system is selected for force analysis. The moment M, shear force Q, normal stress σ, and the uniformly distributed load p(x) applied to the deformed element are obtained. Furthermore, the shear force and moment increases in the corresponding directions are dQ and dM, respectively. Since the simply supported beam is a slender structure, its displacement field can be expressed with respect to the horizontal x-direction. Meanwhile, the deformation is concentrated in the vertical y-direction, so the deflection is used to describe the displacement in the y-direction.

[0079] First, the relationship between moment, shear force, normal stress and uniform load is described according to the equilibrium equation. The resultant force of the deformed microelement in the x and y directions is balanced and the moment is balanced, which is expressed as

[0080]

[0081] dQ+p(x)·dx=0(2)

[0082] dM-Qdx=0(3)

[0083] Among them, σ x represents the normal stress in the horizontal direction, represents the deflection, and dA represents the infinitesimal area in the deflection direction of the neutral layer.

[0084] Then according to Figure 4 The deformation element used for displacement analysis is analyzed, where O represents the center of the deformation element. According to the deformation direction and coordinate position of the deformation element, the layer with a deformation variable of 0 in the deformation element is defined as the neutral layer. According to the geometric equation and the deformation geometric relationship of the neutral layer, the strain expression of the neutral layer is obtained, which is expressed as

[0085]

[0086] Where R represents the radius of curvature of the neutral layer, and dθ represents the arc value corresponding to the neutral layer;

[0087] Then, from the relationship between the curvature radius R and the curvature κ, we get Equation 5:

[0088]

[0089] Where, dS represents the length of the neutral layer;

[0090] Combined with the mathematical expression for the definition of curvature, such as Equation 6:

[0091]

[0092] in, represents the deflection function of the neutral layer, Respectively The corresponding first-order derivative and second-order derivative, v represents the deflection function of the deformed element.

[0093] Then, according to the strain expression and curvature obtained above, we solve equations (4), (5), and (6) together to obtain the strain of the deformed microelement, which is expressed as

[0094]

[0095] Then consider the moment of inertia of the cross section of the deformed microelement, as shown in formula (8):

[0096]

[0097] The physical equation in elastic mechanics, the one-dimensional Hooke's law, is superimposed on the strain of the deformed microelement to calculate the normal stress σ in the horizontal direction. x The relationship between the deflection function v of the deformed microelement is expressed as

[0098]

[0099] Where E represents the elastic modulus of the deformed microelement;

[0100] Then according to σ x The relationship between v and the moment of inertia of the deformed microelement section is calculated by simultaneous equilibrium equations. Substituting equations (1), (3), (8), and (9) into equation (2), the relationship between the uniformly distributed load and the deflection function of the deformed microelement is obtained, which is expressed as

[0101]

[0102] Then, the strain equations of the deformed microelement are calculated by combining equations (1) and (7-9), and the relationship between the moment and the deflection function of the deformed microelement is obtained, which is expressed as

[0103]

[0104] Then, the calculation is performed based on the relationship between the moment and the deflection function of the deformed microelement and the relationship between the uniformly distributed load and the deflection function of the deformed microelement.

[0105] Specifically, according to the ordinary differential equation of formula (10), the general solution is deduced to obtain the displacement field function to be solved, which is expressed as

[0106]

[0107] Among them, c0, c1, c1, c3 represent the coefficients to be determined, p0 represents the load, and x represents the abscissa of the deformed microelement;

[0108] Finally, the above-mentioned unknown coefficients are determined according to the boundary conditions of the simply supported beam system, and the displacement field function of the deformed microelement is obtained, which is expressed as

[0109]

[0110] Among them, the boundary conditions of the simply supported beam system, that is, the deflection and torque at the support of the simply supported beam are 0, are expressed as

[0111]

[0112]

[0113] Among them, v| x＝0 = 0 represents the deflection function of the simply supported beam system at x = 0, v| x＝l = 0 represents the deflection function of the simply supported beam system at x = l, M| x＝0 = 0 represents the moment at x = 0 of the simply supported beam system, M| x＝l =0 represents the moment at x=l in the simply supported beam system.

[0114] According to the above derivation process, it can be known that, firstly, according to the method proposed in the present invention, continuous geometric changes can be achieved by changing at least one variable in the displacement field function. For example, when the elastic modulus E and the moment of inertia I of the simply supported beam are fixed values, the continuous geometric changes of the simply supported beam can be achieved by changing the load p0. Even when faced with a simply supported beam system with a complex structure, the displacement field function can be solved through the above process, and the variables that need to be adjusted in the displacement field function will not be too many, which greatly reduces the computational complexity and has obvious advantages. Secondly, according to the above displacement field function, it can be ensured that the generated new geometric body is second-order continuous in curvature, which is very important for applications such as aerodynamic configurations and shapes that have strict requirements on curvature changes.

[0115] Specifically, in the process of optimizing the impeller profile of a centrifugal compressor, the present invention adopts the impeller profile generated by the above-mentioned aerodynamic configuration design optimization method based on the mechanical deformation of geometric materials, and the compressor performance is greatly improved. The centrifugal compressor is a key compression component of a certain type of turbojet engine. In order to solve the problem of excessive inlet angle of attack in the tip area of ​​the compressor, a new configuration is generated in the blade pressure surface area by the above-mentioned method, such as Figure 5 As shown in Figure 1, the deformation after the external force is applied is compared with the original configuration. Combined with the optimization algorithm, the relationship between the deformation force and the compressor design point performance is studied, as shown in Table 1. Among them, the comparison of the different blade height section deformation of case 2 and case 3 is shown in Table 1. Figure 6As shown, to achieve the same parameterized geometry, the traditional parameterization method is generally to superimpose the thickness distribution through the mid-arc line, and at the same time, to establish multiple parametric expressions of the blade profile in the blade height direction, which is far more than one parameter. This is significantly different from the present invention's proposal that only at least one parameter in the displacement field function needs to be adjusted to achieve the expected deformation result of the aerodynamic configuration.

[0116] Table 1 Typical cases and optimization results

[0117] Serial number Traffic changes Efficiency changes Pressure ratio change 1 11.4％ 2.7％ 1.0％ 2 13.7％ 3.5％ 1.7％ 3 15.3％ 4.0％ 2.5％ 4 17.4％ 4.2％ 3.1％ 5 15.6％ 3.5％ 2.1％ 6 13.9％ 2.5％ 0.7％

[0118] The method proposed in the present invention is further used in the design of the end wall of the blade channel. For the typical separation flow control in the blade channel, the expected geometric configuration change direction of the sensitive position is given. It is necessary to realize a concave or convex structure on one side of the suction surface angle zone to destroy the separation vortex structure in the angle zone. The application research on non-axisymmetric end walls is relatively extensive. The parameter optimization design methods currently used are generally traditional methods such as Fourier series, trigonometric functions, and B-spline curves. For example, Rolls-Royce of the United Kingdom proposed the "FAITH" end wall forming method in cooperation with Durham University in the early 21st century. In this method, the circumferential modeling function uses the first three terms in the Fourier series, and the axial modeling function is a B-spline curve determined by six control points. The final non-axisymmetric end wall shape is as follows: Figure 7 shown.

[0119] In the process of flow channel description and parameterization, the geometric surface is basically expressed as a combination of key curves and certain constraints, such as Figure 8 The figure shows the hub surface parameterized using a cubic B-spline curve. During the optimization design, there are 16 free-moving points. To maintain curvature continuity and geometric parameter discontinuity, additional constraints are required on the geometric relationships between the free-moving points and endpoints, further increasing the complexity of the complex parameterization.

[0120] In the process of optimizing the cascade flow passage of a typical waiting angle separation flow, the sensitive area on the suction side is selected as the parameterized area, such as Figure 9 The purpose is to study the effects of different concave-convex shapes on the diagonal separation flow of the non-axisymmetric end wall. This process is achieved using the method proposed in this paper. Simply adjusting the direction of the applied force, without the need for pre-parameterization of the flow channel, can achieve "concave-convex" shapes in different regions.

[0121] Table 2 provides information and final results for several typical cases. It shows that for the key evaluation parameters of the cascade, total pressure loss and static pressure rise coefficient, the optimal configuration, Case 4, reduced total pressure loss by 7.5% and increased the static pressure rise coefficient by 20.1%, significantly improving the functionality of the cascade.

[0122] Table 2 Comparison of optimization results of typical cases

[0123]

[0124] The above two typical application cases show that for basic aerodynamic configurations, the method proposed in this invention can be used to quickly generate optimized alternative configurations, and ultimately achieves very good results. Compared with other parameterization methods, the two most important advantages of the method proposed in this invention are that there is no need to parameterize the original configuration or the optimization object; secondly, complex deformations can be achieved with fewer variables, and theoretical derivation shows that the new configuration is continuous in curvature. Based on the above application cases, it can be seen that this method has certain potential in the field of aerodynamic configuration optimization design.

[0125] It should be understood that although Figure 2 The steps in the flowchart are shown in sequence as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. In addition, Figure 2 At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least part of the sub-steps or stages of other steps.

[0126] In one embodiment, an aerodynamic configuration design optimization device based on the mechanical deformation of geometric materials is provided, comprising: a simply supported beam system construction module, a force analysis module, a displacement field function calculation module, and an aerodynamic configuration generation module, wherein:

[0127] The simply supported beam system construction module is used to construct a simply supported beam system based on the busbar of the original aerodynamic configuration. One end of the simply supported beam system is clamped, and the other end of the simply supported beam system is deformed by external forces.

[0128] The force analysis module is used to perform force analysis on any deformed microelement in the deformed simply supported beam system, obtain the moment, shear force, normal stress and uniform load applied to the deformed microelement, and describe the relationship between the moment, shear force, normal stress and uniform load according to the equilibrium equation;

[0129] The displacement field function calculation module is used to calculate the strain of the deformed microelement based on the geometric equation and the deformation geometric relationship and curvature of the deformed microelement; the relationship between the uniformly distributed load and the deflection function of the deformed microelement is calculated based on the strain and physical equation; and the displacement field function of the deformed microelement is calculated based on the relationship between the strain and the uniformly distributed load and the deflection function of the deformed microelement; wherein the displacement field function refers to the displacement of the deformed microelement in the vertical direction when the deformed microelement is affected by an external force;

[0130] The aerodynamic configuration generation module is used to generate continuous geometric changes by adjusting at least one variable in the displacement field function to obtain a new simply supported beam system, and use the new simply supported beam system as a new busbar to obtain a new aerodynamic configuration.

[0131] Regarding the specific definition of the aerodynamic configuration design optimization device based on the mechanical deformation of geometric materials, please refer to the definition of the aerodynamic configuration design optimization method based on the mechanical deformation of geometric materials above, and will not be repeated here. The various modules in the above-mentioned aerodynamic configuration design optimization device based on the mechanical deformation of geometric materials can be implemented in whole or in part through software, hardware, and their combination. The above-mentioned modules can be embedded in or independent of the processor in the computer device in the form of hardware, or can be stored in the memory of the computer device in the form of software, so that the processor can call and execute the corresponding operations of the above-mentioned modules.

[0132] The technical features of the above embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0133] The above-described embodiments merely represent several implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that a person skilled in the art could make various modifications and improvements without departing from the spirit of the present application, all of which fall within the scope of protection of the present application. Therefore, the scope of protection of the present patent application shall be determined by the appended claims.

Claims

1. A method for optimizing aerodynamic configuration design based on mechanical deformation of geometric materials, characterized in that: The method comprises: A simply supported beam system is constructed based on the busbar of the original aerodynamic configuration; wherein one end face of the simply supported beam system is clamped, and the other end of the simply supported beam system is deformed by an external force; Performing a force analysis on any deformed microelement in the simply supported beam system after deformation to obtain the moment, shear force, normal stress and uniformly distributed load applied to the deformed microelement, and describing the relationship between the moment, shear force, normal stress and uniformly distributed load according to an equilibrium equation; Calculating based on the geometric equation and the deformation geometric relationship and curvature of the deformed microelement to obtain the strain of the deformed microelement; calculating based on the strain and the physical equation to obtain the relationship between the uniformly distributed load and the deflection function of the deformed microelement; calculating based on the strain and the relationship between the uniformly distributed load and the deflection function of the deformed microelement to obtain the displacement field function of the deformed microelement; wherein the displacement field function refers to the displacement of the deformed microelement in the vertical direction when the deformed microelement is affected by an external force; A new simply supported beam system is obtained by adjusting at least one variable in the displacement field function to generate continuous geometric changes. The new simply supported beam system is used as a new busbar to obtain a new aerodynamic configuration.

2. The method according to claim 1, characterized in that The external forces acting on the simply supported beam system include at least concentrated force, uniform force and non-uniform force.

3. The method according to claim 1, characterized in that Performing a force analysis on any deformed microelement in the simply supported beam system after deformation to obtain the moment, shear force, normal stress, and uniformly distributed load applied to the deformed microelement, and describing the relationship between the moment, shear force, normal stress, and uniformly distributed load according to the equilibrium equation, including: According to the classical plate theory and small deformation theory, a deformed microelement of any length dx in the simply supported beam system after deformation is selected for force analysis to obtain the moment, shear force, normal stress and uniformly distributed load applied to the deformed microelement; The relationship between the moment, shear force, normal stress and uniform load is described by the equilibrium equation, which is expressed as dQ+p(x)·dx=0 dM-Qdx=0 Where M represents the moment, Q represents the shear force, and σ x represents the normal stress in the horizontal direction, p(x) represents the uniform load, dQ represents the increase in shear force, and dM represents the increase in moment. represents the deflection, and dA represents the infinitesimal area in the deflection direction of the neutral layer.

4. The method according to claim 3, characterized in that The strain of the deformed micro-element is obtained by calculating according to the geometric equation and the deformation geometric relationship and curvature of the deformed micro-element, including: According to the deformation direction and coordinate position of the deformed microelement, a layer with a deformation variable of 0 in the deformed microelement is defined as the neutral layer. According to the geometric equation and the deformation geometric relationship of the neutral layer, the strain expression of the neutral layer is obtained, which is expressed as: Wherein, R represents the curvature radius of the neutral layer, and dθ represents the arc value corresponding to the neutral layer; According to the curvature radius R of the neutral layer and the deflection function of the neutral layer Calculation is performed to obtain the curvature of the neutral layer, which is expressed as Where dS represents the length of the neutral layer, Respectively The corresponding first-order derivative and second-order derivative, v represents the deflection function of the deformed microelement; According to the strain expression and curvature, the strain of the deformed microelement is calculated and expressed as 5. The method according to claim 4, characterized in that Calculating based on the strain and the physical equation to obtain the relationship between the uniformly distributed load and the elastic modulus of the deformed microelement includes: According to the strain of the deformed microelement and the physical equation, the normal stress σ in the horizontal direction is obtained. x The relationship between the deflection function v of the deformed microelement is expressed as Wherein, E represents the elastic modulus of the deformed microelement; According to σ x The relationship between the uniform load and the deflection function of the deformed microelement is calculated by using the relationship between v and the moment of inertia of the deformed microelement section, and the relationship between the uniform load and the deflection function of the deformed microelement is obtained, which is expressed as in, Represents the moment of inertia of the cross section of the deformed element.

6. The method according to claim 5, characterized in that The displacement field function of the deformed microelement is obtained by calculating according to the relationship between the strain, the uniformly distributed load, and the deflection function of the deformed microelement, including: The relationship between the moment and the deflection function of the deformed microelement is calculated based on the simultaneous equilibrium equations of the strain variables of the deformed microelement, which is expressed as: The displacement field function of the deformed micro-element is obtained by performing calculation based on the relationship between the moment and the deflection function of the deformed micro-element in combination with the relationship between the uniformly distributed load and the deflection function of the deformed micro-element.

7. The method according to claim 6, characterized in that The displacement field function of the deformed micro-element is obtained by performing calculation based on the relationship between the moment and the deflection function of the deformed micro-element in combination with the relationship between the uniformly distributed load and the deflection function of the deformed micro-element, including: According to the relationship between the moment and the deflection function of the deformed microelement, combined with the relationship between the uniformly distributed load and the deflection function of the deformed microelement, the displacement field function to be solved is obtained, which is expressed as Among them, c0, c1, c1, c3 represent the coefficients to be determined, p0 represents the load, and x represents the abscissa of the deformed microelement; The undetermined coefficients are determined according to the boundary conditions of the simply supported beam system, and the displacement field function of the deformed microelement is obtained, which is expressed as: Where l is the length of the simply supported beam system.

8. The method according to claim 7, characterized in that The boundary conditions of the simply supported beam system are expressed as v| x＝0 ＝0 v| x＝l ＝0 M| x＝0 ＝0 M| x＝l ＝0 Among them, v| x＝0 = 0 represents the deflection function of the simply supported beam system at x = 0, v| x＝l = 0 represents the deflection function of the simply supported beam system at x = l, M| x＝0 = 0 represents the moment at x = 0 of the simply supported beam system, M| x＝l =0 represents the moment at x=l of the simply supported beam system.

9. An aerodynamic configuration design optimization device based on the mechanical deformation of geometric materials, characterized in that: The device comprises: A simply supported beam system construction module is used to construct a simply supported beam system based on the busbar of the original aerodynamic configuration; wherein one end face of the simply supported beam system is fixedly constrained, and the other end of the simply supported beam system is deformed by an external force; a force analysis module, configured to perform force analysis on any deformed microelement in the simply supported beam system after deformation, obtain the moment, shear force, normal stress exerted on the deformed microelement, and the uniformly distributed load applied to the deformed microelement, and describe the relationship between the moment, shear force, normal stress, and uniformly distributed load according to an equilibrium equation; a displacement field function calculation module, configured to calculate, based on a geometric equation and the deformation geometric relationship and curvature of the deformed microelement, a strain of the deformed microelement; calculate, based on the strain and physical equation, a relationship between the uniformly distributed load and the deflection function of the deformed microelement; and calculate, based on the strain and the relationship between the uniformly distributed load and the deflection function of the deformed microelement, a displacement field function of the deformed microelement; wherein the displacement field function refers to the displacement of the deformed microelement in the vertical direction when the deformed microelement is affected by an external force; The aerodynamic configuration generation module is used to generate continuous geometric changes by adjusting at least one variable in the displacement field function to obtain a new simply supported beam system, and use the new simply supported beam system as a new busbar to obtain a new aerodynamic configuration.

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