Methods, devices, equipment, and media for optimizing aircraft geometry under the influence of aerodynamics and aerothermal coupling.

Abstract

This application discloses a method, apparatus, equipment, and medium for optimizing the geometric layout of an aircraft under the influence of aerodynamics and aero-thermal coupling, relating to the field of aircraft layout design technology. The method involves determining the geometric shape and parameters corresponding to the geometric configuration, calculating the geometric deformation of the configuration under steady-state conditions, determining the deformation location and deformation value of the aircraft under the influence of aerodynamics and aero-thermal coupling, characterizing the deformation value to obtain a geometric representation, sampling the geometric parameters and deformation values ​​to obtain geometric configurations under different combinations of geometric parameters and deformation, constructing an aerodynamic performance prediction model, inputting the current geometric parameters and current geometric representation into the aerodynamic performance prediction model, outputting predicted aerodynamic performance indicators, selecting the optimal predicted aerodynamic performance indicators, and using the corresponding optimal geometric parameters to determine the optimized geometric layout shape of the aircraft. This solves the uncertainty optimization problem in aircraft aerodynamic layout design and improves the robustness of aircraft aerodynamic performance.

Description

Technical Field

[0001] This invention relates to the field of aircraft layout design technology, and in particular to a method, apparatus, equipment and medium for optimizing the geometric layout of an aircraft under the influence of aerodynamics and aero-thermal coupling. Background Technology

[0002] Aerodynamic layout is one of the key technologies in aircraft design. For high-speed aircraft subjected to prolonged aerodynamic heating, the aerodynamic shape can change due to long-term aerodynamic / thermal coupling, leading to deviations in aerodynamic performance and affecting aircraft performance. In traditional multidisciplinary coupled aerodynamic and aerothermal design, geometric dimensions (such as the leading edge radius of an airfoil) are mostly used as thermal safety constraints, assuming that the geometric shape does not deform, to complete the thermal safety or thermal redundancy design of the aircraft's aerodynamic layout. In practical engineering applications, the impact of long-endurance aerodynamic and aerothermal coupling effects on aerodynamic layout is directly reflected in changes in geometric shape. This thermal deformation cannot be ignored or simplified in aerodynamic layout design, and this deformation has objective uncertainties and cannot be simply assumed to be a deterministic effect.

[0003] As can be seen from the above, how to comprehensively consider the uncertain impact of aerodynamic / thermal coupling effects on the geometry of aircraft during the aerodynamic layout design stage, solve the problem of uncertainty optimization in aircraft aerodynamic layout design, and improve the robustness of aircraft aerodynamic performance are problems to be solved in this field. Summary of the Invention

[0004] In view of this, the purpose of this invention is to provide a method, apparatus, device, and medium for optimizing the geometric layout of an aircraft under the influence of aerodynamics and aero-thermal coupling. This method can comprehensively consider the uncertainties of aerodynamic / thermal coupling effects on the aircraft's geometric shape during the aerodynamic layout design stage, solve the problem of uncertainty optimization in aircraft aerodynamic layout design, and improve the robustness of the aircraft's aerodynamic performance. The specific solution is as follows:

[0005] In a first aspect, this application discloses a method for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling, including:

[0006] Based on the design requirements of the aircraft, the preset initial geometric configuration is parametrically modeled to obtain the geometric configuration;

[0007] Determine the geometric shape and geometric parameters corresponding to the geometric configuration, and calculate the geometric deformation of the geometric configuration in a stable state;

[0008] The deformation position and deformation value of the aircraft under the influence of aerodynamic force and aero-thermal coupling are determined by using the geometric deformation and geometric shape. The deformation value is characterized in a probability distribution manner to obtain the geometric characterization.

[0009] Based on the geometric representation and the deformation position, the geometric parameters and the deformation values ​​are sampled to obtain the geometric configuration under different combinations of geometric parameters and deformation, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation are calculated.

[0010] The geometric parameters and deformation values ​​are used as inputs, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​are used as outputs to construct an aerodynamic performance prediction model.

[0011] The current geometric parameters and current geometric representation of the aircraft are input into the aerodynamic performance prediction model to output predicted values ​​of aerodynamic performance indicators;

[0012] The optimal aerodynamic performance index prediction value is selected from the predicted aerodynamic performance index values, and the optimal geometric parameters corresponding to the optimal aerodynamic performance index prediction value are determined.

[0013] The optimized aircraft geometry under the influence of aerodynamic forces and aero-thermal coupling is determined using the optimal geometric parameters.

[0014] Optionally, the parametric modeling of the preset initial geometric configuration based on the aircraft's design requirements includes:

[0015] Obtain the preset initial geometry;

[0016] Based on the design requirements of the aircraft, the initial geometric configuration is parametrically modeled using a preset parametric modeling method; the preset parametric modeling method includes a geometric free deformation method and a shape category function transformation method.

[0017] Optionally, the calculation of the geometric deformation of the geometric configuration in a steady state includes:

[0018] After the aircraft with the geometric configuration has completed a flight that meets the preset flight duration and speed conditions, the geometric deformation of the geometric configuration in a stable state is calculated using preset aerodynamic and aerothermal coupling calculation tools.

[0019] Optionally, determining the deformation location and deformation value of the aircraft under the influence of aerodynamic forces and aerothermal coupling using the geometric deformation and geometric shape includes:

[0020] The geometric deformation and geometric shape are compared to obtain the comparison results;

[0021] The comparison results are extracted based on the change in the geometric position of a single grid point to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aero-thermal coupling.

[0022] Alternatively, the comparison results can be extracted based on the deformation of macroscopic geometric quantities to obtain the deformation location and deformation value of the aircraft under the influence of aerodynamic forces and aero-thermal coupling.

[0023] Optionally, the step of sampling the geometric parameters and deformation values ​​based on the geometric representation and the deformation position to obtain the geometric configuration under different combinations of geometric parameters and deformation, and calculating the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation, includes:

[0024] Based on the parametric modeling method, the geometric representation, and the deformation position, and by using a preset sampling method to sample the geometric parameters and deformation values, the geometric configuration under different combinations of geometric parameters and deformation values ​​is obtained; the preset sampling method includes the Latin hypercube sampling method.

[0025] Calculate the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformations; the aerodynamic performance index values ​​include lift coefficient, drag coefficient, lift-to-drag ratio, and peak heat flux.

[0026] Optionally, the step of using the geometric parameters and deformation values ​​as inputs, and using the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​as outputs, to construct an aerodynamic performance prediction model, includes:

[0027] Using the geometric parameters and deformation values ​​as inputs, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​as outputs, an aerodynamic performance prediction model is constructed based on chaotic polynomials and machine learning methods.

[0028] Optionally, the step of inputting the current geometric parameters and current geometric representation of the aircraft into the aerodynamic performance prediction model to output predicted aerodynamic performance indicators; selecting the optimal predicted aerodynamic performance indicator from the predicted aerodynamic performance indicator values, and determining the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance indicator value, includes:

[0029] Using the current geometric parameters of the aircraft as design variables and the current geometric characterization as uncertainty variables, the predicted values ​​of aerodynamic performance indicators are output.

[0030] The optimal aerodynamic performance index prediction value is selected from the predicted aerodynamic performance index values ​​using an intelligent optimization method, and the optimal geometric parameters corresponding to the optimal aerodynamic performance index prediction value are determined.

[0031] Secondly, this application discloses a device for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling, comprising:

[0032] The parametric modeling module is used to parametrically model the preset initial geometric configuration based on the design requirements of the aircraft, and obtain the geometric configuration.

[0033] The geometric deformation calculation module is used to determine the geometric shape and geometric parameters corresponding to the geometric configuration, and to calculate the geometric deformation of the geometric configuration in a stable state.

[0034] The characterization module is used to determine the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aero-thermal coupling using the geometric deformation and geometric shape, and to characterize the deformation value in a probability distribution manner to obtain the geometric characterization;

[0035] The aerodynamic performance index calculation module is used to sample the geometric parameters and deformation values ​​based on the geometric representation and the deformation position to obtain the geometric configuration under different combinations of geometric parameters and deformation, and to calculate the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation.

[0036] The model building module is used to take the geometric parameters and deformation values ​​as inputs and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformations as outputs, so as to build an aerodynamic performance prediction model.

[0037] The prediction module is used to input the current geometric parameters and current geometric representation of the aircraft into the aerodynamic performance prediction model to output predicted values ​​of aerodynamic performance indicators;

[0038] The filtering module is used to filter out the optimal aerodynamic performance index prediction value from the predicted aerodynamic performance index values ​​and determine the optimal geometric parameters corresponding to the optimal aerodynamic performance index prediction value.

[0039] The geometric layout shape determination module is used to determine the optimized aircraft geometric layout shape under the influence of aerodynamics and aero-thermal coupling using the optimal geometric parameters.

[0040] Thirdly, this application discloses an electronic device, including:

[0041] Memory, used to store computer programs;

[0042] A processor is used to execute the computer program to implement the aforementioned method for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling.

[0043] Fourthly, this application discloses a computer storage medium for storing a computer program; wherein, when the computer program is executed by a processor, it implements the steps of the aforementioned disclosed method for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling.

[0044] As can be seen, this application provides a method for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling. The method includes: parametrically modeling a preset initial geometric configuration based on the aircraft's design requirements to obtain a geometric configuration; determining the geometric shape and geometric parameters corresponding to the geometric configuration, and calculating the geometric deformation of the geometric configuration in a stable state; using the geometric deformation and geometric shape to determine the deformation position and deformation value of the aircraft under the influence of aerodynamic forces and aero-thermal coupling, and characterizing the deformation value in a probability distribution manner to obtain a geometric representation; and sampling the geometric parameters and deformation values ​​based on the geometric representation and the deformation position to obtain the geometric layout optimization method under different combinations of geometric parameters and deformation values. The aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation variables are calculated. The geometric parameters and deformation variable values ​​are used as inputs, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation variables are used as outputs to construct an aerodynamic performance prediction model. The current geometric parameters and current geometric representation of the aircraft are input into the aerodynamic performance prediction model to output predicted aerodynamic performance index values. The optimal predicted aerodynamic performance index value is selected from the predicted aerodynamic performance index values, and the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance index value are determined. The optimized geometric layout shape of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling is determined using the optimal geometric parameters. This application parametrically models a preset initial geometric configuration based on the design requirements of the aircraft, obtaining the geometric configuration. It calculates the geometric deformation of the configuration in a stable state to determine the deformation location and value of the aircraft under the influence of aerodynamic and aerothermal coupling. Considering the impact of multidisciplinary aerodynamic and aerothermal coupling effects on the aircraft's shape during long-endurance flight, it integrates complex multidisciplinary coupling effects with geometric layout optimization. The deformation value is characterized using a probability distribution, treating the influence as the uncertainty of aerodynamic shape deformation. Based on the geometric representation and deformation location, geometric parameters and deformation values ​​are sampled to obtain geometric configurations under different combinations of geometric parameters and deformation values. The aerodynamic performance of the geometric configurations under different combinations of geometric parameters and deformation values ​​is then calculated. The aerodynamic performance index values ​​are constructed by taking geometric parameters and deformation values ​​as inputs and outputting aerodynamic performance index values ​​of geometric configurations under different combinations of geometric parameters and deformation values. This constructs an aerodynamic performance prediction model, which improves the efficiency and accuracy of aircraft aerodynamic performance prediction. The current geometric parameters and current geometric characteristics of the aircraft are input into the aerodynamic performance prediction model to output predicted aerodynamic performance index values. The optimal predicted aerodynamic performance index value is selected, and the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance index value are determined. The optimal geometric parameters are then used to determine the optimized geometric layout shape of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling, solving the uncertainty optimization problem of aircraft aerodynamic layout design and improving the robustness of aircraft aerodynamic performance. Attached Figure Description

[0045] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0046] Figure 1 This is a flowchart of a method for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling, as disclosed in this application.

[0047] Figure 2 This is an initial geometric configuration diagram of an aircraft disclosed in this application;

[0048] Figure 3 This is a schematic diagram of a parametric wing disclosed in this application;

[0049] Figure 4 This is a comparison image of a wing before and after optimization as disclosed in this application;

[0050] Figure 5 This application discloses a specific flowchart for optimizing the geometric layout of an aircraft under the influence of aerodynamics and aerothermal coupling.

[0051] Figure 6 This is a schematic diagram of a device for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling, as disclosed in this application.

[0052] Figure 7 This application provides a structural diagram of an electronic device. Detailed Implementation

[0053] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0054] Aerodynamic layout is a key technology in aircraft design. For high-speed aircraft subjected to prolonged aerodynamic heating, the aerodynamic shape can change due to long-term aerodynamic / thermal coupling, leading to deviations in aerodynamic performance and affecting aircraft performance. Traditional aerodynamic and aerothermal multidisciplinary coupled design often uses geometric dimensions (such as the wing leading edge radius) as thermal safety constraints, assuming no geometric deformation, to achieve thermal safety or thermal redundancy design of the aircraft's aerodynamic layout. In practical engineering applications, the impact of long-endurance aerodynamic and aerothermal coupling effects on the aerodynamic layout is directly reflected in changes in geometric shape. This thermal deformation cannot be ignored or simplified in aerodynamic layout design, and this deformation has objective uncertainties and cannot be simply assumed to be a deterministic effect. Therefore, how to comprehensively consider the uncertain impact of aerodynamic / thermal coupling effects on the aircraft's geometric shape during the aerodynamic layout design stage, solve the uncertainty optimization problem of aircraft aerodynamic layout design, and improve the robustness of aircraft aerodynamic performance is a problem that needs to be solved in this field.

[0055] See Figure 1 As shown in the figure, this invention discloses a method for optimizing the geometric layout of an aircraft under the influence of aerodynamics and aerothermal coupling, which may specifically include:

[0056] Step S11: Based on the design requirements of the aircraft, perform parametric modeling of the preset initial geometric configuration to obtain the geometric configuration.

[0057] In this embodiment, a preset initial geometric configuration is obtained; based on the design requirements of the aircraft, the initial geometric configuration is parametrically modeled using a preset parametric modeling method to obtain the geometric configuration; the preset parametric modeling method includes a geometric free deformation method and a shape category function transformation method.

[0058] Specifically, given a preliminary geometric configuration, and based on the aircraft's design requirements, parametric modeling is performed on this preliminary geometric configuration. This involves using mathematical parameters to characterize the entire geometric configuration, which can be adjusted to change the overall configuration. This step can be achieved using traditional methods such as Freeform Factorization (FFD) and Shape Class Function Transformation (CST).

[0059] The initial geometry of the aircraft is as follows Figure 2 As shown, the wing is the core aerodynamic component, and aerodynamic layout optimization mainly focuses on wing deployment; therefore, parametric modeling primarily targets the wing. A schematic diagram of the wing's parametric design is shown below. Figure 3 As shown, the half-span of the leading edge spar is... Wing half span First leading edge sweep angle Second leading edge sweep angle trailing edge sweep angle wing root chord length .

[0060] Step S12: Determine the geometric shape and geometric parameters corresponding to the geometric configuration, and calculate the geometric deformation of the geometric configuration in a stable state.

[0061] In this embodiment, the geometric shape and geometric parameters corresponding to the geometric configuration are determined. After the aircraft of the geometric configuration has flown for a period of time and speed that meet the preset flight conditions, the geometric deformation of the geometric configuration in a stable state is calculated using preset aerodynamic and aerothermal coupling calculation tools.

[0062] This application focuses on geometric configurations and uses aerodynamic and aerothermal coupling calculation tools to calculate the geometric deformation of the geometric configuration in a stable state after long-duration high-speed flight.

[0063] Step S13: Determine the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aero-thermal coupling using the geometric deformation and geometric shape, and characterize the deformation value in a probability distribution manner to obtain the geometric characterization.

[0064] In this embodiment, the geometric deformation and geometric shape are compared to obtain a comparison result; the comparison result is extracted based on the change in the geometric position of a single grid point to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic forces and aero-thermal coupling; or, the comparison result is extracted based on the deformation of macroscopic geometric quantities to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic forces and aero-thermal coupling, and the deformation value is characterized in a probability distribution manner to obtain a geometric representation.

[0065] Calculations show that after prolonged high-speed flight, under the combined effects of aerodynamic forces and aerothermal coupling, the leading edge of the aircraft fuselage deforms, causing an equivalent angle of attack deviation, and the wing deforms, leading to an increase in the bending angle. Therefore, this application proposes to compare the geometric deformation and geometric shape under the influence of aerodynamic forces and aerothermal coupling, quantify the macroscopic geometric shape deformation, and extract key deformation locations and values. This deformation location extraction step can be based on the geometric position change of a single grid point or on the deformation of macroscopic geometric quantities. Then, these deformation variables are treated as an uncertainty quantity, and the uncertainty of the deformation value is characterized using a user-specified probability distribution to obtain a geometric representation.

[0066] Table 1 shows a comparison of deformation characteristics at different angles of attack in the quantitative macroscopic geometric shape variables:

[0067] Table 1 Comparison of deformation characteristics at different angles of attack

[0068]

[0069] It is known that the coupling effect of aerodynamics and aerothermal energy primarily affects the deformation angle of the fuselage leading edge and the wing bending angle of the aircraft. These two geometric parameters are set as random variables, assumed to be independent and following a normal distribution. With a design angle of attack of 4 degrees, the two random variables satisfy the following:

[0070] ;

[0071] ;

[0072] and These represent the standard deviations of the random variables, provided by the user.

[0073] Step S14: Based on the geometric representation and the deformation position, sample the geometric parameters and the deformation values ​​to obtain the geometric configuration under different combinations of geometric parameters and deformation, and calculate the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation.

[0074] In this embodiment, based on the parametric modeling method, the geometric representation, and the deformation position, and using a preset sampling method to sample the geometric parameters and deformation values, the geometric configuration under different combinations of geometric parameters and deformation values ​​is obtained; the preset sampling method includes the Latin hypercube sampling method; the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​are calculated; the aerodynamic performance index values ​​include lift coefficient, drag coefficient, lift-to-drag ratio, and peak heat flux.

[0075] This application is based on parametric modeling methods and geometric characterization under the influence of aerodynamic forces and aero-thermal coupling. It samples the values ​​of geometric parameters and deformations using methods such as Latin hypercube to obtain geometric configurations under different combinations of geometric parameters and deformations. For the sampled shape, it calculates the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformations, such as lift coefficient, drag coefficient, lift-to-drag ratio, and peak heat flux.

[0076] In this embodiment, by sampling design variables and random variables, 2000 sets of sample data of geometric configurations under different combinations of geometric parameters and deformation variables are obtained.

[0077] Step S15: Take the geometric parameters and deformation values ​​as inputs, and take the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformations as outputs, so as to construct an aerodynamic performance prediction model.

[0078] In this embodiment, the geometric parameters and deformation values ​​are used as inputs, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​are used as outputs. An aerodynamic performance prediction model is constructed based on chaotic polynomials and machine learning methods.

[0079] This application employs machine learning and chaotic polynomial techniques to fit and model sample data of 2000 sets of geometric configurations under different combinations of geometric parameters and deformation variables, and constructs an aerodynamic performance prediction model. The aerodynamic performance prediction model can predict the mean and variance of the aerodynamic lift-to-drag ratio of the aircraft under steady-state conditions under the action of aerodynamic forces and aerodynamic-thermal coupling effects based on the input of design variables.

[0080] Step S16: Input the current geometric parameters and current geometric representation of the aircraft into the aerodynamic performance prediction model to output the predicted values ​​of aerodynamic performance indicators.

[0081] Step S17: Select the optimal aerodynamic performance index prediction value from the predicted aerodynamic performance index values, and determine the optimal geometric parameters corresponding to the optimal aerodynamic performance index prediction value.

[0082] In this embodiment, the current geometric parameters of the aircraft are used as design variables, and the current geometric representation is used as an uncertainty variable to output predicted values ​​of aerodynamic performance indicators. The optimal predicted value of aerodynamic performance indicators is selected from the predicted values ​​of aerodynamic performance indicators using an intelligent optimization method, and the optimal geometric parameters corresponding to the optimal predicted value of aerodynamic performance indicators are determined.

[0083] Step S18: Determine the optimized aircraft geometric layout shape under the influence of aerodynamic force and aero-thermal coupling using the optimal geometric parameters.

[0084] This application uses the mean and standard deviation of the aerodynamic lift-to-drag ratio under steady-state conditions of the aircraft's aerodynamic forces and aerodynamic-thermal coupling effects as optimization objectives, and the wing area of ​​the aircraft as a constraint (to meet structural design requirements). It employs intelligent optimization algorithms and aerodynamic performance prediction models to optimize the aircraft's design variables and determine the optimal geometric parameters.

[0085] In this embodiment, a comparison is made before and after wing optimization. Figure 4 As shown in Table 2, the optimized geometric configuration and the comparison of the geometric parameter values ​​of the geometric configuration are presented:

[0086] Table 2 Comparison of optimized geometric configuration and design variable values ​​for geometric configuration

[0087]

[0088] Under steady-state conditions of aerodynamic and aero-thermal coupling effects, the mean and standard deviation of the aerodynamic lift-to-drag ratio for the original geometric configuration are 4.98 and 0.03, respectively. Under the same steady-state conditions, the optimized geometric configuration has a mean and standard deviation of 5.17 and 0.027 for the aerodynamic lift-to-drag ratio, respectively. This means that the optimization improved the statistical mean of the aerodynamic lift-to-drag ratio by 3.82% while maintaining a 10% reduction in the statistical standard deviation. In other words, it not only improved the aerodynamic lift-to-drag ratio of the geometric configuration but also further enhanced its aerodynamic robustness.

[0089] The specific process for optimizing the aircraft geometry under the influence of aerodynamics and aerothermal coupling in this application is as follows: Figure 5 As shown, this invention considers the impact of multidisciplinary aerodynamic and aerothermal coupling effects on the aircraft's shape during long-endurance flight. This impact is treated as an uncertainty in aerodynamic shape deformation. Based on the characterization steps of treating this as an aerodynamic shape coupling effect, the geometric shape coupling effect is represented in aerodynamic layout design. A cross-configuration aerodynamic performance prediction model is constructed to improve the rapid prediction of the aircraft's aerodynamic statistical characteristics. The design of the entire optimization framework incorporates multidisciplinary coupling effects into the aerodynamic layout optimization model, ensuring that the uncertainty of this coupling effect is considered from the outset of aerodynamic layout design. This method solves the problem of rapid optimization of aerodynamic layout design for high-speed aircraft considering step-coupled uncertainty effects, and can provide technical support for the aerodynamic layout design of such aircraft. The core of this invention is the design of the entire optimization framework and the design of the multidisciplinary coupling effect characterization strategy. It achieves the integration of complex multidisciplinary coupling effects with geometric layout optimization, completes the aerodynamic layout design optimization modeling and solution, and improves the design capability of long-endurance high-speed aircraft.

[0090] In this embodiment, a parametric model of a preset initial geometric configuration is performed based on the design requirements of the aircraft to obtain the geometric configuration; the geometric shape and geometric parameters corresponding to the geometric configuration are determined, and the geometric deformation of the geometric configuration in a stable state is calculated; the deformation position and deformation value of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling are determined using the geometric deformation and geometric shape, and the deformation value is characterized in a probability distribution manner to obtain the geometric representation; based on the geometric representation and the deformation position, the geometric parameters and deformation values ​​are sampled to obtain the geometric configuration under different combinations of geometric parameters and deformation values, and the geometric parameters and deformation values ​​are calculated for different combinations. The aerodynamic performance index values ​​of the geometric configuration under the combination are obtained; the geometric parameters and deformation values ​​are used as inputs, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​are used as outputs to construct an aerodynamic performance prediction model; the current geometric parameters and current geometric representation of the aircraft are input into the aerodynamic performance prediction model to output predicted aerodynamic performance index values; the optimal predicted aerodynamic performance index value is selected from the predicted aerodynamic performance index values, and the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance index value are determined; the optimized geometric layout shape of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling is determined using the optimal geometric parameters. This application parametrically models a preset initial geometric configuration based on the design requirements of the aircraft, obtaining the geometric configuration. It calculates the geometric deformation of the configuration in a stable state to determine the deformation location and value of the aircraft under the influence of aerodynamic and aerothermal coupling. Considering the impact of multidisciplinary aerodynamic and aerothermal coupling effects on the aircraft's shape during long-endurance flight, it integrates complex multidisciplinary coupling effects with geometric layout optimization. The deformation value is characterized using a probability distribution, treating the influence as the uncertainty of aerodynamic shape deformation. Based on the geometric representation and deformation location, geometric parameters and deformation values ​​are sampled to obtain geometric configurations under different combinations of geometric parameters and deformation values. The aerodynamic performance of the geometric configurations under different combinations of geometric parameters and deformation values ​​is then calculated. The aerodynamic performance index values ​​are constructed by taking geometric parameters and deformation values ​​as inputs and outputting aerodynamic performance index values ​​of geometric configurations under different combinations of geometric parameters and deformation values. This constructs an aerodynamic performance prediction model, which improves the efficiency and accuracy of aircraft aerodynamic performance prediction. The current geometric parameters and current geometric characteristics of the aircraft are input into the aerodynamic performance prediction model to output predicted aerodynamic performance index values. The optimal predicted aerodynamic performance index value is selected, and the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance index value are determined. The optimal geometric parameters are then used to determine the optimized geometric layout shape of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling, solving the uncertainty optimization problem of aircraft aerodynamic layout design and improving the robustness of aircraft aerodynamic performance.

[0091] See Figure 6As shown in the figure, this invention discloses a device for optimizing the geometric layout of an aircraft under the influence of aerodynamics and aero-thermal coupling, which may specifically include:

[0092] Parametric modeling module 11 is used to parametrically model the preset initial geometric configuration based on the design requirements of the aircraft to obtain the geometric configuration;

[0093] The geometric deformation calculation module 12 is used to determine the geometric shape and geometric parameters corresponding to the geometric configuration, and to calculate the geometric deformation of the geometric configuration in a stable state.

[0094] Characterization module 13 is used to determine the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aerodynamic-thermal coupling using the geometric deformation and geometric shape, and to characterize the deformation value in a probability distribution manner to obtain geometric characterization;

[0095] The aerodynamic performance index calculation module 14 is used to sample the geometric parameters and deformation values ​​based on the geometric representation and the deformation position to obtain the geometric configuration under different combinations of geometric parameters and deformation, and to calculate the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation.

[0096] The model building module 15 is used to take the geometric parameters and the deformation values ​​as inputs, and take the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformations as outputs, so as to build an aerodynamic performance prediction model.

[0097] Prediction module 16 is used to input the current geometric parameters and current geometric representation of the aircraft into the aerodynamic performance prediction model to output predicted values ​​of aerodynamic performance indicators;

[0098] The filtering module 17 is used to filter out the optimal aerodynamic performance index prediction value from the predicted aerodynamic performance index values ​​and determine the optimal geometric parameters corresponding to the optimal aerodynamic performance index prediction value.

[0099] The geometric layout shape determination module 18 is used to determine the optimized aircraft geometric layout shape under the influence of aerodynamics and aero-thermal coupling using the optimal geometric parameters.

[0100] In this embodiment, a parametric model of a preset initial geometric configuration is performed based on the design requirements of the aircraft to obtain the geometric configuration; the geometric shape and geometric parameters corresponding to the geometric configuration are determined, and the geometric deformation of the geometric configuration in a stable state is calculated; the deformation position and deformation value of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling are determined using the geometric deformation and geometric shape, and the deformation value is characterized in a probability distribution manner to obtain the geometric representation; based on the geometric representation and the deformation position, the geometric parameters and deformation values ​​are sampled to obtain the geometric configuration under different combinations of geometric parameters and deformation values, and the geometric parameters and deformation values ​​are calculated for different combinations. The aerodynamic performance index values ​​of the geometric configuration under the combination are obtained; the geometric parameters and deformation values ​​are used as inputs, and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​are used as outputs to construct an aerodynamic performance prediction model; the current geometric parameters and current geometric representation of the aircraft are input into the aerodynamic performance prediction model to output predicted aerodynamic performance index values; the optimal predicted aerodynamic performance index value is selected from the predicted aerodynamic performance index values, and the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance index value are determined; the optimized geometric layout shape of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling is determined using the optimal geometric parameters. This application parametrically models a preset initial geometric configuration based on the design requirements of the aircraft, obtaining the geometric configuration. It calculates the geometric deformation of the configuration in a stable state to determine the deformation location and value of the aircraft under the influence of aerodynamic and aerothermal coupling. Considering the impact of multidisciplinary aerodynamic and aerothermal coupling effects on the aircraft's shape during long-endurance flight, it integrates complex multidisciplinary coupling effects with geometric layout optimization. The deformation value is characterized using a probability distribution, treating the influence as the uncertainty of aerodynamic shape deformation. Based on the geometric representation and deformation location, geometric parameters and deformation values ​​are sampled to obtain geometric configurations under different combinations of geometric parameters and deformation values. The aerodynamic performance of the geometric configurations under different combinations of geometric parameters and deformation values ​​is then calculated. The aerodynamic performance index values ​​are constructed by taking geometric parameters and deformation values ​​as inputs and outputting aerodynamic performance index values ​​of geometric configurations under different combinations of geometric parameters and deformation values. This constructs an aerodynamic performance prediction model, which improves the efficiency and accuracy of aircraft aerodynamic performance prediction. The current geometric parameters and current geometric characteristics of the aircraft are input into the aerodynamic performance prediction model to output predicted aerodynamic performance index values. The optimal predicted aerodynamic performance index value is selected, and the optimal geometric parameters corresponding to the optimal predicted aerodynamic performance index value are determined. The optimal geometric parameters are then used to determine the optimized geometric layout shape of the aircraft under the influence of aerodynamic forces and aerodynamic-thermal coupling, solving the uncertainty optimization problem of aircraft aerodynamic layout design and improving the robustness of aircraft aerodynamic performance.

[0101] In some specific embodiments, the parametric modeling module 11 may specifically include:

[0102] The initial geometry acquisition module is used to acquire the preset initial geometry.

[0103] The initial geometric configuration parametric modeling module is used to perform parametric modeling of the initial geometric configuration based on the design requirements of the aircraft and using preset parametric modeling methods; the preset parametric modeling methods include geometric free deformation methods and shape category function transformation methods.

[0104] In some specific embodiments, the geometric deformation calculation module 12 may specifically include:

[0105] The geometric deformation calculation module for the geometric configuration is used to calculate the geometric deformation of the geometric configuration in a stable state after the aircraft has flown for a period of time and speed that meet the preset flight conditions. This is done using preset aerodynamic and aerothermal coupling calculation tools.

[0106] In some specific embodiments, the characterization module 13 may specifically include:

[0107] The comparison module is used to compare the geometric deformation and the geometric shape to obtain the comparison result;

[0108] The first extraction module is used to extract the comparison results based on the change in the geometric position of a single grid point, so as to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aero-thermal coupling.

[0109] The second extraction module is used to extract the comparison results based on the deformation of macroscopic geometric quantities, so as to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aero-thermal coupling.

[0110] In some specific embodiments, the aerodynamic performance index calculation module 14 may specifically include:

[0111] The sampling module is used to sample the geometric parameters and deformation values ​​based on the parametric modeling method, the geometric representation, and the deformation position, and using a preset sampling method to obtain the geometric configuration under different combinations of geometric parameters and deformations; the preset sampling method includes the Latin hypercube sampling method.

[0112] The aerodynamic performance index calculation module for the geometric configuration is used to calculate the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformations; the aerodynamic performance index values ​​include lift coefficient, drag coefficient, lift-to-drag ratio, and peak heat flux.

[0113] In some specific embodiments, the model building module 15 may specifically include:

[0114] An aerodynamic performance prediction model construction module is used to construct an aerodynamic performance prediction model based on chaotic polynomials and machine learning methods, taking the geometric parameters and deformation values ​​as inputs and the aerodynamic performance index values ​​of the geometric configuration under different combinations of geometric parameters and deformation values ​​as outputs.

[0115] In some specific embodiments, the prediction module 16 may specifically include:

[0116] The aerodynamic performance index prediction module is used to output predicted aerodynamic performance index values, taking the current geometric parameters of the aircraft as design variables and the current geometric characteristics as uncertainty variables.

[0117] In some specific embodiments, the filtering module 17 may specifically include:

[0118] The optimal aerodynamic performance index prediction value screening module is used to select the optimal aerodynamic performance index prediction value from the predicted aerodynamic performance index values ​​using an intelligent optimization method, and determine the optimal geometric parameters corresponding to the optimal aerodynamic performance index prediction value.

[0119] Figure 7 This is a schematic diagram of an electronic device provided in an embodiment of this application. The electronic device 20 specifically includes: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 stores a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the aerodynamic and aerothermal coupling-based aircraft geometry optimization method disclosed in any of the foregoing embodiments.

[0120] In this embodiment, the power supply 23 is used to provide operating voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and external devices, and the communication protocol it follows can be any communication protocol applicable to the technical solution of this application, and is not specifically limited here; the input / output interface 25 is used to acquire external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs, and is not specifically limited here.

[0121] In addition, the memory 22, as a carrier for resource storage, can be a read-only memory, random access memory, disk or optical disk, etc. The resources stored on it include operating system 221, computer program 222 and data 223, etc., and the storage method can be temporary storage or permanent storage.

[0122] The operating system 221 manages and controls the various hardware devices on the electronic device 20 and the computer program 222 to enable the processor 21 to perform calculations and processing on the data 223 in the memory 22. It can be Windows, Unix, Linux, etc. The computer program 222, in addition to including a computer program capable of performing the aerodynamic and aerothermal coupling-based aircraft geometry optimization method disclosed in any of the foregoing embodiments, may further include computer programs capable of performing other specific tasks. The data 223 may include data received by the aerodynamic and aerothermal coupling-based aircraft geometry optimization device from external devices, as well as data collected by its own input / output interface 25.

[0123] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly by hardware, a software module executed by a processor, or a combination of both. The software module can be located in random access memory (RAM), main memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art.

[0124] Furthermore, this application also discloses a computer-readable storage medium storing a computer program. When the computer program is loaded and executed by a processor, it implements the steps of the aircraft geometry optimization method under the influence of aerodynamic forces and aero-thermal coupling disclosed in any of the foregoing embodiments.

[0125] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0126] The foregoing has provided a detailed description of the method, apparatus, device, and storage medium for optimizing the geometric layout of an aircraft under the influence of aerodynamic forces and aero-thermal coupling. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A method for optimization of an aircraft geometry layout under the influence of aerodynamic forces and aerodynamic heating, characterized in that, The method comprises the following steps: Parameterize modeling of a preset initial geometric configuration based on design requirements of an aircraft to obtain a geometric configuration; Determine a geometric shape and a geometric parameter corresponding to the geometric configuration, and calculate geometric deformation of the geometric configuration in a stable state; Determine deformation position and deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling by using the geometric deformation and the geometric shape, and represent the deformation value in a probability distribution manner to obtain geometric representation; Sample the geometric parameter and the deformation value based on the geometric representation and the deformation position to obtain the geometric configuration under different combinations of the geometric parameter and the deformation value, and calculate aerodynamic performance index values of the geometric configuration under different combinations of the geometric parameter and the deformation value; Take the geometric parameter and the deformation value as input, and take the aerodynamic performance index values of the geometric configuration under different combinations of the geometric parameter and the deformation value as output to construct an aerodynamic performance prediction model; Input current geometric parameter and current geometric representation of the aircraft into the aerodynamic performance prediction model to output an aerodynamic performance index prediction value; Select an optimal aerodynamic performance index prediction value from the aerodynamic performance index prediction value, and determine an optimal geometric parameter corresponding to the optimal aerodynamic performance index prediction value; Determine an optimized aircraft geometric layout shape under the influence of aerodynamic force and aerodynamic heat coupling by using the optimal geometric parameter. The determination of the deformation position and the deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling by using the geometric deformation and the geometric shape comprises: comparing the geometric deformation and the geometric shape to obtain a comparison result; extracting the comparison result according to the change of the geometric position of a single grid point to obtain the deformation position and the deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling; or extracting the comparison result according to the deformation value of a macroscopic geometric quantity to obtain the deformation position and the deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling.

2. The aircraft geometry layout optimization method under aerodynamic force and aero- thermal coupled effects according to claim 1, characterized in that, The parameterization modeling of the preset initial geometric configuration based on the design requirements of the aircraft comprises: Obtain a preset initial geometric configuration; Parameterize model the initial geometric configuration based on the design requirements of the aircraft by using a preset parameterization modeling method; the preset parameterization modeling method comprises a geometric free deformation method and a shape category function transformation method.

3. The aircraft geometry layout optimization method under aerodynamic force and aero- thermal coupled effects according to claim 1, characterized in that, The calculation of the geometric deformation of the geometric configuration in a stable state comprises: After the aircraft of the geometric configuration flies for a flight time and at a speed that meet preset conditions, calculate the geometric deformation of the geometric configuration in a stable state by using a preset aerodynamic force and aerodynamic heat coupling calculation tool.

4. The aircraft geometry layout optimization method under aerodynamic force and aero- thermal coupled effects according to claim 1, characterized in that, The sampling of the geometric parameter and the deformation value based on the geometric representation and the deformation position to obtain the geometric configuration under different combinations of the geometric parameter and the deformation value, and the calculation of the aerodynamic performance index values of the geometric configuration under different combinations of the geometric parameter and the deformation value comprise: sample the geometric parameters and the deformation values by using a preset sampling method to obtain the geometric configurations under different combinations of the geometric parameters and the deformation values; the preset sampling method comprises a Latin hypercube sampling method; calculate aerodynamic performance index values of the geometric configurations under different combinations of the geometric parameters and the deformation values; the aerodynamic performance index values comprise lift coefficients, drag coefficients, lift-drag ratios and heat flow peak values.

5. The aircraft geometry layout optimization method under aerodynamic force and aero- thermal coupled effects according to claim 1, characterized in that, the geometric parameters and the deformation values are taken as inputs, and the aerodynamic performance index values of the geometric configurations under different combinations of the geometric parameters and the deformation values are taken as outputs to construct an aerodynamic performance prediction model, comprising: the geometric parameters and the deformation values are taken as inputs, and the aerodynamic performance index values of the geometric configurations under different combinations of the geometric parameters and the deformation values are taken as outputs to construct an aerodynamic performance prediction model, comprising:

6. The method for aircraft geometry layout optimization under aerodynamic force and aero- thermal coupled effects according to any one of claims 1 to 5, characterized in that, the current geometric parameters and the current geometric representation of the aircraft are input into the aerodynamic performance prediction model to output aerodynamic performance index prediction values; the optimal aerodynamic performance index prediction value is selected from the aerodynamic performance index prediction values, and the optimal geometric parameter corresponding to the optimal aerodynamic performance index prediction value is determined, comprising: the current geometric parameters of the aircraft are taken as design variables, and the current geometric representation is taken as an uncertainty variable to output the aerodynamic performance index prediction values; an intelligent optimization method is used to select the optimal aerodynamic performance index prediction value from the aerodynamic performance index prediction values, and the optimal geometric parameter corresponding to the optimal aerodynamic performance index prediction value is determined.

7. An apparatus for optimization of an aircraft geometry layout under the influence of aerodynamic forces and aerodynamic heating, characterized by comprising: a parameterized modeling module configured to perform parameterized modeling on a preset initial geometric configuration based on design requirements of an aircraft to obtain a geometric configuration; a geometric deformation calculation module configured to determine a geometric shape and geometric parameters corresponding to the geometric configuration, and calculate geometric deformation of the geometric configuration in a stable state; a representation module configured to determine deformation positions and deformation values of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling by using the geometric deformation and the geometric shape, represent the deformation values in a probabilistic distribution manner to obtain a geometric representation; an aerodynamic performance index value calculation module configured to sample the geometric parameters and the deformation values based on the geometric representation and the deformation positions to obtain the geometric configurations under different combinations of the geometric parameters and the deformation values, and calculate aerodynamic performance index values of the geometric configurations under different combinations of the geometric parameters and the deformation values; a model construction module configured to take the geometric parameters and the deformation values as inputs, and take the aerodynamic performance index values of the geometric configurations under different combinations of the geometric parameters and the deformation values as outputs to construct an aerodynamic performance prediction model; a prediction module configured to input current geometric parameters and a current geometric representation of an aircraft into the aerodynamic performance prediction model to output aerodynamic performance index prediction values; a screening module configured to select an optimal aerodynamic performance index prediction value from the aerodynamic performance index prediction values, and determine an optimal geometric parameter corresponding to the optimal aerodynamic performance index prediction value. A geometric layout shape determining module is configured to determine an optimized aircraft geometric layout shape under the influence of aerodynamic force and aerodynamic heat coupling. The determining of the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling by using the geometric deformation and geometric shape includes: comparing the geometric deformation and the geometric shape to obtain a comparison result; extracting the comparison result according to the change of the geometric position of a single grid point to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling; or extracting the comparison result according to the deformation value of a macroscopic geometric quantity to obtain the deformation position and deformation value of the aircraft under the influence of aerodynamic force and aerodynamic heat coupling.

8. An electronic device, comprising: The computer program product comprises: a memory configured to store a computer program; a processor configured to execute the computer program to implement the aircraft geometric layout optimization method under the influence of aerodynamic force and aerodynamic heat coupling according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, a memory configured to store a computer program; wherein the computer program is executed by a processor to implement the aircraft geometric layout optimization method under the influence of aerodynamic force and aerodynamic heat coupling according to any one of claims 1 to 6.

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