Spray flow interference control optimization design method and system based on empennage layout

Abstract

The invention provides a jet disturbance control optimization design method and system based on empennage layout, and the method comprises the steps: S1, obtaining aerodynamic parameters of a jet disturbance flow field of an aircraft, and taking the aerodynamic parameters as a sample set; s2, training a pre-constructed agent model by using the sample set to obtain an optimal solution; s3, performing precision verification on the proxy model with the optimal solution, and if a verification result meets a preset requirement, ending training; and if the verification result does not meet the preset requirement, adding data points to the sample set and then repeatedly executing the steps S1-S3 until the verification result meets the preset requirement. According to the rapid optimization design method based on empennage layout passive control, optimization design is carried out on the empennage key size of the aircraft model, so that the aerodynamic interference influence is reduced, and the stability of an interception missile is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerodynamic layout optimization, and in particular to a jet interference control optimization design method and system based on tail wing layout. Background Art

[0002] Jet control technology is an active flow control technology that directly changes the flight trajectory or attitude of an aircraft through the reaction force of the jet. It has the advantages of fast response speed, no restrictions on airspace and speed domains, and high control accuracy. The flight range of future hypersonic aircraft will range from low altitude to high altitude, covering dense atmosphere to thin atmosphere. The aerodynamic force varies greatly under different environments, and numerical calculation and simulation take a long time. The proxy model in the proxy model optimization method is an approximation of the real objective function, which can quickly obtain an approximate optimal solution, and is therefore more suitable for dealing with complex engineering problems. Therefore, it is particularly important to construct a proxy model for the rapid optimization design of the jet interference control layout. Summary of the invention

[0003] The purpose of the present invention is to provide a method and system for optimizing the design of jet interference control based on tail wing layout, aiming to solve the above-mentioned problems in the prior art.

[0004] The embodiment of the present invention provides a jet interference control optimization design method based on tail wing layout, comprising:

[0005] S1: Acquire aerodynamic parameters of the aircraft jet interference flow field, and use the aerodynamic parameters as a sample set;

[0006] S2: using the sample set to train the pre-built proxy model to obtain an optimal solution;

[0007] S3: Verify the accuracy of the proxy model that obtains the optimal solution. If the verification result meets the preset requirements, end the training; if the verification result does not meet the preset requirements, add data points to the sample set and repeat steps S1-S3 until the verification result meets the preset requirements.

[0008] The embodiment of the present invention provides a jet interference control optimization design system based on tail wing layout, comprising:

[0009] A data module, used for obtaining aerodynamic parameters of the aircraft jet interference flow field, and using the aerodynamic parameters as a sample set;

[0010] A training module, used to train a pre-built proxy model using the sample set to obtain an optimal solution;

[0011] The verification module is used to verify the accuracy of the proxy model that obtains the optimal solution. If the verification result meets the preset requirements, the training is terminated; if the verification result does not meet the preset requirements, the data module to the verification module is repeatedly executed after adding data points to the sample set until the verification result meets the preset requirements.

[0012] An embodiment of the present invention also provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the steps of the above-mentioned method for optimizing the design of jet interference control based on tail wing layout are implemented.

[0013] An embodiment of the present invention further provides a computer-readable storage medium, on which a program for implementing information transmission is stored. When the program is executed by a processor, the steps of the above-mentioned jet interference control optimization design method based on tail wing layout are implemented.

[0014] The use of the embodiments of the present invention may include the following beneficial effects: the embodiments of the present invention propose a rapid optimization design method based on passive control of the tail wing layout, which optimizes the design of key dimensions of the tail wing of the aircraft model, thereby reducing the impact of aerodynamic interference and improving the stability of intercepting missiles. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate one or more embodiments of this specification or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this specification. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0016] Figure 1 is a flow chart of a jet interference control optimization design method based on tail wing layout according to an embodiment of the present invention;

[0017] Figure 2 is a flow chart of a rapid optimization design method based on tail wing layout jet interference control according to an embodiment of the present invention;

[0018] Figure 3 is a schematic diagram of training results based on a proxy model according to an embodiment of the present invention;

[0019] Figure 4 It is a schematic diagram of a jet interference control optimization design system based on tail wing layout according to an embodiment of the present invention. DETAILED DESCRIPTION

[0020] In order to enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the following will be combined with the drawings in one or more embodiments of this specification to clearly and completely describe the technical solutions in one or more embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this specification, not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of this document.

[0021] Method Embodiment

[0022] According to an embodiment of the present invention, a jet interference control optimization design method based on tail wing layout is provided. Figure 1 FIG. 1 is a flow chart of a jet interference control optimization design method based on tail wing layout according to an embodiment of the present invention. Figure 1 As shown, the jet interference control optimization design method based on tail wing layout according to an embodiment of the present invention specifically includes:

[0023] Step S101, obtaining aerodynamic parameters of the aircraft jet interference flow field, and using the aerodynamic parameters as a sample set, specifically includes:

[0024] According to the optimization design requirements, corresponding simulation software is selected to establish an aircraft simulation model, the aircraft simulation model is used to perform simulation calculations, and the three-dimensional compressible Navier-Stokes equations are solved to obtain the aerodynamic parameters of the aircraft jet interference flow field;

[0025] Step S102, using the sample set to train the pre-built proxy model to obtain an optimal solution, specifically includes:

[0026] Using the sample set to train the pre-built proxy model, the tail layout of the aircraft simulation model is continuously optimized until an optimal solution is obtained;

[0027] Wherein, the proxy model is a Kriging model;

[0028] The optimal solution is the minimum orbit control jet interference torque;

[0029] Step S103, verifying the accuracy of the proxy model that obtains the optimal solution. If the verification result meets the preset requirements, the training is terminated; if the verification result does not meet the preset requirements, adding data points to the sample set and repeating steps S101-S103 until the verification result meets the preset requirements.

[0030] The above technical solution of the embodiment of the present invention is described in detail below in combination with the specific situation of the jet interference control optimization design method based on the tail wing layout of the embodiment of the present invention.

[0031] The embodiment of the present invention proposes a rapid optimization design method based on the jet interference control of the tail wing layout. By optimizing the design of the tail wing size of the aircraft model, the additional interference effect of the jet can be reduced and the stability of the intercepting missile can be improved.

[0032] The fast optimization design method based on tail wing layout jet interference control proposed in the embodiment of the present invention includes:

[0033] Step 1, obtaining a sample set, the sample data is obtained through numerical simulation, and the sample data is the calculated aerodynamic parameters;

[0034] Step 2, construct a proxy model based on the kriging model;

[0035] Step 3, training the proxy model through the sample set;

[0036] Step 4: Obtain the optimal solution (minimum orbit control jet interference torque) and verify the accuracy.

[0037] If the accuracy meets the requirements, the training ends; if not, new data points are added to the sample set for training until the accuracy is met.

[0038] The embodiment of the present invention proposes a rapid optimization design method based on tail layout jet interference control, which optimizes the tail angle arranged on the aircraft model. Figure 2 As shown, the purpose of the embodiment of the present invention is to optimize the orbit control jet interference torque by designing the tail layout. Taking the tail sweep angle as an example, the embodiment of the present invention includes the following steps:

[0039] (1) Establishing an aircraft model, for example, parametric modeling can be achieved by using 3D solid modeling software such as CATIA. Optionally, the established aircraft model is a cone-column skirt track control jet model.

[0040] (2) By solving the three-dimensional compressible Navier-Stokes equations, the jet interference flow field of the aircraft model is obtained.

[0041] The three-dimensional compressible Navier-Stokes equations are

[0042]

[0043] in, is a conserved variable, are the inviscid flux vectors in the x, y, and z directions respectively, are the viscous flux vectors in the x, y, and z directions respectively; t is time, x is the flow direction in the rectangular coordinate system, y is the normal direction in the rectangular coordinate system, and z is the circumferential direction in the rectangular coordinate system.

[0044] The steps for establishing the coordinate system are as follows: using a three-dimensional Cartesian rectangular coordinate system, the x-axis is along the flow direction of the model, the y-axis is along the normal direction, the z-axis is along the circumferential direction, and the coordinate origin O is selected as the midpoint of the leading edge of the model.

[0045] The above equations can be solved by commercial fluid simulation software or self-developed programs to obtain the aerodynamic parameters of the jet interference flow field.

[0046] (3) Optimize the design of the tail sweep angle, with the goal of reducing the pitch moment disturbance generated by the track control jet. Note that the tail sweep angle here is only an example, and may also be other geometric variables in the embodiments of the present invention.

[0047] The embodiment of the present invention controls a typical cone-shaped skirt track control jet model, with a flight Mach number of 8.0, a flight altitude of 25km, an angle of attack of 0°, and an optimized design of the tail sweep angle. The control target is to reduce the pitch moment interference generated by the track control jet. After calculation, if Figure 3 The figure shows the optimization result provided by the embodiment of the present invention. In this case, the interference torque caused by the track control jet is minimal, meeting the optimization goal.

[0048] System Example

[0049] According to an embodiment of the present invention, a jet interference control optimization design system based on tail wing layout is provided. Figure 4 FIG. 1 is a schematic diagram of a jet interference control optimization design system based on tail wing layout according to an embodiment of the present invention. Figure 4 As shown, the jet interference control optimization design system based on tail wing layout according to an embodiment of the present invention specifically includes:

[0050] The data module 40 is used to obtain the aerodynamic parameters of the aircraft jet interference flow field, and use the aerodynamic parameters as a sample set, specifically for:

[0051] According to the optimization design requirements, corresponding simulation software is selected to establish an aircraft simulation model, the aircraft simulation model is used to perform simulation calculations, and the three-dimensional compressible Navier-Stokes equations are solved to obtain the aerodynamic parameters of the aircraft jet interference flow field;

[0052] The training module 42 is used to train the pre-built proxy model using the sample set to obtain the optimal solution, specifically for:

[0053] Using the sample set to train the pre-built proxy model, the tail layout of the aircraft simulation model is continuously optimized until an optimal solution is obtained;

[0054] Wherein, the proxy model is a Kriging model;

[0055] The optimal solution is the minimum orbit control jet interference torque;

[0056] The verification module 44 is used to verify the accuracy of the proxy model that obtains the optimal solution. If the verification result meets the preset requirements, the training is terminated; if the verification result does not meet the preset requirements, the data module 40 to the verification module 44 are repeatedly executed after adding data points to the sample set until the verification result meets the preset requirements.

[0057] The embodiment of the present invention is a system embodiment corresponding to the above-mentioned method embodiment. The specific operations of each module can be understood by referring to the description of the method embodiment, which will not be repeated here.

[0058] In summary, the embodiments of the present invention have the following beneficial effects:

[0059] 1. The embodiment of the present invention provides a rapid optimization design method based on tail wing layout jet interference control, which optimizes the design of the tail wing arranged on the aircraft model.

[0060] 2. The embodiment of the present invention adopts a proxy model to obtain an optimized design result through fewer sample points.

[0061] Device Example 1

[0062] An embodiment of the present invention provides an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the computer program implements the steps described in the method embodiment when executed by the processor.

[0063] Device Example 2

[0064] An embodiment of the present invention provides a computer-readable storage medium, on which a program for implementing information transmission is stored. When the program is executed by a processor, the steps described in the method embodiment are implemented.

[0065] The computer-readable storage medium in this embodiment includes, but is not limited to, ROM, RAM, magnetic disk or optical disk, etc.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A jet interference control optimization design method based on tail wing layout, characterized in that include: S1: Acquire aerodynamic parameters of the aircraft jet interference flow field, and use the aerodynamic parameters as a sample set; S2: using the sample set to train the pre-built proxy model to obtain an optimal solution; S3: Verify the accuracy of the proxy model that obtains the optimal solution. If the verification result meets the preset requirements, end the training; if the verification result does not meet the preset requirements, add data points to the sample set and repeat steps S1-S3 until the verification result meets the preset requirements.

2. The method according to claim 1, characterized in that The S1 specifically includes: According to the optimization design requirements, the corresponding simulation software is selected to establish an aircraft simulation model, the aircraft simulation model is used to perform simulation calculations, and the three-dimensional compressible Navier-Stokes equations are solved to obtain the aerodynamic parameters of the aircraft jet interference flow field.

3. The method according to claim 1, characterized in that The S2 specifically includes: The sample set is used to train the pre-built proxy model, and the tail layout of the aircraft simulation model is continuously optimized until the optimal solution is obtained.

4. The method according to claim 3, characterized in that The proxy model is a Kriging model; The optimal solution is the minimum orbit control jet interference torque.

5. A jet interference control optimization design system based on tail wing layout, characterized in that include: A data module, used for obtaining aerodynamic parameters of the aircraft jet interference flow field, and using the aerodynamic parameters as a sample set; A training module, used to train a pre-built proxy model using the sample set to obtain an optimal solution; The verification module is used to verify the accuracy of the proxy model that obtains the optimal solution. If the verification result meets the preset requirements, the training is terminated; if the verification result does not meet the preset requirements, the data module to the verification module is repeatedly executed after adding data points to the sample set until the verification result meets the preset requirements.

6. The system according to claim 5, characterized in that The data module is specifically used for: According to the optimization design requirements, the corresponding simulation software is selected to establish an aircraft simulation model, the aircraft simulation model is used to perform simulation calculations, and the three-dimensional compressible Navier-Stokes equations are solved to obtain the aerodynamic parameters of the aircraft jet interference flow field.

7. The system according to claim 5, characterized in that The training module is specifically used for: The sample set is used to train the pre-built proxy model, and the tail layout of the aircraft simulation model is continuously optimized until the optimal solution is obtained.

8. The system according to claim 7, characterized in that The proxy model is a Kriging model; The optimal solution is the minimum orbit control jet interference torque.

9. An electronic device, characterized in that: include: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the computer program is executed by the processor, the steps of the method for optimizing the design of jet interference control based on the tail wing layout are implemented as described in any one of claims 1 to 4.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores an implementation program for information transmission, and when the program is executed by a processor, the steps of the jet interference control optimization design method based on tail wing layout as described in any one of claims 1 to 4 are implemented.

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