Hypersonic aircraft modification method and system based on supersonic area law

Abstract

The embodiment of the invention provides a hypersonic aircraft modification method and system based on a supersonic area law, and the method comprises the steps: obtaining the forward projection area distribution of the Mach-plane cut section of each component of the initial configuration of a ridge-shaped combined hypersonic aircraft at each meridian angle under the design Mach number; according to the forward projection area distribution of each component at each meridian angle, obtaining the average equivalent revolution body area distribution corresponding to each component, and further obtaining the average equivalent revolution body first area distribution of the whole configuration; establishing a second area distribution with a low-resistance characteristic based on the first area distribution of the average equivalent revolution body of the initial configuration; removing the average equivalent revolution body area distribution of the non-modification part from the second area distribution to obtain third area distribution of the to-be-modified part corresponding to the ideal area distribution of the whole configuration; and according to the third area distribution, the to-be-shaped part is shaped, and a new configuration shape is obtained.

Description

Technical Field

[0001] This document relates to the technical field of hypersonic aircraft, and in particular to a hypersonic aircraft shaping method and system based on the supersonic area law. Background Art

[0002] As a flight configuration, the ridge assembly is widely used in the aerodynamic shape design of hypersonic aircraft. Modifying the ridge assembly type hypersonic aircraft to obtain low drag characteristics is an important way to achieve its excellent aerodynamic performance. As an aircraft design theory for the purpose of drag reduction, the area law (which can be divided into transonic area law and supersonic area law) aims to obtain low drag characteristics by reasonably arranging the relevant cross-sectional area distribution of the aircraft, and has been successfully applied to the design of various transonic and supersonic aircraft models. However, in the field of hypersonic aircraft design, the application research of the area law is currently very lacking.

[0003] The key to the aircraft shaping technology based on the supersonic area law lies in the average equivalent rotational body area distribution corresponding to the aircraft and whether the reasonable adjustment of the area distribution is feasible and simple to operate. In the traditional aircraft design based on the supersonic area law, by designing the fuselage as a rotational body and shaping the fuselage, it is feasible and simple to adjust the average equivalent rotational body area distribution corresponding to the entire aircraft to approach the ideal area distribution. However, the aerodynamic shape of hypersonic aircraft is very different from that of traditional aircraft. Except for missiles, other hypersonic aircraft parts are rarely designed with a complete rotational body shape. The original shaping method is no longer feasible and simple to operate. Therefore, regarding the shaping application of the supersonic area law on hypersonic aircraft, it is also necessary to develop an aircraft shaping technology method based on the supersonic area law, including aircraft configuration selection and shaping specific details. Summary of the invention

[0004] One or more embodiments of this specification provide a hypersonic aircraft shaping method based on a supersonic area law, comprising:

[0005] Under the design Mach number, the forward projection area distribution of the Mach surface intercept section of each component of the initial configuration of the ridge-shaped assembly hypersonic aircraft at each meridian angle is obtained;

[0006] According to the forward projection area distribution of each component at each meridian angle, the average equivalent rotational body area distribution corresponding to each component is obtained, and then the average equivalent rotational body first area distribution of the entire configuration is obtained;

[0007] Establishing a second area distribution having low resistance characteristics based on the average equivalent gyroid first area distribution of the initial configuration;

[0008] Removing the average equivalent swirl area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the to-be-modified component corresponding to the ideal area distribution of the entire configuration;

[0009] According to the third area distribution, the component to be modified is modified to obtain a new configuration shape.

[0010] Furthermore, the ridge-shaped assembly-type hypersonic aircraft includes a volume component for providing additional volume and a lift component for providing lift for the entire configuration.

[0011] Furthermore, the volume component is a proposed reshaping component, and the appearance of the proposed reshaping component is a partially rotated body; the lift component is a non-reshaping component.

[0012] Furthermore, the second area distribution is a Sias-Hake area distribution.

[0013] Furthermore, the specific method of modifying the component to be modified according to the third area distribution to obtain a new configuration shape is:

[0014] The radius distribution of the volume component with a partial rotational body shape is adjusted, thereby adjusting the average equivalent rotational body area distribution of the volume component and the average equivalent rotational body area distribution of the entire configuration.

[0015] One or more embodiments of this specification provide a hypersonic aircraft shaping system based on a supersonic area law, comprising:

[0016] The forward projection area distribution acquisition module is used to obtain the forward projection area distribution of the Mach surface intercept section of each component of the initial configuration of the ridge-shaped assembly type hypersonic aircraft at each meridian angle under the design Mach number;

[0017] The first area distribution acquisition module is used to obtain the average equivalent rotational body area distribution corresponding to each component according to the forward projection area distribution of each component at each meridian angle, and then obtain the average equivalent rotational body first area distribution of the initial configuration;

[0018] A second area distribution acquisition module: used to establish a second area distribution with low resistance characteristics based on the average equivalent swirl first area distribution of the initial configuration;

[0019] A third area distribution acquisition module: used for removing the average equivalent rotational body area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the to-be-modified component corresponding to the ideal area distribution of the entire configuration;

[0020] Reshaping module: used to reshape the part to be reshaped according to the third area distribution to obtain a new configuration shape.

[0021] Furthermore, the ridge-shaped assembly-type hypersonic aircraft includes a volume component for providing additional volume and a lift component for providing lift for the entire configuration; the volume component is a proposed reshaping component, and the proposed reshaping component has an outer shape of a partially rotated body; the lift component is a non-reshaping component.

[0022] Furthermore, the second area distribution is a Sias-Hake area distribution.

[0023] One or more embodiments of the present specification provide an electronic device, including:

[0024] processor; and,

[0025] A memory arranged to store computer executable instructions, which, when executed, cause the processor to implement the steps of the hypersonic aircraft shaping method based on the supersonic area law.

[0026] One or more embodiments of the present specification provide a storage medium for storing computer-executable instructions, which, when executed, implement the steps of the hypersonic aircraft shaping method based on the supersonic area law.

[0027] According to the embodiment of the present invention, the average equivalent rotational body area distribution of the aircraft itself and its components is obtained, and then an ideal area distribution with low resistance characteristics for the entire configuration is established according to the average equivalent rotational body area distribution of the entire configuration. The average equivalent rotational body area distribution of the non-modified components is removed from the ideal area distribution of the entire configuration to obtain the area distribution of the to-be-modified components corresponding to the ideal area distribution of the entire configuration. The to-be-modified components are modified according to the area distribution, and the to-be-modified components are defined as a partial rotational body shape, thereby solving the operational feasibility and simplicity problems of the aircraft shaping technology based on the supersonic area law in the design of hypersonic aircraft. The average equivalent rotational body area distribution of the new configuration shape obtained after the shaping is completed is close to the ideal area distribution and has low resistance characteristics, thereby solving the problem of the prior art lacking an effective theoretical basis in the design of ridge-shaped assembly type hypersonic aircraft. A modified ridge-shaped assembly type hypersonic aircraft is designed based on the supersonic area law, and the design process is short, there is no need to establish an aerodynamic model to solve aerodynamic values ​​for iterative shape optimization, the computing resource usage is small, and the output results are effective.

[0028] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented according to the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] 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.

[0030] Figure 1 A flow chart of a hypersonic vehicle shaping method based on a supersonic area law provided for one or more embodiments of this specification;

[0031] Figure 2 A schematic diagram of components of a ridge-shaped assembly-type hypersonic aircraft provided for one or more embodiments of this specification.

[0032] Figure 3 A schematic diagram of the forward projection area of ​​a Mach surface section of a ridge-shaped assembly-type hypersonic aircraft at a given meridian angle is provided for one or more embodiments of the present specification.

[0033] Figure 4 A schematic diagram of the appearance of a ridge-shaped assembly-type hypersonic aircraft after modification is provided for one or more embodiments of the present specification.

[0034] Figure 5 The average equivalent rotational body area distribution of a ridge-shaped assembly type hypersonic aircraft before and after shaping and the shaping standard for area distribution - Sias-Hake area distribution provided for one or more embodiments of this specification;

[0035] Figure 6 A schematic diagram of the composition of a hypersonic aircraft shaping system based on a supersonic area law provided in one or more embodiments of this specification;

[0036] Figure 7 A schematic diagram of the structure of an electronic device provided for one or more embodiments of this specification. DETAILED DESCRIPTION

[0037] 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.

[0038] Method Embodiment

[0039] According to an embodiment of the present invention, a hypersonic vehicle shaping method based on a supersonic area law is provided. Figure 1 A flow chart of a hypersonic vehicle shaping method based on a supersonic area law is provided for one or more embodiments of this specification, such as Figure 1 As shown, the hypersonic aircraft shaping method based on the supersonic area law according to an embodiment of the present invention specifically includes:

[0040] S1. Obtain the forward projection area distribution of the Mach surface cut-off section of each component of the initial configuration of the ridge-shaped assembly type hypersonic aircraft at each meridian angle at the design Mach number;

[0041] The ridge-shaped assembly-type hypersonic aircraft includes a volume component (hereinafter referred to as component I) that provides additional volume and a lift component (hereinafter referred to as component II) that provides lift for the entire configuration. Specifically, component I is a proposed reshaping component, which is designed as a partially rotated body shape; component II is a non-reshaping component.

[0042] S2. According to the forward projection area distribution of each component at each meridian angle, the average equivalent rotational body area distribution corresponding to each component is obtained, and then the average equivalent rotational body first area distribution of the initial configuration is obtained;

[0043] Specifically, the average equivalent rotational volume area distribution A of a component is the average value of the forward projection area distribution A(θ, x) of the Mach surface intercept section at each meridian angle.

[0044]

[0045] S3. Establishing a second area distribution having low resistance characteristics based on the average equivalent swirl first area distribution of the initial configuration;

[0046] The ideal area distribution with low resistance characteristics for the entire configuration is the Sias-Hake area distribution, which can be written as:

[0047]

[0048] Optionally, A max is the maximum projected area, x k is the maximum projected area A max The most recent position, x max is the total length of the entire projected area distribution.

[0049] S4. removing the average equivalent volume area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the proposed modified component corresponding to the ideal area distribution of the entire configuration;

[0050] S5. According to the third area distribution, the component to be modified is modified to obtain a new configuration shape.

[0051] Among them, the radius distribution of component I with a partial rotational body shape is adjusted, and then the average equivalent rotational body area distribution of component I and the average equivalent rotational body area distribution of the entire configuration are adjusted to approach the ideal area distribution of the entire configuration.

[0052] Specifically, there is a linear correspondence between the average equivalent rotational body area distribution of the partial rotational body and the forward projection area distribution of the corresponding complete rotational body. For example, the average equivalent rotational body area distribution of one-third of the rotational body is also one-third of the forward projection area distribution of the corresponding complete rotational body, and so on. The shaping of the intended shaping component of the partial rotational body can be converted into shaping the corresponding complete rotational body, and the forward projection area distribution of the complete rotational body is only related to the rotational body radius distribution, and has nothing to do with the meridian angle. Shaping only requires adjusting its radius distribution, thereby achieving the purpose of convenient shaping.

[0053] In a specific embodiment, reference Figure 2 As shown, a ridge-shaped assembly-type hypersonic aircraft is taken as an example.

[0054] 1) When the design Mach number is M = 5, since the aircraft has a plane-symmetrical shape, A(x,θ) = A(x,π-θ) ， Meridian angle range can be selected Select Meridian Angle Obtain the forward projection area distribution of the Mach surface cut-off section of each component of the initial configuration of the ridge-shaped assembly hypersonic aircraft at the above meridian angle.

[0055] 2) Obtaining the average equivalent rotational volume area distribution corresponding to each component, and then obtaining the average equivalent rotational volume area distribution of the entire configuration;

[0056] Among them, the average equivalent rotation volume area distribution of the components is

[0057]

[0058] The average equivalent isomeric area distribution of the entire configuration is

[0059]

[0060] 3) Establish an ideal area distribution with low resistance characteristics for the entire configuration based on the average equivalent gyroscopic area distribution of the initial configuration.

[0061] The ideal area distribution with low resistance characteristics for the entire configuration is the Sias-Hake area distribution.

[0062]

[0063] The maximum projected area A max The maximum projected area is the same as the initial configuration. x max is the total length of the average equivalent gyrosome projected area distribution of the initial configuration.

[0064] 4) Obtain the area distribution of the proposed modified part corresponding to the ideal area distribution of the entire configuration

[0065]

[0066] 5) Distribution by area The radius distribution of component I is adjusted, and a new configuration shape is obtained after completion. The initial configuration shape wave drag coefficient is 0.0119, and the wave drag coefficient is reduced to 0.0112 after the modification, and the drag is reduced by 6%.

[0067] The beneficial effects of the present invention are as follows:

[0068] The feasibility and convenient application of the vehicle shaping technology based on the supersonic area law in the design of hypersonic aircraft has been realized; compared with the existing ridge-shaped assembly hypersonic aircraft design technology, it has a clear and effective theoretical support, and the output results are effective; the design process is short, and there is no need to establish an aerodynamic model to solve aerodynamic values ​​for iterative shape optimization, and the computing resources occupied are small.

[0069] System Example

[0070] According to an embodiment of the present invention, a schematic diagram of the composition of a hypersonic aircraft shaping system based on a supersonic area law provided in one or more embodiments of this specification is provided. Figure 6 A schematic diagram of a hypersonic aircraft shaping system based on a supersonic area law is provided for one or more embodiments of this specification, such as Figure 6 As shown, according to an embodiment of the present invention, a schematic diagram of a hypersonic aircraft shaping system based on a supersonic area law provided for one or more embodiments of this specification specifically includes:

[0071] The forward projection area distribution acquisition module 60 is used to respectively acquire the forward projection area distribution of the Mach surface intercept section of each component of the initial configuration of the ridge-shaped assembly type hypersonic aircraft at each meridian angle under the design Mach number;

[0072] The first area distribution acquisition module 62 is used to obtain the average equivalent rotational volume area distribution corresponding to each component according to the forward projection area distribution of each component at each meridian angle, and then obtain the average equivalent rotational volume first area distribution of the initial configuration;

[0073] The second area distribution acquisition module 64 is used to establish a second area distribution with low resistance characteristics based on the average equivalent rotational body first area distribution of the initial configuration;

[0074] A third area distribution acquisition module 66 is used to remove the average equivalent rotational volume area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the to-be-modified component corresponding to the ideal area distribution of the entire configuration;

[0075] The shaping module 68 is used to shape the component to be shaped according to the third area distribution to obtain a new configuration shape.

[0076] 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.

[0077] Device Example 1

[0078] An embodiment of the present invention provides an electronic device, such as Figure 7 As shown, it includes: a memory 70, a processor 72, and a computer program stored in the memory 70 and executable on the processor 72, and when the computer program is executed by the processor 72, the following method steps are implemented:

[0079] S1. Obtain the forward projection area distribution of the Mach surface cut-off section of each component of the initial configuration of the ridge-shaped assembly type hypersonic aircraft at each meridian angle at the design Mach number;

[0080] S2. According to the forward projection area distribution of each component at each meridian angle, the average equivalent rotational body area distribution corresponding to each component is obtained, and then the average equivalent rotational body first area distribution of the entire configuration is obtained;

[0081] S3. Establishing a second area distribution having low resistance characteristics based on the average equivalent swirl first area distribution of the initial configuration;

[0082] S4. removing the average equivalent volume area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the proposed modified component corresponding to the ideal area distribution of the entire configuration;

[0083] S5. According to the third area distribution, the component to be modified is modified to obtain a new configuration shape.

[0084] Device Example 2

[0085] 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 the processor 72, the following method steps are implemented:

[0086] S1. Obtain the forward projection area distribution of the Mach surface cut-off section of each component of the initial configuration of the ridge-shaped assembly type hypersonic aircraft at each meridian angle at the design Mach number;

[0087] S2. According to the forward projection area distribution of each component at each meridian angle, the average equivalent rotational body area distribution corresponding to each component is obtained, and then the average equivalent rotational body first area distribution of the entire configuration is obtained;

[0088] S3. Establishing a second area distribution having low resistance characteristics based on the average equivalent swirl first area distribution of the initial configuration;

[0089] S4. removing the average equivalent volume area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the proposed modified component corresponding to the ideal area distribution of the entire configuration;

[0090] S5. According to the third area distribution, the component to be modified is modified to obtain a new configuration shape.

[0091] The computer-readable storage medium in this embodiment includes, but is not limited to, ROM, RAM, magnetic disk or optical disk, etc.

[0092] 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 hypersonic vehicle shaping method based on supersonic area law, characterized in that: include: Under the design Mach number, the forward projection area distribution of the Mach surface intercept section of each component of the initial configuration of the ridge-shaped assembly hypersonic aircraft at each meridian angle is obtained; According to the forward projection area distribution of each component at each meridian angle, the average equivalent rotational body area distribution corresponding to each component is obtained, and then the average equivalent rotational body first area distribution of the initial configuration is obtained; Establishing a second area distribution having low resistance characteristics based on the average equivalent gyroid first area distribution of the initial configuration; Removing the average equivalent swirl area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the to-be-modified component corresponding to the ideal area distribution of the entire configuration; According to the third area distribution, the component to be modified is modified to obtain a new configuration shape.

2. The method according to claim 1, characterized in that The ridge-shaped assembly-type hypersonic aircraft includes a volume component for providing additional volume and a lift component for providing lift for the entire configuration.

3. The method according to claim 2, characterized in that The volume component is a proposed reshaping component, and the appearance of the proposed reshaping component is a partially rotated body; the lift component is a non-reshaping component.

4. The method according to claim 1, characterized in that: The second area distribution is the Sias-Hake area distribution.

5. The method according to claim 1, characterized in that The specific method of modifying the component to be modified according to the third area distribution to obtain a new configuration shape is: The radius distribution of the volume component with a partial rotational body shape is adjusted, thereby adjusting the average equivalent rotational body area distribution of the volume component and the average equivalent rotational body area distribution of the entire configuration.

6. A hypersonic vehicle shaping system based on supersonic area law, characterized in that: include: The forward projection area distribution acquisition module is used to obtain the forward projection area distribution of the Mach surface intercept section of each component of the initial configuration of the ridge-shaped assembly type hypersonic aircraft at each meridian angle under the design Mach number; The first area distribution acquisition module is used to obtain the average equivalent rotational body area distribution corresponding to each component according to the forward projection area distribution of each component at each meridian angle, and then obtain the average equivalent rotational body first area distribution of the initial configuration; A second area distribution acquisition module: used to establish a second area distribution with low resistance characteristics based on the average equivalent swirl first area distribution of the initial configuration; A third area distribution acquisition module: used for removing the average equivalent rotational body area distribution of the non-modified component from the second area distribution to obtain a third area distribution of the to-be-modified component corresponding to the ideal area distribution of the entire configuration; Reshaping module: used to reshape the part to be reshaped according to the third area distribution to obtain a new configuration shape.

7. The system according to claim 6, characterized in that The ridge-shaped assembly-type hypersonic aircraft includes a volume component for providing additional volume and a lift component for providing lift for the entire configuration; the volume component is a proposed reshaping component, and the proposed reshaping component has an outer shape of a partially rotated body; the lift component is a non-reshaping component.

8. The system according to claim 6, characterized in that The second area distribution is the Sias-Hake area distribution.

9. An electronic device, characterized in that: include: processor; as well as, A memory arranged to store computer executable instructions, wherein when the computer executable instructions are executed, the processor implements the steps of the hypersonic aircraft shaping method based on the supersonic area law according to any one of claims 1 to 6.

10. A storage medium, characterized in that: Used to store computer executable instructions, which, when executed, implement the steps of the hypersonic aircraft shaping method based on the supersonic area law as described in any one of claims 1 to 6.

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