A method and system for determining the acoustic fatigue resistance form of thin-walled aircraft fuselage structure

Abstract

The present application belongs to the technical field of selecting the acoustic fatigue resistant form of thin-walled aircraft fuselage structures, and specifically relates to a method and system for determining the acoustic fatigue resistant form of thin-walled aircraft fuselage structures. On the basis of setting the acoustic fatigue resistant design goal and design constraints of the thin-walled fuselage structure, a combination of thin-walled fuselage structural forms is constructed, and then the thin-walled fuselage structural forms that meet the design requirements are screened, and with reference to the unit weight acoustic fatigue life benefit, an evaluation equation for the thin-walled fuselage structural form is constructed, and the optimal thin-walled fuselage structural form is calculated and determined, so that the optimal structural form can be obtained with high efficiency.

Description

Technical Field

[0001] The present application belongs to the technical field of selection of acoustic fatigue resistance forms of thin-walled aircraft fuselage structures, and specifically relates to a method and system for determining the acoustic fatigue resistance forms of thin-walled aircraft fuselage structures. Background Art

[0002] The thin-walled structure of the aircraft fuselage is in a high-intensity noise environment for a long time, and the resulting acoustic fatigue problem seriously restricts the long-term healthy use of the aircraft. The acoustic fatigue safety of the thin-walled structure of the fuselage needs to be considered during the design and development stage of advanced aircraft.

[0003] At present, during the aircraft design and development stage, the acoustic fatigue resistance design of the thin-walled structure of the aircraft fuselage is mainly divided into the acoustic load environment prediction and structural form selection in the aircraft preliminary design stage, and the acoustic fatigue life prediction, verification and local detail optimization and modification in the aircraft detailed design stage. The goals and focus of the acoustic fatigue resistance design of the thin-walled structure of the aircraft fuselage are different in the aircraft preliminary design stage and detailed design stage. The preliminary design stage requires the ability to quickly determine the structural form with a high acoustic fatigue life, while the detailed design stage requires the accurate prediction of the acoustic fatigue life under the premise of confirming the structural form, and improve the acoustic fatigue life through detail optimization.

[0004] At present, in the preliminary design stage of the aircraft, the form of the thin-walled structure of the fuselage is determined by the method of "sound fatigue life trial calculation of various structural forms + design experience judgment". It is extremely dependent on the level and experience of designers. The selection process is highly arbitrary and uncertain, inefficient, and prone to omissions, making it difficult to obtain the optimal anti-sound fatigue structure.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0006] The purpose of the present application is to provide a method and system for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage, so as to overcome or alleviate at least one of the technical deficiencies of the known ones.

[0007] The technical solution of this application is:

[0008] On the one hand, a method for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage is provided, comprising:

[0009] Steps for setting the design target of the fuselage thin-wall structure against acoustic fatigue: setting the design target of the fuselage thin-wall structure against acoustic fatigue, including the allowable range of the fundamental frequency, the maximum amplitude of the acoustic response, and the minimum acoustic fatigue life of the fuselage thin-wall structure;

[0010] Steps for setting design constraints of the fuselage thin-wall structure: setting design constraints of the fuselage thin-wall structure, including overall geometric size limits, maximum weight, and basic structure types of the fuselage thin-wall structure;

[0011] The steps of combining and constructing the fuselage thin-walled structural forms: combining and constructing the fuselage thin-walled structural forms based on the basic structure types and their geometric dimensions and material parameters under the overall geometric dimension restrictions, and eliminating the fuselage thin-walled structural forms that exceed the maximum weight;

[0012] Calculation steps for the acoustic fatigue resistance design parameters of the fuselage thin-wall structure: Calculate the acoustic fatigue resistance design parameters of each fuselage thin-wall structure, including the fundamental frequency, acoustic response amplitude, and acoustic fatigue life of the fuselage thin-wall structure;

[0013] Screening steps for fuselage thin-walled structures: Screening fundamental frequency, acoustic response amplitude, acoustic fatigue life, and fuselage thin-walled structures that meet the allowable range of fundamental frequency, maximum acoustic response amplitude, and minimum acoustic fatigue life;

[0014] Steps for determining the thin-wall structure of the fuselage: Taking the unit weight acoustic fatigue life benefit as a reference, construct an evaluation equation for the thin-wall structure of the fuselage, and calculate and determine the optimal thin-wall structure of the fuselage.

[0015] Optionally, in the above-mentioned method for determining the acoustic fatigue resistance form of the thin-walled structure of the fuselage of an aircraft, the basic structural types of the thin-walled structure of the fuselage include flat plates, curved plates, stiffened wall panels, box sections, and honeycombs.

[0016] Optionally, in the above-mentioned method for determining the acoustic fatigue resistance form of the thin-walled structure of the aircraft fuselage, the material parameters of the basic structure type are divided into parameters of isotropic metal materials and parameters of anisotropic composite materials;

[0017] The parameters of isotropic metal materials include Young's modulus, Poisson's ratio, and density;

[0018] The parameters of anisotropic composite materials include elastic parameters and density, wherein the elastic parameters include Young's modulus, shear modulus and Poisson's ratio in three directions.

[0019] Optionally, in the above-mentioned method for determining the acoustic fatigue resistance form of the aircraft fuselage thin-wall structure, the acoustic fatigue resistance design parameters of each fuselage thin-wall structure form are calculated, specifically using an engineering algorithm, and only considering the main resonance response.

[0020] Optionally, in the above-mentioned method for determining the acoustic fatigue resistance form of the aircraft fuselage thin-wall structure, the fuselage thin-wall structure form evaluation equation is constructed as follows:

[0021] F = N / m; or,

[0022] F = [N / (a•m)] × [1 / (b•p)]; or,

[0023] F = A × (N / m) + B × (N / p);

[0024] in,

[0025] F is the benefit of the thin-walled structure of the fuselage;

[0026] N is the acoustic fatigue life of the thin-walled structure of the fuselage;

[0027] m is the weight of the thin-walled structure of the fuselage;

[0028] a is the first type weighting coefficient of the fuselage thin-wall structure weight;

[0029] A is the second type of weighting coefficient for the weight of the thin-walled structure of the fuselage;

[0030] p is the material and processing cost of the thin-walled structure of the fuselage;

[0031] b is the first type weighted coefficient of the fuselage thin-wall structure material and its processing cost;

[0032] B is the second type of weighted coefficient for the fuselage thin-walled structure material and its processing cost.

[0033] On the other hand, a system for determining the anti-acoustic fatigue form of a thin-walled structure of an aircraft fuselage is provided, which is used to implement any of the above-mentioned methods for determining the anti-acoustic fatigue form of a thin-walled structure of an aircraft fuselage, comprising:

[0034] The module for setting the acoustic fatigue resistance design target of the fuselage thin-wall structure is used to set the acoustic fatigue resistance design target of the fuselage thin-wall structure, including the allowable range of the fundamental frequency of the fuselage thin-wall structure, the maximum amplitude of the acoustic response, and the minimum acoustic fatigue life;

[0035] The fuselage thin-wall structure design constraint setting module is used to set the design constraints of the fuselage thin-wall structure, including the overall geometric size limit, maximum weight, and basic structure type of the fuselage thin-wall structure;

[0036] A fuselage thin-walled structural form combination construction module is used to combine and construct fuselage thin-walled structural forms based on basic structural types and their geometric dimensions and material parameters under the overall geometric dimension restrictions, and to eliminate fuselage thin-walled structural forms that exceed the maximum weight;

[0037] The module for calculating the acoustic fatigue resistance design parameters of the fuselage thin-wall structure is used to calculate the acoustic fatigue resistance design parameters of each fuselage thin-wall structure, including the fundamental frequency, acoustic response amplitude, and acoustic fatigue life of the fuselage thin-wall structure;

[0038] Screening module for fuselage thin-walled structure: used to screen the fundamental frequency, acoustic response amplitude, acoustic fatigue life, and fuselage thin-walled structure that meets the allowable range of fundamental frequency, maximum acoustic response amplitude, and minimum acoustic fatigue life;

[0039] Fuselage thin-wall structure form determination module: It is used to construct the fuselage thin-wall structure form evaluation equation based on the unit weight acoustic fatigue life benefit, and calculate and determine the optimal fuselage thin-wall structure form.

[0040] Optionally, in the above-mentioned system for determining the acoustic fatigue resistance form of the thin-walled structure of the fuselage of an aircraft, the basic structural types of the thin-walled structure of the fuselage include flat plates, curved plates, stiffened wall panels, box sections, and honeycombs.

[0041] Optionally, in the above-mentioned system for determining the acoustic fatigue resistance form of the thin-walled structure of the aircraft fuselage, the material parameters of the basic structure type are divided into parameters of isotropic metal materials and parameters of anisotropic composite materials;

[0042] The parameters of isotropic metal materials include Young's modulus, Poisson's ratio, and density;

[0043] The parameters of anisotropic composite materials include elastic parameters and density, wherein the elastic parameters include Young's modulus, shear modulus and Poisson's ratio in three directions.

[0044] Optionally, in the above-mentioned aircraft fuselage thin-wall structure anti-acoustic fatigue form determination system, the anti-acoustic fatigue design parameters of each fuselage thin-wall structure form are calculated, specifically using an engineering algorithm, and only considering the main resonance response.

[0045] Optionally, in the above-mentioned aircraft fuselage thin-wall structure anti-acoustic fatigue form determination system, the fuselage thin-wall structure form evaluation equation is constructed as follows:

[0046] F = N / m; or,

[0047] F = [N / (a•m)] × [1 / (b•p)]; or,

[0048] F = A × (N / m) + B × (N / p);

[0049] in,

[0050] F is the benefit of the thin-walled structure of the fuselage;

[0051] N is the acoustic fatigue life of the thin-walled structure of the fuselage;

[0052] m is the weight of the thin-walled structure of the fuselage;

[0053] a is the first type weighting coefficient of the fuselage thin-wall structure weight;

[0054] A is the second type of weighting coefficient for the weight of the thin-walled structure of the fuselage;

[0055] p is the material and processing cost of the thin-walled structure of the fuselage;

[0056] b is the first type weighted coefficient of the fuselage thin-wall structure material and its processing cost;

[0057] B is the second type of weighted coefficient for the fuselage thin-walled structure material and its processing cost.

[0058] This application has at least the following beneficial technical effects:

[0059] Provided are a method and system for determining the acoustic fatigue resistance form of a thin-walled fuselage structure of an aircraft. On the basis of setting the acoustic fatigue resistance design goal and design constraints of the thin-walled fuselage structure, a combination of thin-walled structural forms of the fuselage is constructed, and then the thin-walled structural forms of the fuselage that meet the design requirements are screened, and an evaluation equation for the thin-walled fuselage structure is constructed with reference to the acoustic fatigue life benefit per unit weight, and the optimal thin-walled fuselage structure is determined by calculation, so that the optimal structural form can be obtained with high efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] Figure 1 is a schematic diagram of a method for determining the anti-acoustic fatigue form of a thin-walled structure of an aircraft fuselage provided in an embodiment of the present application;

[0061] Figure 2 It is a schematic diagram of a system for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage provided in an embodiment of the present application.

[0062] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0063] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0064] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the elements or objects appearing before the term include the elements or objects listed after the term and their equivalents, but do not exclude other elements or objects.

[0065] On the one hand, the present application provides a method for determining the anti-acoustic fatigue form of a thin-walled structure of an aircraft fuselage, such as Figure 1 shown.

[0066] Steps for setting design goals for acoustic fatigue resistance of thin-walled fuselage structures.

[0067] Set the acoustic fatigue resistance design goals of the thin-walled fuselage structure, including the allowable range of the fundamental frequency of the thin-walled fuselage structure, the maximum amplitude of the acoustic response, and the minimum acoustic fatigue life.

[0068] The allowable range of the fundamental frequency of the thin-walled fuselage structure is set according to the frequency spectrum characteristics of the load environment of the thin-walled fuselage structure, and the maximum frequency of the load environment needs to be avoided to avoid resonance.

[0069] The maximum amplitude of the acoustic response of the thin-walled structure of the fuselage is the upper limit of the acoustic response amplitude of the thin-walled structure of the fuselage, which can be determined according to the aircraft design requirements.

[0070] The minimum acoustic fatigue life of the thin-walled fuselage structure is the lower limit of the acoustic fatigue life of the thin-walled fuselage structure and can be determined according to the aircraft design requirements.

[0071] Steps for setting constraints in fuselage thin-wall structure design.

[0072] Set the design constraints of the thin-walled fuselage structure, including the overall geometric size limit, maximum weight, and basic structure type of the thin-walled fuselage structure.

[0073] The overall geometric dimension limitations of the fuselage thin-wall structure include the upper and lower limits of the overall length, width, and thickness of the fuselage thin-wall structure, which can be determined based on the aircraft design requirements.

[0074] The maximum weight of the thin-walled fuselage structure can be determined based on the aircraft design requirements.

[0075] The basic structural types of the fuselage thin-wall structure are the common basic structural types that constitute the fuselage thin-wall structure, which may specifically include flat plates, curved plates, stiffened wall panels, box sections, honeycombs, etc.

[0076] Combined construction steps of fuselage thin-wall structure form.

[0077] Based on the basic structure types, their geometric dimensions and material parameters, and within the overall geometric dimension constraints, fuselage thin-walled structural forms are combined and constructed, and those that exceed the maximum weight are eliminated.

[0078] By combining and constructing the thin-walled structure of the fuselage, the principles of the thin-walled structure design of the fuselage, such as strength requirements, can be designed and constructed automatically in a programmed manner.

[0079] The materials of the basic structure can be divided into isotropic metal materials and anisotropic composite materials. The material parameters of metal materials include Young's modulus, Poisson's ratio, and density. Composite materials can be homogenized and equivalent to orthotropic materials, and the material parameters include elastic parameters and density. Among them, the elastic parameters include Young's modulus, shear modulus, and Poisson's ratio in three directions.

[0080] Calculation steps for the acoustic fatigue resistance design parameters of the thin-walled fuselage structure.

[0081] Calculate the anti-acoustic fatigue design parameters of each fuselage thin-wall structure, including the fundamental frequency, acoustic response amplitude, and acoustic fatigue life of the fuselage thin-wall structure.

[0082] The anti-acoustic fatigue design parameters of each thin-walled fuselage structure can be automatically calculated by engineering algorithm programming. The mathematical calculation of engineering algorithm is relatively simple and efficient, and it is easy to program and automate. ESDU, "Aircraft Structure Acoustic Fatigue Design Manual", "Modern Fighter Structure Dynamic Strength Design Technical Guide" and other reference books list many engineering calculation methods and fatigue life curves of materials required for calculating acoustic fatigue life. When calculating the anti-acoustic fatigue design parameters of each thin-walled fuselage structure, the acoustic response characteristics of the thin-walled fuselage structure are considered. It can be assumed that only the response of the main resonance peak is large, and only the main resonance response is considered to construct the corresponding acoustic response amplitude and acoustic fatigue life calculation model.

[0083] Screening steps for thin-walled fuselage structures.

[0084] The screening of fundamental frequency, acoustic response amplitude, acoustic fatigue life, and the thin-walled structure of the fuselage that meets the allowable range of fundamental frequency, maximum acoustic response amplitude, and minimum acoustic fatigue life can be performed automatically through programming.

[0085] Steps to determine the thin-wall structure of the fuselage.

[0086] With reference to the acoustic fatigue life benefit per unit weight, an evaluation equation for the thin-wall structure of the fuselage is constructed, and the optimal thin-wall structure of the fuselage is calculated and determined, which can be performed automatically through programming.

[0087] The evaluation equation of the fuselage thin-wall structure can be specifically constructed as follows:

[0088] F = N / m;

[0089] in,

[0090] F is the benefit of the thin-wall structure of the fuselage. The larger the calculated value is, the better the thin-wall structure of the fuselage is.

[0091] N is the acoustic fatigue life of the thin-walled structure of the fuselage;

[0092] m is the weight of the thin-walled structure of the fuselage.

[0093] If the material and processing cost of the thin-walled structure of the fuselage are taken into consideration, the following optimization design can be performed on the evaluation equation of the thin-walled structure of the fuselage:

[0094] F = [N / (a•m)] × [1 / (b•p)];

[0095] in,

[0096] a is the first type of weighting coefficient of the weight of the thin-walled structure of the fuselage, and the value range is 1 to 10. The higher the degree of concern about the weight of the thin-walled structure of the fuselage, the smaller the value;

[0097] p is the material and processing cost of the thin-walled structure of the fuselage;

[0098] b is the first type of weighted coefficient of the fuselage thin-walled structure material and its processing cost, and the value range is 1~10. The higher the attention paid to the fuselage thin-walled structure material and its processing cost, the smaller the value is, and the design constraint a+b=10 can be used.

[0099] Or the fuselage thin-wall structure form evaluation equation is optimized as follows:

[0100] F = A × (N / m) + B × (N / p);

[0101] in,

[0102] A is the second type of weighting coefficient of the weight of the thin-walled structure of the fuselage, and the value range is 0~1. The higher the degree of concern about the weight of the thin-walled structure of the fuselage, the larger the value;

[0103] B is the second type of weighted coefficient for the fuselage thin-walled structural material and its processing cost, and its value range can be 0~1. The higher the level of concern about the fuselage thin-walled structural material and its processing cost, the larger the value, and the design constraint A+B=1 can be used.

[0104] The method for determining the acoustic fatigue resistance form of the thin-walled structure of an aircraft fuselage disclosed in the above-mentioned embodiment, on the basis of setting the acoustic fatigue resistance design goal and design constraints of the thin-walled structure of the fuselage, combines and constructs the thin-walled structure form of the fuselage, and then screens out the thin-walled structure form of the fuselage that meets the design requirements, and uses the unit weight acoustic fatigue life benefit as a reference to construct an evaluation equation for the thin-walled structure form of the fuselage, calculates and determines the optimal thin-walled structure form of the fuselage, and can obtain the optimal structure form with high efficiency.

[0105] On the other hand, a system for determining the acoustic fatigue resistance of a thin-walled structure of an aircraft fuselage is provided. Figure 2 As shown, including:

[0106] The module for setting the acoustic fatigue resistance design target of the fuselage thin-wall structure is used to set the acoustic fatigue resistance design target of the fuselage thin-wall structure, including the allowable range of the fundamental frequency of the fuselage thin-wall structure, the maximum amplitude of the acoustic response, and the minimum acoustic fatigue life;

[0107] The fuselage thin-wall structure design constraint setting module is used to set the design constraints of the fuselage thin-wall structure, including the overall geometric size limit, maximum weight, and basic structure type of the fuselage thin-wall structure;

[0108] A fuselage thin-walled structural form combination construction module is used to combine and construct fuselage thin-walled structural forms based on basic structural types and their geometric dimensions and material parameters under the overall geometric dimension restrictions, and to eliminate fuselage thin-walled structural forms that exceed the maximum weight;

[0109] The module for calculating the acoustic fatigue resistance design parameters of the fuselage thin-wall structure is used to calculate the acoustic fatigue resistance design parameters of each fuselage thin-wall structure, including the fundamental frequency, acoustic response amplitude, and acoustic fatigue life of the fuselage thin-wall structure;

[0110] Screening module for fuselage thin-walled structure: used to screen the fundamental frequency, acoustic response amplitude, acoustic fatigue life, and fuselage thin-walled structure that meets the allowable range of fundamental frequency, maximum acoustic response amplitude, and minimum acoustic fatigue life;

[0111] Fuselage thin-wall structure form determination module: It is used to construct the fuselage thin-wall structure form evaluation equation based on the unit weight acoustic fatigue life benefit, and calculate and determine the optimal fuselage thin-wall structure form.

[0112] In some optional embodiments, in the above-mentioned aircraft fuselage thin-wall structure anti-acoustic fatigue form determination system, the basic structural types of fuselage thin-wall structures include flat plates, curved plates, stiffened wall panels, box sections, and honeycombs.

[0113] In some optional embodiments, in the above-mentioned system for determining the acoustic fatigue resistance form of the thin-walled structure of the aircraft fuselage, the material parameters of the basic structure type are divided into parameters of isotropic metal materials and parameters of anisotropic composite materials;

[0114] The parameters of isotropic metal materials include Young's modulus, Poisson's ratio, and density;

[0115] The parameters of anisotropic composite materials include elastic parameters and density, wherein the elastic parameters include Young's modulus, shear modulus and Poisson's ratio in three directions.

[0116] In some optional embodiments, in the above-mentioned aircraft fuselage thin-wall structure anti-acoustic fatigue form determination system, the anti-acoustic fatigue design parameters of each fuselage thin-wall structure form are calculated, specifically using an engineering algorithm, and assuming that only the response of the main resonance peak is large.

[0117] In some optional embodiments, in the above-mentioned aircraft fuselage thin-wall structure anti-acoustic fatigue form determination system, the fuselage thin-wall structure form evaluation equation is constructed as follows:

[0118] F = N / m; or,

[0119] F = [N / (a•m)] × [1 / (b•p)]; or,

[0120] F = A × (N / m) + B × (N / p);

[0121] in,

[0122] F is the benefit of the thin-walled structure of the fuselage;

[0123] N is the acoustic fatigue life of the thin-walled structure of the fuselage;

[0124] m is the weight of the thin-walled structure of the fuselage;

[0125] a is the first type weighting coefficient of the fuselage thin-wall structure weight;

[0126] A is the second type of weighting coefficient for the weight of the thin-walled structure of the fuselage;

[0127] p is the material and processing cost of the thin-walled structure of the fuselage;

[0128] b is the first type weighted coefficient of the fuselage thin-wall structure material and its processing cost;

[0129] B is the second type of weighted coefficient for the fuselage thin-walled structure material and its processing cost.

[0130] Regarding the system for determining the anti-acoustic fatigue form of the thin-walled structure of an aircraft fuselage disclosed in the above-mentioned embodiment, since it corresponds to the method for determining the anti-acoustic fatigue form of the thin-walled structure of an aircraft fuselage disclosed in the above-mentioned embodiment, the description is relatively simple. For specific related matters, please refer to the relevant description of the part of the method for determining the anti-acoustic fatigue form of the thin-walled structure of an aircraft fuselage. Its technical effects can also refer to the technical effects of the relevant parts of the method for determining the anti-acoustic fatigue form of the thin-walled structure of an aircraft fuselage, and will not be repeated here.

[0131] In addition, technicians in the field should also be able to realize that the various modules of the aircraft fuselage thin-walled structure anti-acoustic fatigue form determination system disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, this application generally describes them according to their functions. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Technicians in the field can choose to adopt different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0132] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A method for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage, characterized in that: include: Steps for setting the design target of the fuselage thin-wall structure against acoustic fatigue: setting the design target of the fuselage thin-wall structure against acoustic fatigue, including the allowable range of the fundamental frequency, the maximum amplitude of the acoustic response, and the minimum acoustic fatigue life of the fuselage thin-wall structure; Steps for setting design constraints of the fuselage thin-wall structure: setting design constraints of the fuselage thin-wall structure, including overall geometric size limits, maximum weight, and basic structure types of the fuselage thin-wall structure; The steps of combining and constructing the fuselage thin-walled structural forms: combining and constructing the fuselage thin-walled structural forms based on the basic structure types and their geometric dimensions and material parameters under the overall geometric dimension restrictions, and eliminating the fuselage thin-walled structural forms that exceed the maximum weight; Calculation steps for the acoustic fatigue resistance design parameters of the fuselage thin-wall structure: Calculate the acoustic fatigue resistance design parameters of each fuselage thin-wall structure, including the fundamental frequency, acoustic response amplitude, and acoustic fatigue life of the fuselage thin-wall structure; Screening steps for fuselage thin-walled structures: Screening fundamental frequency, acoustic response amplitude, acoustic fatigue life, and fuselage thin-walled structures that meet the allowable range of fundamental frequency, maximum acoustic response amplitude, and minimum acoustic fatigue life; The steps for determining the thin-wall structure of the fuselage are as follows: taking the unit weight acoustic fatigue life benefit as a reference, constructing the evaluation equation for the thin-wall structure of the fuselage, and calculating and determining the optimal thin-wall structure of the fuselage; The evaluation equation for the thin-walled structure of the fuselage is constructed as follows: F = N / m; or, F = [N / (a•m)] × [1 / (b•p)]; or, F = A × (N / m) + B × (N / p); in, F is the benefit of the thin-walled structure of the fuselage; N is the acoustic fatigue life of the thin-walled structure of the fuselage; m is the weight of the thin-walled structure of the fuselage; a is the first type weighting coefficient of the fuselage thin-wall structure weight; A is the second type of weighting coefficient for the weight of the thin-walled structure of the fuselage; p is the material and processing cost of the thin-walled structure of the fuselage; b is the first type weighted coefficient of the fuselage thin-wall structure material and its processing cost; B is the second type of weighted coefficient for the fuselage thin-walled structure material and its processing cost.

2. The method for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage according to claim 1, characterized in that: The basic structural types of fuselage thin-wall structures include flat plates, curved plates, stiffened wall panels, box sections, and honeycombs.

3. The method for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage according to claim 1, characterized in that: The material parameters of the basic structural types are divided into parameters of isotropic metal materials and parameters of anisotropic composite materials; The parameters of isotropic metal materials include Young's modulus, Poisson's ratio, and density; The parameters of anisotropic composite materials include elastic parameters and density, wherein the elastic parameters include Young's modulus, shear modulus and Poisson's ratio in three directions.

4. The method for determining the acoustic fatigue resistance form of a thin-walled structure of an aircraft fuselage according to claim 1, characterized in that: The acoustic fatigue resistance design parameters of each thin-walled fuselage structure are calculated using an engineering algorithm and only the main resonance response is considered.

5. A system for determining the anti-acoustic fatigue form of a thin-walled structure of an aircraft fuselage, used to implement the method for determining the anti-acoustic fatigue form of a thin-walled structure of an aircraft fuselage according to claim 1, characterized in that: include: The module for setting the acoustic fatigue resistance design target of the fuselage thin-wall structure is used to set the acoustic fatigue resistance design target of the fuselage thin-wall structure, including the allowable range of the fundamental frequency of the fuselage thin-wall structure, the maximum amplitude of the acoustic response, and the minimum acoustic fatigue life; The fuselage thin-wall structure design constraint setting module is used to set the design constraints of the fuselage thin-wall structure, including the overall geometric size limit, maximum weight, and basic structure type of the fuselage thin-wall structure; A fuselage thin-walled structural form combination construction module is used to combine and construct fuselage thin-walled structural forms based on basic structural types and their geometric dimensions and material parameters under the overall geometric dimension restrictions, and to eliminate fuselage thin-walled structural forms that exceed the maximum weight; The module for calculating the acoustic fatigue resistance design parameters of the fuselage thin-wall structure is used to calculate the acoustic fatigue resistance design parameters of each fuselage thin-wall structure, including the fundamental frequency, acoustic response amplitude, and acoustic fatigue life of the fuselage thin-wall structure; Screening module for fuselage thin-walled structure: used to screen the fundamental frequency, acoustic response amplitude, acoustic fatigue life, and fuselage thin-walled structure that meets the allowable range of fundamental frequency, maximum acoustic response amplitude, and minimum acoustic fatigue life; Fuselage thin-wall structure form determination module: used to construct the fuselage thin-wall structure form evaluation equation based on the unit weight acoustic fatigue life benefit, and calculate and determine the optimal fuselage thin-wall structure form; The evaluation equation for the thin-walled structure of the fuselage is constructed as follows: F = N / m; or, F = [N / (a•m)] × [1 / (b•p)]; or, F = A × (N / m) + B × (N / p); in, F is the benefit of the thin-walled structure of the fuselage; N is the acoustic fatigue life of the thin-walled structure of the fuselage; m is the weight of the thin-walled structure of the fuselage; a is the first type weighting coefficient of the fuselage thin-wall structure weight; A is the second type of weighting coefficient for the weight of the thin-walled structure of the fuselage; p is the material and processing cost of the thin-walled structure of the fuselage; b is the first type weighted coefficient of the fuselage thin-wall structure material and its processing cost; B is the second type of weighted coefficient for the fuselage thin-walled structure material and its processing cost.

6. The system for determining the acoustic fatigue resistance of thin-walled aircraft fuselage structures according to claim 5, characterized in that: The basic structural types of fuselage thin-wall structures include flat plates, curved plates, stiffened wall panels, box sections, and honeycombs.

7. The system for determining the acoustic fatigue resistance of thin-walled aircraft fuselage structures according to claim 5, characterized in that: The material parameters of the basic structural types are divided into parameters of isotropic metal materials and parameters of anisotropic composite materials; The parameters of isotropic metal materials include Young's modulus, Poisson's ratio, and density; The parameters of anisotropic composite materials include elastic parameters and density, wherein the elastic parameters include Young's modulus, shear modulus and Poisson's ratio in three directions.

8. The system for determining the anti-acoustic fatigue form of the aircraft fuselage thin-walled structure according to claim 5, characterized in that: The acoustic fatigue resistance design parameters of each thin-walled fuselage structure are calculated using an engineering algorithm and only the main resonance response is considered.

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