Aircraft riding quality evaluation method and system, electronic product and medium thereof

Abstract

The invention provides an aircraft riding quality evaluation method and system, an electronic product and a medium thereof, and aims to establish an aircraft normal overload turbulence response function, establish an aircraft turbulence frequency spectrum function, establish an aircraft normal overload frequency spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence frequency spectrum function, and then establish a normal overload frequency weight function to evaluate the riding quality of an aircraft. And establishing an aircraft riding quality frequency spectrum function by using an aircraft normal overload frequency spectrum function and a normal overload frequency weighting function, calculating the aircraft riding quality according to common frequency integral, and evaluating the aircraft riding quality, so that a more reliable means is provided for evaluating the aircraft riding quality, and the aircraft design can be better served.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft ride quality assessment, and specifically relates to an aircraft ride quality assessment method, system, electronic product and medium thereof. Background Art

[0002] When an aircraft flies in the atmosphere, it often encounters atmospheric turbulence, which produces unexpected additional overloads, vibrations and bumps, resulting in a decrease in the aircraft's ride quality.

[0003] When designing an aircraft, especially a large aircraft, it is necessary to evaluate the ride quality of the aircraft to determine whether the ride quality of the designed aircraft meets the requirements.

[0004] Currently, the ride quality of an aircraft is mostly evaluated by calculating the root mean square of normal acceleration, which requires calculating the root mean square of acceleration at a selected frequency. However, the human body has different sensitivities to different vibration frequencies, and existing evaluation methods do not take this difference into account, resulting in a large difference between the calculated ride quality and the actual experience, making it difficult to effectively evaluate the ride quality of an aircraft.

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

[0006] The purpose of this application is to provide an aircraft ride quality evaluation method, system, electronic product and medium

[0007] , to overcome or alleviate at least one of the known technical deficiencies.

[0008] The technical solution of this application is:

[0009] On the one hand, a method for evaluating aircraft ride quality is provided, comprising:

[0010] The steps of establishing the aircraft normal overload turbulence response function are as follows: establishing the aircraft normal overload turbulence response function;

[0011] Steps for establishing aircraft turbulence spectrum function: establishing aircraft turbulence spectrum function;

[0012] The steps of establishing the normal overload spectrum function of an aircraft are as follows: establishing the normal overload spectrum function of an aircraft based on the normal overload turbulence response function of the aircraft and the turbulence spectrum function of the aircraft;

[0013] Steps for establishing a normal overload frequency weight function: establishing a normal overload frequency weight function;

[0014] The steps of establishing the aircraft ride quality spectrum function are as follows: establishing the aircraft ride quality spectrum function by using the aircraft normal overload spectrum function and the normal overload frequency weight function;

[0015] Aircraft ride quality calculation steps: Calculate the aircraft ride quality by frequency integration using the aircraft ride quality spectrum function.

[0016] Optionally, in the above-mentioned aircraft ride quality evaluation method, in the step of establishing the aircraft normal overload turbulence response function, the aircraft normal overload turbulence response function is established, specifically:

[0017]

[0018] in,

[0019] is the aircraft normal overload turbulence response function;

[0020] V * is the current flight speed;

[0021] To trim the aircraft for lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack;

[0022] is the turbulence transfer function for aircraft speed and angle of attack.

[0023] Optionally, in the above-mentioned aircraft ride quality evaluation method, in the step of establishing an aircraft turbulence spectrum function, establishing an aircraft turbulence spectrum function is specifically as follows:

[0024]

[0025] in,

[0026] is the aircraft turbulence spectrum function;

[0027] is the intensity of turbulence in the x-axis and y-axis directions;

[0028] is the size of the turbulence in the x-axis and y-axis directions;

[0029] ω is the turbulence frequency;

[0030] l is the wingspan of the aircraft;

[0031] i is the imaginary number symbol.

[0032] Optionally, in the above-mentioned aircraft ride quality assessment method, in the step of establishing an aircraft normal overload spectrum function, establishing an aircraft normal overload spectrum function is specifically as follows:

[0033]

[0034] in,

[0035] is the aircraft normal overload spectrum function.

[0036] Optionally, in the above-mentioned aircraft ride quality evaluation method, in the step of establishing a normal overload frequency weight function, a normal overload frequency weight function is established, specifically:

[0037]

[0038] in,

[0039] W(ω) is the normal overload frequency weight function.

[0040] Optionally, in the above-mentioned aircraft ride quality evaluation method, in the step of establishing an aircraft ride quality spectrum function, establishing an aircraft ride quality spectrum function is specifically:

[0041]

[0042] in,

[0043] Φ R (ω) is the aircraft ride quality spectrum function.

[0044] Optionally, in the above-mentioned aircraft ride quality evaluation method, in the aircraft ride quality calculation step, the aircraft ride quality is calculated by:

[0045]

[0046] in,

[0047] D i For the quality of the aircraft ride;

[0048] ω f Calculate cutoff frequencies for aircraft ride quality;

[0049] Calculates the starting frequency for ride quality.

[0050] Optionally, in the above-mentioned aircraft ride quality evaluation method, in the aircraft ride quality calculation step, the ride quality calculation starting frequency Take 0.1.

[0051] Another aspect provides an aircraft ride quality assessment system, comprising:

[0052] An aircraft normal overload turbulence response function establishment module is used to establish an aircraft normal overload turbulence response function;

[0053] An aircraft turbulence spectrum function establishment module is used to establish an aircraft turbulence spectrum function;

[0054] The aircraft normal overload spectrum function establishment module establishes the aircraft normal overload spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence spectrum function;

[0055] A normal overload frequency weight function establishment module is used to establish a normal overload frequency weight function;

[0056] Aircraft ride quality spectrum function establishment module: establish the aircraft ride quality spectrum function based on the aircraft normal overload spectrum function and normal overload frequency weight function;

[0057] Aircraft ride quality calculation module: calculates the aircraft ride quality by frequency integration using the aircraft ride quality spectrum function.

[0058] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the aircraft normal overload turbulence response function establishment module, an aircraft normal overload turbulence response function is established, specifically:

[0059]

[0060] in,

[0061] is the aircraft normal overload turbulence response function;

[0062] V * is the current flight speed;

[0063] To trim the aircraft for lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack;

[0064] is the turbulence transfer function for aircraft speed and angle of attack.

[0065] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the aircraft turbulence spectrum function establishment module, an aircraft turbulence spectrum function is established, specifically:

[0066]

[0067] in,

[0068] is the aircraft turbulence spectrum function;

[0069] is the intensity of turbulence in the x-axis and y-axis directions;

[0070] is the size of the turbulence in the x-axis and y-axis directions;

[0071] ω is the turbulence frequency;

[0072] l is the wingspan of the aircraft;

[0073] i is the imaginary number symbol.

[0074] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the aircraft normal overload spectrum function establishment module, an aircraft normal overload spectrum function is established, specifically:

[0075]

[0076] in,

[0077] is the aircraft normal overload spectrum function.

[0078] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the normal overload frequency weight function establishment module, a normal overload frequency weight function is established, specifically:

[0079]

[0080] in,

[0081] W(ω) is the normal overload frequency weight function.

[0082] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the aircraft ride quality spectrum function establishment module, an aircraft ride quality spectrum function is established, specifically:

[0083]

[0084] in,

[0085] Φ R (ω) is the aircraft ride quality spectrum function.

[0086] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the aircraft ride quality calculation module, the aircraft ride quality is calculated by:

[0087]

[0088] in,

[0089] D i For the quality of the aircraft ride;

[0090] ω f Calculate cutoff frequencies for aircraft ride quality;

[0091] Calculates the starting frequency for ride quality.

[0092] Optionally, in the above-mentioned aircraft ride quality evaluation system, in the aircraft ride quality calculation module, the ride quality calculation starting frequency Take 0.1.

[0093] Another aspect provides an electronic device, comprising:

[0094] processor;

[0095] The memory stores a computer program, wherein the computer program is configured to implement any of the above-mentioned aircraft ride quality evaluation methods when executed by the processor.

[0096] On the other hand, an electronic medium is provided, which is a computer-readable storage medium. The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, any of the above-mentioned aircraft ride quality evaluation methods can be implemented.

[0097] This application has at least the following beneficial technical effects:

[0098] Provided are an aircraft ride quality evaluation method, system, electronic product and medium thereof. Based on the aircraft turbulence response equation, an aircraft turbulence transfer coefficient equation is established, an aircraft turbulence transfer function is established, thereby establishing an aircraft normal overload turbulence response function, and an aircraft turbulence spectrum function is established. Then, the aircraft normal overload turbulence response function and the aircraft turbulence spectrum function are used to establish an aircraft normal overload spectrum function, and then a normal overload frequency weight function is established. Subsequently, the aircraft normal overload spectrum function and the normal overload frequency weight function are used to establish an aircraft ride quality spectrum function. The aircraft ride quality is calculated according to the commonly used frequency integrals, and the aircraft ride quality is evaluated. This provides a more reliable means for aircraft ride quality evaluation and can better serve aircraft design. BRIEF DESCRIPTION OF THE DRAWINGS

[0099] Figure 1 is a schematic diagram of an aircraft ride quality evaluation method provided in an embodiment of the present application;

[0100] Figure 2 is a schematic diagram of an aircraft ride quality evaluation system provided in an embodiment of the present application.

[0101] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0102] 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.

[0103] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0104] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0105] On one hand, the present application provides an aircraft ride quality evaluation method, which provides acceleration functions of different frequencies according to the sensitivity level of the human body to different vibration frequencies, and then calculates the ride quality considering the vibration sensitivity, so as to obtain a more accurate aircraft ride quality calculation result, such as Figure 1 shown.

[0106] Steps for establishing the aircraft normal overload turbulence response function: Establish the aircraft normal overload turbulence response function.

[0107]

[0108] in,

[0109] is the aircraft normal overload turbulence response function;

[0110] V * is the current flight speed;

[0111] To trim the aircraft for lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack;

[0112] is the turbulence transfer function for aircraft speed and angle of attack, which can be determined by referring to the following steps:

[0113] S1. Establish the aircraft turbulence response equation.

[0114]

[0115] in,

[0116] s is the Laplace operator; g is the gravitational acceleration;

[0117] It is the derivative of the aircraft's X-axis force and Y-axis force to the flight speed V and the angle of attack α;

[0118] is the aircraft pitch moment to flight speed V, angle of attack α, and angle of attack derivative Pitch rate ω z The derivative of

[0119] △V is the change of the aircraft's flight speed, △α is the change of the aircraft's angle of attack, and △θ is the change of the aircraft's pitch angle;

[0120] V * is the trim point speed;

[0121] W x is the x-axis component of the turbulent velocity, W y is the y-axis component of the turbulent velocity, W yx is the gradient of the y-axis component of the turbulent velocity in the x-axis direction.

[0122] Changes in atmospheric turbulence can To express.

[0123] S2. Based on the aircraft turbulence response equation, establish the aircraft speed and angle of attack turbulence response function.

[0124]

[0125]

[0126] in,

[0127] det, is the intermediate calculation coefficient.

[0128] The aircraft normal overload is calculated as:

[0129] Steps for establishing aircraft turbulence spectrum function: Establish aircraft turbulence spectrum function.

[0130]

[0131] in,

[0132] is the aircraft turbulence spectrum function;

[0133] is the intensity of turbulence in the x-axis and y-axis directions;

[0134] is the size of the turbulence in the x-axis and y-axis directions;

[0135] ω is the turbulence frequency;

[0136] l is the wingspan of the aircraft;

[0137] i is the imaginary number symbol;

[0138] Steps for establishing the aircraft normal overload spectrum function: establish the aircraft normal overload spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence spectrum function.

[0139]

[0140] in,

[0141] is the aircraft normal overload spectrum function.

[0142] Steps for establishing a normal overload frequency weight function: Establish a normal overload frequency weight function.

[0143]

[0144] in,

[0145] W(ω) is the normal overload frequency weight function, which is designed considering the human body’s sensitivity to vibration frequency.

[0146] Steps for establishing an aircraft ride quality spectrum function: establish an aircraft ride quality spectrum function based on an aircraft normal overload spectrum function and a normal overload frequency weight function.

[0147]

[0148] in,

[0149] Φ R (ω) is the aircraft ride quality spectrum function.

[0150] Aircraft ride quality calculation steps: Calculate the aircraft ride quality by frequency integration using the aircraft ride quality spectrum function.

[0151]

[0152] in,

[0153] D i For the quality of the aircraft ride;

[0154] ω f Calculate the cutoff frequency for the aircraft ride quality, above which the turbulence response is not significant, which can also be obtained through testing or simulation;

[0155] Calculate the starting frequency for ride quality, which can be 0.1.

[0156] In a specific example, the aircraft ride quality evaluation method disclosed in the above embodiment is implemented as follows:

[0157] The calculation of aircraft aerodynamic derivatives under different speed conditions is shown in the following table:

[0158] The intensity and scale of different turbulence are shown in the following table:

[0159] The calculation results of aircraft ride quality are shown in the following table:

[0160] The aircraft ride quality evaluation method disclosed in the above embodiment establishes an aircraft speed and angle of attack turbulence response function based on the aircraft turbulence response equation, thereby establishing an aircraft normal overload turbulence response function, and establishing an aircraft turbulence spectrum function, and then establishing an aircraft normal overload spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence spectrum function, and then establishing a normal overload frequency weight function, and then establishing an aircraft ride quality spectrum function based on the aircraft normal overload spectrum function and the normal overload frequency weight function, and then calculating the aircraft ride quality according to the commonly used frequency integral, and evaluating the aircraft ride quality, providing a more reliable means for aircraft ride quality evaluation, which can better serve aircraft design.

[0161] The aircraft ride quality evaluation method disclosed in the above embodiment has a rigorous theoretical basis. According to the normal overload spectrum function and the weight function of the normal overload to the vibration frequency, the ride quality within the commonly used frequency range is obtained by integration, which can effectively improve the calculation accuracy of the aircraft ride quality.

[0162] On the other hand, a system for evaluating the ride quality of an aircraft is provided. Figure 2 As shown, including:

[0163] An aircraft normal overload turbulence response function establishment module is used to establish an aircraft normal overload turbulence response function;

[0164] An aircraft turbulence spectrum function establishment module is used to establish an aircraft turbulence spectrum function;

[0165] The aircraft normal overload spectrum function establishment module establishes the aircraft normal overload spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence spectrum function;

[0166] A normal overload frequency weight function establishment module is used to establish a normal overload frequency weight function;

[0167] Aircraft ride quality spectrum function establishment module: establish the aircraft ride quality spectrum function based on the aircraft normal overload spectrum function and normal overload frequency weight function;

[0168] Aircraft ride quality calculation module: calculates the aircraft ride quality by frequency integration using the aircraft ride quality spectrum function.

[0169] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the aircraft normal overload turbulence response function establishment module, an aircraft normal overload turbulence response function is established, specifically:

[0170]

[0171] in,

[0172] is the aircraft normal overload turbulence response function;

[0173] V * is the current flight speed;

[0174] To trim the aircraft for lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack;

[0175] is the turbulence transfer function for aircraft speed and angle of attack.

[0176] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the aircraft turbulence spectrum function establishment module, an aircraft turbulence spectrum function is established, specifically:

[0177]

[0178] in,

[0179] is the aircraft turbulence spectrum function;

[0180] is the intensity of turbulence in the x-axis and y-axis directions;

[0181] is the size of the turbulence in the x-axis and y-axis directions;

[0182] ω is the turbulence frequency;

[0183] l is the wingspan of the aircraft;

[0184] i is the imaginary number symbol.

[0185] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the aircraft normal overload spectrum function establishment module, an aircraft normal overload spectrum function is established, specifically:

[0186]

[0187] in,

[0188] is the aircraft normal overload spectrum function.

[0189] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the normal overload frequency weight function establishment module, a normal overload frequency weight function is established, specifically:

[0190]

[0191] in,

[0192] W(ω) is the normal overload frequency weight function.

[0193] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the aircraft ride quality spectrum function establishment module, an aircraft ride quality spectrum function is established, specifically:

[0194]

[0195] in,

[0196] Φ R (ω) is the aircraft ride quality spectrum function.

[0197] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the aircraft ride quality calculation module, the aircraft ride quality is calculated as follows:

[0198]

[0199] in,

[0200] D i For the quality of the aircraft ride;

[0201] ω f Calculate cutoff frequencies for aircraft ride quality;

[0202] Calculates the starting frequency for ride quality.

[0203] Furthermore, in the above-mentioned aircraft ride quality evaluation system, in the aircraft ride quality calculation module, the ride quality calculation starting frequency Take 0.1.

[0204] As the aircraft ride quality assessment system disclosed in the above embodiment corresponds to the aircraft ride quality assessment method disclosed in the above embodiment, the description is relatively simple. For specific related matters, please refer to the relevant description of the aircraft ride quality assessment method part. Its technical effects can also refer to the technical effects of the relevant part of the aircraft ride quality assessment method, which will not be repeated here.

[0205] In addition, technicians in the field should also be able to realize that the various modules of the aircraft ride quality evaluation 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.

[0206] Another aspect provides an electronic device, comprising:

[0207] processor;

[0208] A memory stores a computer program, wherein the computer program is configured to implement any of the above-mentioned aircraft ride quality evaluation methods when executed by the processor.

[0209] In some optional embodiments, the processor can be a central processing unit CPU or other form of processing unit with data processing capability and / or instruction execution capability, can be a general-purpose processor or a special-purpose processor, and can control other components in the compensation electronic device to perform the desired functions.

[0210] In some optional embodiments, the memory may include various forms of computer-readable storage media, such as volatile memory and / or non-volatile memory, the volatile memory may be a random access memory RAM and / or a cache memory cache, and the non-volatile memory may be a read-only memory ROM, a hard disk, a flash memory, etc. The memory may store a computer program, and the processor runs the computer program to implement the functions in the embodiments of the present application and / or other desired functions. In addition, various application programs and various data may also be stored.

[0211] In some optional embodiments, the processor and the memory may be connected via a bus system, which may be a serial or parallel communication bus or the like.

[0212] It should be noted that, for the sake of clarity and brevity, not all components of the electronic device are shown in the above embodiments. To implement the necessary functions of the electronic device, technicians in the field can provide and set other components not shown according to specific needs.

[0213] For the electronic device disclosed in the above embodiments, since its processor can implement any of the above-mentioned aircraft ride quality evaluation methods when executing the computer program stored in its memory, its technical effects can be correspondingly referred to the technical effects of the above-mentioned aircraft ride quality evaluation method part, which will not be repeated here.

[0214] On the other hand, an electronic medium is provided, which is a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, any of the above-mentioned aircraft ride quality evaluation methods can be implemented.

[0215] In some optional embodiments, the computer-readable storage medium may include a memory card of a smartphone, a storage component of a tablet computer, a hard disk of a personal computer, a random access memory RAM, a read-only memory ROM, an erasable programmable read-only memory EPROM, a portable compact disk read-only memory CD-ROM, flash memory, or any combination of the above storage media, or other applicable storage media.

[0216] 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 evaluating aircraft ride quality, characterized in that: include: The steps of establishing the aircraft normal overload turbulence response function are as follows: establishing the aircraft normal overload turbulence response function; Steps for establishing aircraft turbulence spectrum function: establishing aircraft turbulence spectrum function; The steps of establishing the normal overload spectrum function of an aircraft are as follows: establishing the normal overload spectrum function of an aircraft based on the normal overload turbulence response function of the aircraft and the turbulence spectrum function of the aircraft; Steps for establishing a normal overload frequency weight function: establishing a normal overload frequency weight function; The steps of establishing the aircraft ride quality spectrum function are as follows: establishing the aircraft ride quality spectrum function by using the aircraft normal overload spectrum function and the normal overload frequency weight function; Aircraft ride quality calculation steps: Calculate the aircraft ride quality by frequency integration using the aircraft ride quality spectrum function.

2. The aircraft ride quality evaluation method according to claim 1, characterized in that: In the step of establishing the aircraft normal overload turbulence response function, the aircraft normal overload turbulence response function is established, specifically: in, is the aircraft normal overload turbulence response function; V * is the current flight speed; To trim the aircraft for lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack; is the turbulence transfer function for aircraft speed and angle of attack.

3. The aircraft ride quality evaluation method according to claim 2, characterized in that: In the step of establishing the aircraft turbulence spectrum function, the aircraft turbulence spectrum function is established, specifically: in, is the aircraft turbulence spectrum function; is the intensity of turbulence in the x-axis and y-axis directions; is the size of the turbulence in the x-axis and y-axis directions; ω is the turbulence frequency; l is the aircraft wingspan; i is the imaginary number symbol.

4. The aircraft ride quality evaluation method according to claim 3, characterized in that: In the step of establishing the aircraft normal overload spectrum function, the aircraft normal overload spectrum function is established, specifically: in, is the aircraft normal overload spectrum function.

5. The aircraft ride quality evaluation method according to claim 4, characterized in that: In the step of establishing the normal overload frequency weight function, a normal overload frequency weight function is established, specifically: in, W(ω) is the normal overload frequency weight function.

6. The aircraft ride quality evaluation method according to claim 5, characterized in that: In the step of establishing the aircraft ride quality spectrum function, the aircraft ride quality spectrum function is established, specifically: in, Φ R (ω) is the aircraft ride quality spectrum function.

7. The aircraft ride quality evaluation method according to claim 6, characterized in that: In the aircraft ride quality calculation step, the aircraft ride quality is calculated, specifically: in, D i For the quality of the aircraft ride; ω f Calculate cutoff frequencies for aircraft ride quality; Calculates the starting frequency for ride quality.

8. The aircraft ride quality evaluation method according to claim 7, characterized in that: In the aircraft ride quality calculation step, the ride quality calculation starting frequency Take 0.

1.

9. An aircraft ride quality evaluation system, characterized in that: include: An aircraft normal overload turbulence response function establishment module is used to establish an aircraft normal overload turbulence response function; An aircraft turbulence spectrum function establishment module is used to establish an aircraft turbulence spectrum function; The aircraft normal overload spectrum function establishment module establishes the aircraft normal overload spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence spectrum function; A normal overload frequency weight function establishment module is used to establish a normal overload frequency weight function; Aircraft ride quality spectrum function establishment module: establish the aircraft ride quality spectrum function based on the aircraft normal overload spectrum function and normal overload frequency weight function; Aircraft ride quality calculation module: calculates the aircraft ride quality by frequency integration using the aircraft ride quality spectrum function.

10. The aircraft ride quality evaluation system according to claim 9, characterized in that: In the aircraft normal overload turbulence response function establishment module, the aircraft normal overload turbulence response function is established, specifically: in, is the aircraft normal overload turbulence response function; V * is the current flight speed; To trim the aircraft for lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack; is the turbulence transfer function for aircraft speed and angle of attack.

11. The aircraft ride quality evaluation system according to claim 10, characterized in that: In the aircraft turbulence spectrum function establishment module, the aircraft turbulence spectrum function is established, specifically: in, is the aircraft turbulence spectrum function; is the intensity of turbulence in the x-axis and y-axis directions; is the size of the turbulence in the x-axis and y-axis directions; ω is the turbulence frequency; l is the aircraft wingspan; i is the imaginary number symbol.

12. The aircraft ride quality evaluation system according to claim 11, characterized in that: In the aircraft normal overload spectrum function establishment module, the aircraft normal overload spectrum function is established, specifically: in, is the aircraft normal overload spectrum function.

13. The aircraft ride quality evaluation system according to claim 12, characterized in that: In the normal overload frequency weight function establishment module, a normal overload frequency weight function is established, specifically: in, W(ω) is the normal overload frequency weight function.

14. The aircraft ride quality evaluation system according to claim 13, characterized in that: In the aircraft ride quality spectrum function establishment module, an aircraft ride quality spectrum function is established, specifically: in, Φ R (ω) is the aircraft ride quality spectrum function.

15. The aircraft ride quality evaluation system according to claim 14, characterized in that: In the aircraft ride quality calculation module, the aircraft ride quality is calculated, specifically: in, D i For the quality of the aircraft ride; ω f Calculate cutoff frequencies for aircraft ride quality; Calculates the starting frequency for ride quality.

16. The aircraft ride quality evaluation system according to claim 15, characterized in that: In the aircraft ride quality calculation module, the ride quality calculation start frequency Take 0.

1.

17. An electronic device, characterized in that: include: processor; A memory storing a computer program, wherein the computer program is configured to implement the aircraft ride quality evaluation method of claim 1 when executed by the processor.

18. An electronic medium, characterized in that: The electronic medium is a computer-readable storage medium, which stores a computer program. When the computer program is executed by a processor, the aircraft ride quality evaluation method according to claim 1 can be implemented.

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