An aircraft ride quality evaluation method and system, electronic product and medium thereof

Abstract

Provided are an aircraft ride quality evaluation method and system, an electronic product, and a medium thereof. An aircraft normal load turbulence response function is established, and an aircraft turbulence spectrum function is established. Then, an aircraft normal load spectrum function is established based on the aircraft normal load turbulence response function and the aircraft turbulence spectrum function. A normal load frequency weight function is then established. Subsequently, an aircraft ride quality spectrum function is established based on the aircraft normal load spectrum function and the normal load frequency weight function. The aircraft ride quality is calculated by integrating the aircraft ride quality spectrum function according to a common frequency, and the aircraft ride quality is evaluated. The aircraft ride quality evaluation provides a more reliable means for serving aircraft design.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft ride quality evaluation, and particularly relates to an aircraft ride quality evaluation method and system, an electronic product and a medium thereof. BACKGROUND

[0002] When an aircraft flies in the atmosphere, it often encounters atmospheric turbulence, which produces undesirable additional overloads, vibrations and jolts, resulting in a decline in the ride quality of the aircraft.

[0003] When designing an aircraft, especially a large aircraft, the ride quality of the aircraft needs to be evaluated to determine whether the ride quality of the designed aircraft meets the requirements.

[0004] Currently, the ride quality of the aircraft is evaluated by calculating the root mean square of the normal acceleration, which requires calculating the root mean square of the acceleration at the selected frequency. However, the sensitivity of the human body to different vibration frequencies is not the same, and the existing evaluation method does not consider this difference, resulting in a large difference between the calculated ride quality and the real feeling, making it difficult to effectively evaluate the ride quality of the aircraft.

[0005] The present application is proposed in view of the existence of the above technical defects. SUMMARY

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

[0007] to overcome or alleviate at least one aspect of the known technical defects.

[0008] The technical solution of the present application is:

[0009] In one aspect, an aircraft ride quality evaluation method is provided, comprising:

[0010] An aircraft normal overload turbulence response function establishing step: establishing an aircraft normal overload turbulence response function;

[0011] An aircraft turbulence frequency spectrum function establishing step: establishing an aircraft turbulence frequency spectrum function;

[0012] An aircraft normal overload frequency spectrum function establishing step: establishing an aircraft normal overload frequency spectrum function based on the aircraft normal overload turbulence response function and the aircraft turbulence frequency spectrum function;

[0013] A normal overload frequency weight function establishing step: establishing a normal overload frequency weight function;

[0014] An aircraft ride quality frequency spectrum function establishing step: establishing an aircraft ride quality frequency spectrum function based on the aircraft normal overload frequency spectrum function and the normal overload frequency weight function;

[0015] The aircraft ride quality calculation step is to calculate the aircraft ride quality by frequency integration according to the aircraft ride quality spectrum function.

[0016] Optionally, in the aircraft ride quality evaluation method, the step of establishing the aircraft normal load turbulence response function is specifically as follows:

[0017]

[0018] wherein,

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

[0020] V * is the current flight speed;

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

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

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

[0024]

[0025] wherein,

[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 turbulence in the x-axis and y-axis directions;

[0029] ω is the turbulence frequency;

[0030] l is the aircraft wingspan;

[0031] i is the imaginary symbol.

[0032] Optionally, in the aircraft ride quality evaluation method, the step of establishing the aircraft normal load spectrum function is specifically as follows:

[0033]

[0034] wherein,

[0035] A spectrum function of normal acceleration of the aircraft.

[0036] Optionally, in the method for evaluating the ride quality of the aircraft, the step of establishing the frequency weight function of the normal acceleration comprises:

[0037]

[0038] wherein,

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

[0040] Optionally, in the method for evaluating the ride quality of the aircraft, the step of establishing the spectrum function of the ride quality of the aircraft comprises:

[0041]

[0042] wherein,

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

[0044] Optionally, in the method for evaluating the ride quality of the aircraft, the step of calculating the ride quality of the aircraft comprises:

[0045]

[0046] wherein,

[0047] D i is the ride quality of the aircraft.

[0048] ω f is the calculation cutoff frequency of the ride quality of the aircraft.

[0049] is the calculation start frequency of the ride quality of the aircraft.

[0050] Optionally, in the method for evaluating the ride quality of the aircraft, the calculation start frequency of the ride quality of the aircraft is 0.1.

[0051] In another aspect, a system for evaluating the ride quality of an aircraft is provided, comprising:

[0052] a module for establishing a turbulence response function of the normal acceleration of the aircraft;

[0053] a module for establishing a spectrum function of the turbulence of the aircraft;

[0054] The aircraft normal load spectrum function establishing module is configured to establish the aircraft normal load spectrum function based on the aircraft normal load turbulence response function and the aircraft turbulence spectrum function.

[0055] The normal load frequency weight function establishing module is configured to establish the normal load frequency weight function.

[0056] The aircraft ride quality spectrum function establishing module is configured to establish the aircraft ride quality spectrum function based on the aircraft normal load spectrum function and the normal load frequency weight function.

[0057] The aircraft ride quality calculating module is configured to calculate the aircraft ride quality by frequency integration based on the aircraft ride quality spectrum function.

[0058] Optionally, in the aircraft ride quality evaluation system, the aircraft normal load turbulence response function establishing module is configured to establish the aircraft normal load turbulence response function, and the aircraft normal load turbulence response function is specifically as follows:

[0059]

[0060] wherein,

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

[0062] V * is the current flight speed;

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

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

[0065] Optionally, in the aircraft ride quality evaluation system, the aircraft turbulence spectrum function establishing module is configured to establish the aircraft turbulence spectrum function, and the aircraft turbulence spectrum function is specifically as follows:

[0066]

[0067] wherein,

[0068] is the aircraft turbulence spectrum function;

[0069] is the intensity of the 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 aircraft wingspan;

[0073] i is an imaginary symbol.

[0074] Optionally, in the aircraft ride quality evaluation system, the aircraft normal acceleration frequency spectrum function establishing module establishes the aircraft normal acceleration frequency spectrum function, specifically:

[0075]

[0076] wherein,

[0077] is the aircraft normal acceleration frequency spectrum function.

[0078] Optionally, in the aircraft ride quality evaluation system, the normal acceleration frequency weight function establishing module establishes the normal acceleration frequency weight function, specifically:

[0079]

[0080] wherein,

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

[0082] Optionally, in the aircraft ride quality evaluation system, the aircraft ride quality frequency spectrum function establishing module establishes the aircraft ride quality frequency spectrum function, specifically:

[0083]

[0084] wherein,

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

[0086] Optionally, in the aircraft ride quality evaluation system, the aircraft ride quality calculating module calculates the aircraft ride quality, specifically:

[0087]

[0088] wherein,

[0089] D i is the aircraft ride quality;

[0090] ω f is the aircraft ride quality calculating cutoff frequency;

[0091] is the ride quality calculating start frequency.

[0092] Optionally, in the aircraft ride quality evaluation system, the ride quality calculating start frequency is 0.1.

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

[0094] processor;

[0095] The memory stores a computer program configured to implement any of the above-described aircraft passenger quality assessment methods when executed by the processor.

[0096] Another aspect provides an electronic medium that is a computer-readable storage medium storing a computer program that, when executed by a processor, can implement any of the above-described methods for assessing aircraft passenger quality.

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

[0098] This invention provides a method, system, electronic product, and medium for assessing aircraft passenger comfort. Based on the aircraft turbulent response equation, it establishes the aircraft turbulent transfer coefficient equation, the aircraft turbulent transfer function, and thus the aircraft normal overload turbulent response function and the aircraft turbulent spectrum function. Furthermore, using the aircraft normal overload turbulent response function and the aircraft turbulent spectrum function, it establishes the aircraft normal overload spectrum function, followed by the establishment of a normal overload frequency weighting function. Subsequently, using the aircraft normal overload spectrum function and the normal overload frequency weighting function, it establishes the aircraft passenger comfort spectrum function. The aircraft passenger comfort is calculated by integrating at commonly used frequencies, thus assessing the aircraft passenger comfort. This provides a more reliable means for assessing aircraft passenger comfort and can better serve aircraft design. Attached Figure Description

[0099] Figure 1 This is a schematic diagram of the aircraft passenger quality assessment method provided in the embodiments of this application;

[0100] Figure 2 This is a schematic diagram of the aircraft passenger quality assessment system provided in the embodiments of this application.

[0101] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0102] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0103] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words indicating the orientation used in the description of the present application are only used to indicate the relative direction or positional relationship, and when the absolute position of the described object changes, the relative positional relationship may also change accordingly. In the description of the present application, "including" indicates that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0104] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the "installation", "connection" and similar words used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection or detachable connection; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through intermediate medium, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0105] The present application provides an aircraft ride quality evaluation method, according to the sensitivity level of human body to different vibration frequencies, the acceleration function of different frequencies is given, then the ride quality considering vibration sensitivity is calculated, more accurate aircraft ride quality calculation result can be obtained, such as Figure 1 .

[0106] The step of establishing the aircraft normal overload turbulence response function is: establishing the aircraft normal overload turbulence response function.

[0107]

[0108] Wherein,

[0109] The aircraft normal overload turbulence response function is:

[0110] V * The current flight speed is:

[0111] The aircraft trim lift coefficient is: The derivative of the aircraft lift coefficient with respect to the angle of attack is:

[0112] The aircraft speed and angle of attack turbulence transfer function can be determined by the following steps:

[0113] S1, establish the aircraft turbulence response equation.

[0114]

[0115] Wherein,

[0116] s is Laplace operator; g is gravity acceleration;

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

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

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

[0120] V * is the trim point speed;

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

[0122] The atmospheric turbulent change can be represented as .

[0123] S2, according to the aircraft turbulent response equation, the aircraft speed and angle of attack turbulent response function is established.

[0124]

[0125]

[0126] wherein,

[0127] det, is an intermediate calculation coefficient.

[0128] The normal overload of the aircraft is calculated as:

[0129] The aircraft turbulent spectrum function establishment step is to establish the aircraft turbulent spectrum function.

[0130]

[0131] wherein,

[0132] is the aircraft turbulent spectrum function;

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

[0134] L is the aircraft wingspan;

[0135] ω is the turbulence frequency;

[0136] L is the aircraft wingspan;

[0137] i is the imaginary unit;

[0138] The aircraft normal acceleration frequency spectrum function establishment step: establishing the aircraft normal acceleration frequency spectrum function with the aircraft normal acceleration turbulence response function and the aircraft turbulence frequency spectrum function.

[0139]

[0140] wherein,

[0141] is the aircraft normal acceleration frequency spectrum function.

[0142] The normal acceleration frequency weight function establishment step: establishing the normal acceleration frequency weight function.

[0143]

[0144] wherein,

[0145] W(ω) is the normal acceleration frequency weight function, considering the sensitivity of human body to vibration frequency for design.

[0146] The aircraft ride quality frequency spectrum function establishment step: establishing the aircraft ride quality frequency spectrum function with the aircraft normal acceleration frequency spectrum function and the normal acceleration frequency weight function.

[0147]

[0148] wherein,

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

[0150] The aircraft ride quality calculation step: calculating the aircraft ride quality by frequency integration according to the aircraft ride quality frequency spectrum function.

[0151]

[0152] wherein,

[0153] D i is the aircraft ride quality;

[0154] ω f is the aircraft ride quality calculation cutoff frequency, higher than the frequency, the turbulence response is not obvious, and it can also be obtained through testing or simulation;

[0155] The initial frequency is calculated for the ride quality, and specifically can be taken as 0.1.

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

[0157] In different speed states, the aircraft aerodynamic derivatives are calculated as shown in the following table:

[0158]

[0159] The strengths and scales of different turbulence are shown in the following table:

[0160]

[0161] The aircraft ride quality calculation results are shown in the following table:

[0162]

[0163] The aircraft ride quality evaluation method disclosed in the above embodiments is based on the aircraft turbulence response equation to establish the aircraft speed and angle of attack turbulence response function, thereby establishing the aircraft normal load turbulence response function, and establishing the aircraft turbulence frequency spectrum function. Further, the aircraft normal load frequency spectrum function is established based on the aircraft normal load turbulence response function and the aircraft turbulence frequency spectrum function. Then, the normal load frequency weight function is established. Thereafter, the aircraft ride quality frequency spectrum function is established based on the aircraft normal load frequency spectrum function and the normal load frequency weight function. The aircraft ride quality is calculated by integrating the commonly used frequency, and the aircraft ride quality is evaluated. This provides a more reliable means for aircraft ride quality evaluation, and can better serve aircraft design.

[0164] The aircraft ride quality evaluation method disclosed in the above embodiments has a rigorous theoretical basis. According to the normal load frequency spectrum function and the weight function of the normal load on the vibration frequency, the ride quality in the commonly used frequency range is obtained by integration, which can effectively improve the calculation accuracy of the aircraft ride quality.

[0165] In another aspect, an aircraft ride quality evaluation system is provided, as shown in Figure 2 The system includes:

[0166] The aircraft normal load turbulence response function establishing module is used to establish the aircraft normal load turbulence response function.

[0167] The aircraft turbulence frequency spectrum function establishing module is used to establish the aircraft turbulence frequency spectrum function.

[0168] The aircraft normal load frequency spectrum function establishing module is used to establish the aircraft normal load frequency spectrum function based on the aircraft normal load turbulence response function and the aircraft turbulence frequency spectrum function.

[0169] The normal overload frequency weight function establishing module is configured to establish a normal overload frequency weight function;

[0170] The aircraft ride quality spectrum function establishing module is configured to establish an aircraft ride quality spectrum function based on the aircraft normal overload spectrum function and the normal overload frequency weight function.

[0171] The aircraft ride quality calculating module is configured to calculate the aircraft ride quality by frequency integration based on the aircraft ride quality spectrum function.

[0172] Further, in the aircraft ride quality evaluation system, the aircraft normal overload turbulence response function establishing module is configured to establish an aircraft normal overload turbulence response function, and the aircraft normal overload turbulence response function is specifically as follows:

[0173]

[0174] wherein,

[0175] is the aircraft normal overload turbulence response function;

[0176] V * is the current flight speed;

[0177] is the aircraft trimmed lift coefficient, is the derivative of the aircraft lift coefficient with respect to the angle of attack;

[0178] is the aircraft speed and angle of attack turbulence transfer function.

[0179] Further, in the aircraft ride quality evaluation system, the aircraft turbulence spectrum function establishing module is configured to establish an aircraft turbulence spectrum function, and the aircraft turbulence spectrum function is specifically as follows:

[0180]

[0181] wherein,

[0182] is the aircraft turbulence spectrum function;

[0183] is the intensity of the turbulence in the x-axis and y-axis directions;

[0184] is the size of the turbulence in the x-axis and y-axis directions;

[0185] ω is the turbulence frequency;

[0186] l is the aircraft wingspan;

[0187] i is the imaginary symbol.

[0188] Further, in the aircraft ride quality evaluation system, the aircraft normal acceleration frequency spectrum function establishing module establishes the aircraft normal acceleration frequency spectrum function, specifically:

[0189]

[0190] wherein,

[0191] is the aircraft normal acceleration frequency spectrum function.

[0192] Further, in the aircraft ride quality evaluation system, the normal acceleration frequency weight function establishing module establishes the normal acceleration frequency weight function, specifically:

[0193]

[0194] wherein,

[0195] W(ω) is the normal acceleration frequency weight function.

[0196] Further, in the aircraft ride quality evaluation system, the aircraft ride quality frequency spectrum function establishing module establishes the aircraft ride quality frequency spectrum function, specifically:

[0197]

[0198] wherein,

[0199] Φ R (ω) is the aircraft ride quality frequency spectrum function.

[0200] Further, in the aircraft ride quality evaluation system, the aircraft ride quality calculating module calculates the aircraft ride quality, specifically:

[0201]

[0202] wherein,

[0203] D i is the aircraft ride quality;

[0204] ω f is the aircraft ride quality calculation cutoff frequency;

[0205] is the ride quality calculation starting frequency.

[0206] Further, in the aircraft ride quality evaluation system, the aircraft ride quality calculating module, the ride quality calculation starting frequency is 0.1.

[0207] For the aircraft ride quality evaluation system disclosed in the above embodiments, since it corresponds to the aircraft ride quality evaluation method disclosed in the above embodiments, the description is relatively simple, and the specific related parts can be referred to the related description of the aircraft ride quality evaluation method part. The technical effects can also be referred to the technical effects of the aircraft ride quality evaluation method related part, which will not be described here.

[0208] In addition, those skilled in the art should also be aware that each module of the aircraft ride quality evaluation system disclosed in the embodiments of the present application can be realized in the form of electronic hardware, computer software or a combination of both. In order to clearly illustrate the interchangeability of hardware and software, the embodiments in the present application are generally described in terms of functions. Whether the functions are executed in hardware or software form depends on the specific application and design constraints of the technical solution. Those skilled in the art can choose different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered beyond the scope of the present application.

[0209] In another aspect, an electronic device is provided, comprising:

[0210] a processor;

[0211] a memory storing a computer program configured to be executed by the processor to implement any of the above aircraft ride quality evaluation methods.

[0212] In some optional embodiments, the processor can be a central processing unit (CPU) or other forms of processing unit having data processing capability and / or instruction execution capability, which can be a general purpose processor or a dedicated processor, and can control other components in the compensation electronic device to perform desired functions.

[0213] In some optional embodiments, the memory can include various forms of computer readable storage media, such as volatile memory and / or non-volatile memory. The volatile memory can be random access memory (RAM) and / or cache memory. The non-volatile memory can be read-only memory (ROM), hard disk, flash memory, etc. The memory can store a computer program, which is executed by the processor to implement the functions in the embodiments of the present application and / or other desired functions. In addition, various application programs and various data can also be stored.

[0214] In some optional embodiments, the processor and the memory can be connected through a bus system, which can be a serial, parallel communication bus, etc.

[0215] It should be noted that, for the sake of clarity and conciseness, all the constituent units of the electronic device are not given in the above embodiments, and other constituent units not shown can be provided and set according to specific needs to achieve necessary functions of the electronic device.

[0216] For the electronic device disclosed in the above embodiments, since the processor can implement any of the above aircraft ride quality evaluation methods when executing the computer program stored on the memory, the technical effects can be correspondingly referred to the technical effects of the aircraft ride quality evaluation method part, which will not be repeated here.

[0217] In another aspect, an electronic medium is provided, which is a computer readable storage medium, and the computer readable storage medium stores a computer program, and the computer program can implement any of the above aircraft ride quality evaluation methods when executed by a processor.

[0218] In some optional embodiments, the computer readable storage medium can include a memory card of a smart phone, 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 disc read-only memory CD-ROM, a flash memory, or any combination of the above storage media, and can also be other applicable storage media.

[0219] So far, the technical solutions of the present application have been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A method for evaluating the quality of aircraft passenger experience, characterized in that, include: Steps for establishing the aircraft normal overload turbulent response function: Establish the aircraft normal overload turbulent response function; Steps for establishing the aircraft turbulence spectrum function: Establish the aircraft turbulence spectrum function; Steps for establishing the aircraft normal overload spectrum function: The aircraft normal overload turbulent response function and the aircraft turbulent spectrum function are used to establish the aircraft normal overload spectrum function; Steps for establishing the normal overload frequency weighting function: Establish the normal overload frequency weighting function; Steps for establishing the aircraft ride quality spectrum function: The aircraft ride quality spectrum function is established using the aircraft normal overload spectrum function and the normal overload frequency weighting function. Aircraft ride quality calculation steps: Calculate the aircraft ride quality by integrating the frequency using the aircraft ride quality spectrum function. In the steps of establishing the aircraft normal overload turbulent response function, the specific steps are as follows: in, The normal overload turbulent response function of the aircraft; V * Current flight speed; C y* For the aircraft trim lift coefficient, This is the derivative of the aircraft's lift coefficient with respect to the angle of attack; For the turbulent transfer function of aircraft speed and angle of attack; The steps for establishing the aircraft turbulence spectrum function are as follows: in, The turbulence spectrum function of the aircraft; The intensity of the turbulence in the x-axis and y-axis directions; These represent the dimensions of the turbulence in the x-axis and y-axis directions; ω is the turbulence frequency; l represents the aircraft's wingspan; i is the symbol for an imaginary number; In the steps of establishing the aircraft normal overload spectrum function, the establishment of the aircraft normal overload spectrum function is specifically as follows: in, The normal overload spectrum function of the aircraft; In the step of establishing the normal overload frequency weighting function, the normal overload frequency weighting function is established as follows: in, W(ω) is the normal overload frequency weighting function; The steps for establishing the aircraft ride quality spectrum function are as follows: in, Φ R (ω) is the spectrum function of aircraft ride quality.

2. The method for evaluating aircraft passenger comfort according to claim 1, characterized in that, The calculation of aircraft passenger comfort involves the following steps: in, D i For the quality of the flight experience; ω f Calculate the cutoff frequency for aircraft passenger comfort; The starting frequency is calculated for ride quality.

3. The method for evaluating aircraft passenger comfort according to claim 2, characterized in that, In the process of calculating the quality of flight comfort, the starting frequency for comfort calculation is... Take 0.

1.

4. An aircraft passenger comfort assessment system, characterized in that, include: The module for establishing the aircraft normal overload turbulent response function is used to establish the aircraft normal overload turbulent response function. The module for establishing the aircraft turbulence spectrum function is used to establish the aircraft turbulence spectrum function. The module for establishing the aircraft normal overload spectrum function uses the aircraft normal overload turbulent response function and the aircraft turbulent spectrum function to establish the aircraft normal overload spectrum function. The module for establishing the normal overload frequency weighting function is used to establish the normal overload frequency weighting function. Aircraft ride quality spectrum function establishment module: The aircraft ride quality spectrum function is established using the aircraft normal overload spectrum function and the normal overload frequency weighting function. Aircraft ride quality calculation module: Calculates aircraft ride quality by frequency integration using the aircraft ride quality spectrum function. In the module for establishing the aircraft normal overload turbulent response function, the aircraft normal overload turbulent response function is established as follows: in, The normal overload turbulent response function of the aircraft; V * Current flight speed; C y* For the aircraft trim lift coefficient, This is the derivative of the aircraft's lift coefficient with respect to the angle of attack; For the turbulent transfer function of aircraft speed and angle of attack; In the module for establishing the aircraft turbulence spectrum function, the aircraft turbulence spectrum function is established as follows: in, The turbulence spectrum function of the aircraft; The intensity of the turbulence in the x-axis and y-axis directions; These represent the dimensions of the turbulence in the x-axis and y-axis directions; ω is the turbulence frequency; l represents the aircraft's wingspan; i is the symbol for an imaginary number; In the module for establishing the aircraft normal overload spectrum function, the aircraft normal overload spectrum function is established as follows: in, The normal overload spectrum function of the aircraft; In the module for establishing the normal overload frequency weighting function, the normal overload frequency weighting function is established as follows: in, W(ω) is the normal overload frequency weighting function; In the module for establishing the aircraft ride quality spectrum function, the specific steps for establishing the aircraft ride quality spectrum function are as follows: in, Φ R (ω) is the spectrum function of aircraft ride quality.

5. The aircraft passenger comfort assessment system according to claim 4, characterized in that, The aircraft ride quality calculation module calculates aircraft ride quality as follows: in, D i For the quality of the flight experience; ω f Calculate the cutoff frequency for aircraft passenger comfort; The starting frequency is calculated for ride quality.

6. The aircraft passenger comfort assessment system according to claim 5, characterized in that, In the aircraft ride quality calculation module, the starting frequency for ride quality calculation is... Take 0.

1.

7. An electronic device, characterized in that, include: processor; The memory stores a computer program configured to implement the aircraft passenger quality assessment method of claim 1 when executed by the processor.

8. An electronic medium, characterized in that, The electronic medium is a computer-readable storage medium that stores a computer program that, when executed by a processor, can implement the aircraft ride quality assessment method of claim 1.

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