Flap lateral force derivative calculation method and device

Abstract

The invention belongs to the technical field of aircraft design, and relates to a flap lateral force derivative calculation method and device. The method comprises the following steps: S1, determining a first lateral force derivative component generated by the sweepback influencing the flap; s2, determining a second lateral force derivative component generated when the wing body assembly affects the flap; s3, a third lateral force derivative component generated when the vertical tail influences the flap is determined; and S4, superposing the first lateral force derivative component, the second lateral force derivative component and the third lateral force derivative component to obtain a flap lateral force derivative. The calculation model reflects the influence of flap configuration parameters, lift coefficient increment, viscous resistance coefficient increment, a vertical fin lateral force derivative, a wing aspect ratio, a tip-root ratio, a wing mounting position, a horizontal tail mounting position and width and height changes of a fuselage cross section on the lateral force, and the lateral force derivative of the flap can be accurately calculated.

Description

Technical Field

[0001] This application belongs to the field of aircraft design technology, and specifically relates to a method and device for calculating the derivative of flap lateral force. Background Technology

[0002] Flap deflection not only increases the aircraft's lift and drag coefficients but also increases its lateral forces. The increase in the lateral force derivative is related not only to the flap configuration but also to parameters such as the wing aspect ratio, tip-root ratio, wing mounting position, horizontal tail mounting position, vertical tail configuration, and the lateral force derivative generated by the vertical tail. Due to the large number of parameters involved, the calculation model for the flap lateral force derivative is quite complex. Therefore, accurately constructing such a model to guide flap structure optimization is a crucial technical problem that needs to be solved. Summary of the Invention

[0003] To address the aforementioned issues, this application provides a method and apparatus for calculating the derivative of flap lateral force, offering technical support for the calculation and evaluation of flap lateral force derivative.

[0004] The first aspect of this application provides a method for calculating the derivative of the lateral force of a flap, mainly including:

[0005] Step S1: Determine the derivative component of the first lateral force generated by the flaps due to the sweep angle;

[0006] Step S2: Determine the derivative component of the second lateral force generated by the flaps due to the influence of the wing-body combination;

[0007] Step S3: Determine the derivative component of the third lateral force generated by the vertical tail fin affecting the flaps;

[0008] Step S4: Superimpose the first lateral force derivative component, the second lateral force derivative component, and the third lateral force derivative component to obtain the flap lateral force derivative.

[0009] Preferably, in step S1, the derivative component of the first lateral force is calculated using the following formula. :

[0010] ;

[0011] in, The viscous drag coefficient of the inner flap. is the viscous drag coefficient of the outer flap.

[0012] Preferably, the viscous drag coefficient of the inner flap is calculated using the following formula. :

[0013] ;

[0014] in, G represents the viscous drag coefficient of all flaps, and G is the ratio of the viscous drag coefficients of the inner and outer flaps.

[0015] Preferably, the viscous drag coefficient of the outer flap is calculated using the following formula. :

[0016] .

[0017] Preferably, the ratio G of the viscous drag coefficients of the inner and outer flaps is calculated using the following formula:

[0018] ;

[0019] in, The inner chord length of the inner flap. The outer chord length of the inner flap. The inner wing chord length of the outer flap. The outer wing chord length of the outer flap. The position of the inner flap along the span of the inner wing. The outer wing spanwise position of the inner flap. This refers to the spanwise position of the inner side of the outer flap. This refers to the spanwise position of the outer flap.

[0020] Preferably, in step S2, the derivative component of the second lateral force is calculated using the following formula. :

[0021] ;

[0022] in, This represents the increase in the lift coefficient generated by the flaps;

[0023] ;

[0024] ;

[0025] Where A is the wing aspect ratio, z is the height of the point where the wing root chord is 1 / 4 of its length from the fuselage centerline, and h is the height of the fuselage cross-section at the wing-fuselage junction. For wingspan, parameters The parameters are obtained by interpolation calculation based on parameters bd and zx in a given first interpolation table. Based on the wing aspect ratio A and the wing tip root ratio Interpolation calculations are performed using the given second interpolation table to obtain:

[0026] ;

[0027] ;

[0028] Where d is the width of the fuselage cross-section.

[0029] Preferably, in step S3, the derivative component of the third lateral force is calculated using the following formula. :

[0030] ;

[0031] in, For the lateral force derivative of the vertical tail fin, Parameters for mounting the horizontal stabilizer on the fuselage;

[0032] ;

[0033] ;

[0034] in, The installation height of the horizontal tail fin. The height of the vertical tail.

[0035] The second aspect of this application provides a device for calculating the derivative of the lateral force of a flap, mainly comprising:

[0036] The first lateral force derivative component determination module is used to determine the first lateral force derivative component generated by the sweep angle affecting the flap;

[0037] The second lateral force derivative component determination module is used to determine the second lateral force derivative component generated by the wing-body combination affecting the flaps;

[0038] The third lateral force derivative component determination module is used to determine the third lateral force derivative component generated by the vertical tail affecting the flaps;

[0039] The flap lateral force derivative determination module is used to superimpose the first lateral force derivative component, the second lateral force derivative component, and the third lateral force derivative component to obtain the flap lateral force derivative.

[0040] Preferably, in the first lateral force derivative component determination module, the first lateral force derivative component is calculated using the following formula. :

[0041] ;

[0042] in, The viscous drag coefficient of the inner flap. is the viscous drag coefficient of the outer flap.

[0043] Preferably, the viscous drag coefficient of the inner flap is calculated using the following formula. :

[0044] ;

[0045] in, G represents the viscous drag coefficient of all flaps, and G is the ratio of the viscous drag coefficients of the inner and outer flaps.

[0046] Preferably, the viscous drag coefficient of the outer flap is calculated using the following formula. :

[0047] .

[0048] Preferably, the ratio G of the viscous drag coefficients of the inner and outer flaps is calculated using the following formula:

[0049] ;

[0050] in, The inner chord length of the inner flap. The outer chord length of the inner flap. The inner wing chord length of the outer flap. The outer wing chord length of the outer flap. The position of the inner flap along the span of the inner wing. The outer wing spanwise position of the inner flap. This refers to the spanwise position of the inner side of the outer flap. This refers to the spanwise position of the outer flap.

[0051] Preferably, in the second lateral force derivative component determination module, the second lateral force derivative component is calculated using the following formula. :

[0052] ;

[0053] in, This represents the increase in the lift coefficient generated by the flaps;

[0054] ;

[0055] ;

[0056] Where A is the wing aspect ratio, z is the height of the point where the wing root chord is 1 / 4 of its length from the fuselage centerline, and h is the height of the fuselage cross-section at the wing-fuselage junction. For wingspan, parameters The parameters are obtained by interpolation calculation based on parameters bd and zx in a given first interpolation table. Based on the wing aspect ratio A and the wing tip root ratio Interpolation calculations are performed using the given second interpolation table to obtain:

[0057] ;

[0058] ;

[0059] Where d is the width of the fuselage cross-section.

[0060] Preferably, in the third lateral force derivative component determination module, the third lateral force derivative component is calculated using the following formula. :

[0061] ;

[0062] in, For the lateral force derivative of the vertical tail fin, Parameters for mounting the horizontal stabilizer on the fuselage;

[0063] ;

[0064] ;

[0065] in, The installation height of the horizontal tail fin. The height of the vertical tail.

[0066] A third aspect of this application provides a computer device including a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the flap lateral force derivative calculation method as described above.

[0067] A fourth aspect of this application provides a readable storage medium storing a computer program that, when executed by a processor, is used to implement the method for calculating the derivative of the flap lateral force as described above.

[0068] The calculation model in this application reflects the influence of flap configuration parameters, lift coefficient increment, viscous drag coefficient increment, vertical tail lateral force derivative, wing aspect ratio, tip-root ratio, wing mounting position, horizontal tail mounting position, and changes in the width and height of the fuselage cross section on the lateral force, and can accurately calculate the lateral force derivative of the flap. Attached Figure Description

[0069] Figure 1 This is a flowchart of a preferred embodiment of the method for calculating the derivative of the flap lateral force in this application.

[0070] Figure 2 This is a schematic diagram defining the structural parameters of the aircraft in this application.

[0071] Figure 3 This application Figure 2 A schematic diagram of the tail fin structure parameters in the embodiment shown.

[0072] Figure 4 This application Figure 2 Rear view of the aircraft in the illustrated embodiment.

[0073] Figure 5 This is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of this application. Detailed Implementation

[0074] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0075] The first aspect of this application provides a method for calculating the derivative of the lateral force of a flap, such as... Figure 1 As shown, it mainly includes:

[0076] Step S1: Determine the derivative component of the first lateral force generated by the flaps due to the sweep angle;

[0077] Step S2: Determine the derivative component of the second lateral force generated by the flaps due to the influence of the wing-body combination;

[0078] Step S3: Determine the derivative component of the third lateral force generated by the vertical tail fin affecting the flaps;

[0079] Step S4: Superimpose the first lateral force derivative component, the second lateral force derivative component, and the third lateral force derivative component to obtain the flap lateral force derivative.

[0080] This application first theoretically analyzes the sensitive factors of the lateral force derivative of the flap, and then constructs a calculation model for the lateral force derivative of the flap based on theoretical analysis and experimental data.

[0081] In step S4, the calculation model for the lateral force derivative of the flap is as follows:

[0082] ;

[0083] Derivative of lateral force generated by flaps It consists of three parts: the derivative component of the lateral force generated by the flap due to the sweep angle calculated in step S1. Step S2 calculates the derivative components of the lateral force generated by the flaps due to the influence of the wing-body combination. The derivative components of the lateral force generated by the vertical tail fin affecting the flaps, calculated in step S3. .

[0084] Step S1 is used to calculate the derivative components of the first lateral force. .

[0085] In some alternative implementations, in step S1, the derivative component of the first lateral force is calculated using the following formula. :

[0086] ;

[0087] in, The viscous drag coefficient of the inner flap. is the viscous drag coefficient of the outer flap.

[0088] In some alternative implementations, the viscous drag coefficient of the inner flap is calculated using the following formula. :

[0089] ;

[0090] in, G represents the viscous drag coefficient of all flaps, and G is the ratio of the viscous drag coefficients of the inner and outer flaps.

[0091] In some alternative implementations, the viscous drag coefficient of the outer flap is calculated using the following formula. :

[0092] .

[0093] In some alternative implementations, the ratio G of the viscous drag coefficients of the inner and outer flaps is calculated using the following formula:

[0094] ;

[0095] Among them, such as Figure 2 As shown, The inner chord length of the inner flap. The outer chord length of the inner flap. The inner wing chord length of the outer flap. The outer wing chord length of the outer flap. The position of the inner flap along the span of the inner wing. The outer wing spanwise position of the inner flap. This refers to the spanwise position of the inner side of the outer flap. This refers to the spanwise position of the outer flap.

[0096] Step S2 is used to calculate the derivative components of the second lateral force.

[0097] In some alternative implementations, in step S2, the derivative component of the second lateral force is calculated using the following formula. :

[0098] ;

[0099] in, This represents the increase in the lift coefficient generated by the flaps;

[0100] ;

[0101] ;

[0102] Among them, such as Figure 4 As shown, A is the wing aspect ratio, z is the height of the point where the wing root chord is 1 / 4 of its length from the fuselage centerline, and h is the height of the fuselage cross-section at the wing-fuselage junction. For wingspan, parameters The parameters are calculated by interpolation using parameters bd and zx in the first interpolation table shown in Table 1. Based on the wing aspect ratio A and the wing tip root ratio Interpolation calculations are performed using the second interpolation table shown in Table 2.

[0103] ;

[0104] ;

[0105] Where d is the width of the fuselage cross-section.

[0106] Table 1 Data required for interpolation calculation

[0107]

[0108] Table 2 Data required for interpolation calculation

[0109]

[0110] Step S3 is used to calculate the derivative component of the third lateral force.

[0111] In some alternative implementations, in step S3, the derivative component of the third lateral force is calculated using the following formula. :

[0112] ;

[0113] in, For the lateral force derivative of the vertical tail fin, Parameters for mounting the horizontal stabilizer on the fuselage;

[0114] ;

[0115] ;

[0116] Among them, such as Figure 3 As shown, The installation height of the horizontal tail fin. This refers to the height of the vertical stabilizer. Typically, the horizontal stabilizer is mounted on the fuselage. It is 0.035.

[0117] The example aircraft has a wingspan of 44m, an aspect ratio of 7.9, a tip-to-root ratio of 0.2, and a wing installation height of 1.4m. The width and height of the fuselage cross-section at the wing-fuselage junction are both 6m. The spanwise positions of the inner and outer chords of the inner flaps are 3.08m and 7.19m, respectively, with a flap hinge line sweep angle of 6° and a root chord leading edge distance of 4.1m from the center of gravity. The spanwise positions of the inner and outer chords of the outer flaps are 8.22m and 15.07m, respectively, with a flap hinge line sweep angle of 14° and a root chord leading edge distance of 2.7m from the center of gravity. The vertical tail height is 6.2m, and the horizontal tail installation height is 3.8m.

[0118] Calculation conditions: Flight speed Mach 0.2, lift coefficient increment from flaps 0.846, viscous drag coefficient of the inner flap 0.016, viscous drag coefficient of the outer flap 0.015. Lateral force derivative of the vertical tail -0.531 / rad. The flow chart of the lateral force derivative from flaps is as follows:

[0119] (1) Calculate the derivative components of the lateral force affected by the sweep angle. It is -0.031 / rad;

[0120] (2) Calculate the derivative of the lateral force due to the influence of the wing-body combination. It is -0.038 / rad;

[0121] (3) Calculate the derivative components of the lateral force due to the influence of the vertical tail. It is -0.04 / rad;

[0122] (4) Final calculation of the derivative of the flap lateral force It is -0.109 / rad.

[0123] A second aspect of this application provides a flap lateral force derivative calculation device corresponding to the above method, mainly comprising:

[0124] The first lateral force derivative component determination module is used to determine the first lateral force derivative component generated by the sweep angle affecting the flap;

[0125] The second lateral force derivative component determination module is used to determine the second lateral force derivative component generated by the wing-body combination affecting the flaps;

[0126] The third lateral force derivative component determination module is used to determine the third lateral force derivative component generated by the vertical tail affecting the flaps;

[0127] The flap lateral force derivative determination module is used to superimpose the first lateral force derivative component, the second lateral force derivative component, and the third lateral force derivative component to obtain the flap lateral force derivative.

[0128] In some optional embodiments, in the first lateral force derivative component determination module, the first lateral force derivative component is calculated using the following formula. :

[0129] ;

[0130] in, The viscous drag coefficient of the inner flap. is the viscous drag coefficient of the outer flap.

[0131] In some alternative implementations, the viscous drag coefficient of the inner flap is calculated using the following formula. :

[0132] ;

[0133] in, G represents the viscous drag coefficient of all flaps, and G is the ratio of the viscous drag coefficients of the inner and outer flaps.

[0134] In some alternative implementations, the viscous drag coefficient of the outer flap is calculated using the following formula. :

[0135] .

[0136] In some alternative implementations, the ratio G of the viscous drag coefficients of the inner and outer flaps is calculated using the following formula:

[0137] ;

[0138] in, The inner chord length of the inner flap. The outer chord length of the inner flap. The inner wing chord length of the outer flap. The outer wing chord length of the outer flap. The position of the inner flap along the span of the inner wing. The outer wing spanwise position of the inner flap. This refers to the spanwise position of the inner side of the outer flap. This refers to the spanwise position of the outer flap.

[0139] In some optional embodiments, in the second lateral force derivative component determination module, the second lateral force derivative component is calculated using the following formula. :

[0140] ;

[0141] in, This represents the increase in the lift coefficient generated by the flaps;

[0142] ;

[0143] ;

[0144] Where A is the wing aspect ratio, z is the height of the point where the wing root chord is 1 / 4 of its length from the fuselage centerline, and h is the height of the fuselage cross-section at the wing-fuselage junction. For wingspan, parameters The parameters are obtained by interpolation calculation based on parameters bd and zx in a given first interpolation table. Based on the wing aspect ratio A and the wing tip root ratio Interpolation calculations are performed using the given second interpolation table to obtain:

[0145] ;

[0146] ;

[0147] Where d is the width of the fuselage cross-section.

[0148] In some optional embodiments, the third lateral force derivative component determination module calculates the third lateral force derivative component using the following formula. :

[0149] ;

[0150] in, For the lateral force derivative of the vertical tail fin, Parameters for mounting the horizontal stabilizer on the fuselage;

[0151] ;

[0152] ;

[0153] in, The installation height of the horizontal tail fin. The height of the vertical tail.

[0154] In a third aspect of this application, a computer device is provided, comprising a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for calculating the derivative of the flap lateral force as described above.

[0155] In a fourth aspect, this application provides a readable storage medium storing a computer program that, when executed by a processor, implements the flap lateral force derivative calculation method described above. This computer-readable storage medium may be included in the apparatus described in the above embodiments; or it may exist independently and not incorporated into the apparatus. The aforementioned computer-readable storage medium carries one or more programs that, when executed by the apparatus, process data according to the method described above.

[0156] The following is for reference. Figure 5 It shows a schematic diagram of the structure of a computer device 400 suitable for implementing the embodiments of this application. Figure 5 The computer device shown is merely an example and should not be construed as limiting the functionality and scope of the embodiments described in this application.

[0157] like Figure 5 As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage section 408 into a random access memory (RAM) 403. The RAM 403 also stores various programs and data required for the operation of the device 400. The CPU 401, ROM 402, and RAM 403 are interconnected via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0158] The following components are connected to I / O interface 405: an input section 406 including a keyboard, mouse, etc.; an output section 407 including a cathode ray tube (CRT), liquid crystal display (LCD), etc., and speakers, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to I / O interface 405 as needed. A removable medium 411, such as a disk, optical disk, magneto-optical disk, semiconductor memory, etc., is installed on drive 410 as needed so that computer programs read from it can be installed into storage section 408 as needed.

[0159] Specifically, according to embodiments of this application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication section 409, and / or installed from removable medium 411. When the computer program is executed by central processing unit (CPU) 401, it performs the functions defined in the methods of this application. It should be noted that the computer storage medium of this application can be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium can be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of computer-readable storage media may include, but are not limited to: electrical connections having one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In this application, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in connection with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can also be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on a computer-readable medium can be transmitted using any suitable medium, including but not limited to: wireless, wire, optical fiber, RF, etc., or any suitable combination thereof.

[0160] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0161] The modules or units described in the embodiments of this application can be implemented in software or hardware. The described modules or units can also be located in a processor, and the names of these modules or units do not necessarily constitute a limitation on the module or unit itself.

[0162] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for calculating the derivative of the lateral force of a flap, characterized in that, include: Step S1: Determine the derivative component of the first lateral force generated by the flaps due to the sweep angle; Step S2: Determine the derivative component of the second lateral force generated by the flaps due to the influence of the wing-body combination; Step S3: Determine the derivative component of the third lateral force generated by the vertical tail fin affecting the flaps; Step S4: Superimpose the first lateral force derivative component, the second lateral force derivative component, and the third lateral force derivative component to obtain the flap lateral force derivative.

2. The method for calculating the derivative of the flap lateral force as described in claim 1, characterized in that, In step S1, the derivative components of the first lateral force are calculated using the following formula. : ； in, The viscous drag coefficient of the inner flap. is the viscous drag coefficient of the outer flap.

3. The method for calculating the derivative of the flap lateral force as described in claim 2, characterized in that, The viscous drag coefficient of the inner flap is calculated using the following formula. : ； in, G represents the viscous drag coefficient of all flaps, and G is the ratio of the viscous drag coefficients of the inner and outer flaps.

4. The method for calculating the derivative of the flap lateral force as described in claim 3, characterized in that, The viscous drag coefficient of the outer flap is calculated using the following formula. : 。 5. The method for calculating the derivative of the flap lateral force as described in claim 4, characterized in that, The ratio G of the viscous drag coefficients of the inner and outer flaps is calculated using the following formula: ； in, The inner chord length of the inner flap. The outer chord length of the inner flap. The inner wing chord length of the outer flap. The outer flap is the chord length of the outer wing. This refers to the spanwise position of the inner flap. The outer wing spanwise position of the inner flap. This refers to the spanwise position of the inner wing of the outer flap. This refers to the spanwise position of the outer flap.

6. The method for calculating the derivative of the flap lateral force as described in claim 1, characterized in that, In step S2, the derivative components of the second lateral force are calculated using the following formula. : ； in, This represents the increase in the lift coefficient generated by the flaps; ； ； Where A is the wing aspect ratio, z is the height of the point where the wing root chord is 1 / 4 of its length from the fuselage centerline, and h is the height of the fuselage cross-section at the wing-fuselage junction. For wingspan, parameters The parameters are obtained by interpolation calculation based on parameters bd and zx in a given first interpolation table. Based on the wing aspect ratio A and the wing tip root ratio Interpolation calculations are performed using the given second interpolation table to obtain: ； ； Where d is the width of the fuselage cross-section.

7. The method for calculating the derivative of the flap lateral force as described in claim 1, characterized in that, In step S3, the derivative component of the third lateral force is calculated using the following formula. : ； in, For the lateral force derivative of the vertical tail fin, Parameters for mounting the horizontal stabilizer on the fuselage; ； ； in, The installation height of the horizontal tail fin. The height of the vertical tail.

8. A device for calculating the derivative of the lateral force of a flap, characterized in that, include: The first lateral force derivative component determination module is used to determine the first lateral force derivative component generated by the sweep angle affecting the flap; The second lateral force derivative component determination module is used to determine the second lateral force derivative component generated by the wing-body combination affecting the flaps; The third lateral force derivative component determination module is used to determine the third lateral force derivative component generated by the vertical tail affecting the flaps; The flap lateral force derivative determination module is used to superimpose the first lateral force derivative component, the second lateral force derivative component, and the third lateral force derivative component to obtain the flap lateral force derivative.

9. The flap lateral force derivative calculation device as described in claim 8, characterized in that, In the first lateral force derivative component determination module, the first lateral force derivative component is calculated using the following formula. : ； in, The viscous drag coefficient of the inner flap. is the viscous drag coefficient of the outer flap.

10. The flap lateral force derivative calculation device as described in claim 9, characterized in that, The viscous drag coefficient of the inner flap is calculated using the following formula. : ； in, G represents the viscous drag coefficient of all flaps, and G is the ratio of the viscous drag coefficients of the inner and outer flaps.

11. The flap lateral force derivative calculation device as described in claim 10, characterized in that, The viscous drag coefficient of the outer flap is calculated using the following formula. : 。 12. The flap lateral force derivative calculation device as described in claim 11, characterized in that, The ratio G of the viscous drag coefficients of the inner and outer flaps is calculated using the following formula: ； in, The inner chord length of the inner flap. The outer chord length of the inner flap. The inner wing chord length of the outer flap. The outer flap is the chord length of the outer wing. This refers to the spanwise position of the inner flap. The outer wing spanwise position of the inner flap. This refers to the spanwise position of the inner wing of the outer flap. This refers to the spanwise position of the outer flap.

13. The flap lateral force derivative calculation device as described in claim 8, characterized in that, In the second lateral force derivative component determination module, the second lateral force derivative component is calculated using the following formula. : ； in, This represents the increase in the lift coefficient generated by the flaps; ； ； Where A is the wing aspect ratio, z is the height of the point where the wing root chord is 1 / 4 of its length from the fuselage centerline, and h is the height of the fuselage cross-section at the wing-fuselage junction. For wingspan, parameters The parameters are obtained by interpolation calculation based on parameters bd and zx in a given first interpolation table. Based on the wing aspect ratio A and the wing tip root ratio Interpolation calculations are performed using the given second interpolation table to obtain: ； ； Where d is the width of the fuselage cross-section.

14. The flap lateral force derivative calculation device as described in claim 8, characterized in that, In the module for determining the third lateral force derivative component, the third lateral force derivative component is calculated using the following formula. : ； in, For the lateral force derivative of the vertical tail fin, Parameters for mounting the horizontal stabilizer on the fuselage; ； ； in, The installation height of the horizontal tail fin. The height of the vertical tail.

15. A computer device, characterized in that, It includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the flap lateral force derivative calculation method as described in any one of claims 1-7.

16. A readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it is used to implement the method for calculating the derivative of the flap lateral force as described in any one of claims 1-7.

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