Transverse static stability derivative calculation method and device for take-off and landing configuration wing

Abstract

The invention belongs to the technical field of aircraft design, and relates to a transverse static stability derivative calculation method and device for a take-off and landing configuration wing. The method comprises the following steps: S1, determining a transverse static stability derivative generated by a wing plane parameter; s2, determining a transverse static stability derivative generated by the dihedral angle of the wing; s3, determining a transverse static stability derivative increment generated by the flap; s4, the sum of the transverse static stability derivative generated by the wing plane parameters, the transverse static stability derivative generated by the wing dihedral angle and the transverse static stability derivative increment generated by the wing flap serves as the wing transverse static stability derivative of the wing flap release configuration. The calculation model reflects the influence of airfoil lift characteristics, a wing dihedral angle, a wing aspect ratio, a tip-root ratio, a wing sweepback angle, a flap elongation, a flap lift coefficient increment and a wing pressure center position change on the transverse static stability, and the transverse static stability derivative of the take-off and landing configuration wing 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 apparatus for calculating the lateral static stability derivative of a take-off and landing configuration wing. Background Technology

[0002] The lateral static stability of the takeoff and landing configuration is significantly improved compared to the cruise configuration. The increase in the lateral static stability derivative mainly comes from the flaps, with the flaps contributing approximately 60% of the increase in the lateral static stability derivative compared to the cruise configuration. The lateral static stability of the flap-extended configuration wing is related not only to the wing aspect ratio, tip-root ratio, sweep angle, dihedral angle, and lift coefficient, but also to the flap span, the increase in lift coefficient generated by the flaps, and the spanwise change in the aerodynamic pressure center caused by flap extension. Due to the numerous factors affecting the lateral static stability of the takeoff and landing configuration, its calculation model is also quite complex. Therefore, accurately constructing a calculation model for the lateral static stability derivative of the takeoff and landing configuration to guide wing 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 lateral static stability derivative of a takeoff and landing configuration wing, which can provide technical support for the calculation and evaluation of the lateral static stability of aircraft takeoff and landing configurations.

[0004] The first aspect of this application provides a method for calculating the lateral static stability derivative of a takeoff and landing configuration wing, mainly including:

[0005] Step S1: Determine the lateral static stability derivative generated by the wing planar parameters;

[0006] Step S2: Determine the lateral static stability derivative generated by the dihedral angle on the wing;

[0007] Step S3: Determine the increment of the lateral static stability derivative generated by the flap;

[0008] Step S4: The sum of the lateral static stability derivatives generated by the wing plane parameters, the lateral static stability derivatives generated by the wing dihedral angle, and the lateral static stability derivatives generated by the flaps is taken as the lateral static stability derivative of the flap-out configuration wing.

[0009] Preferably, in step S1, the lateral static stability derivative generated by the wing plane parameters is calculated using the following formula:

[0010] ;

[0011] in, The lift coefficient, Let be the lateral static stability derivative of the incompressible flow of the wing. This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0012] Preferably, the parameters are calculated using the following formula. :

[0013] ;

[0014] in, ;

[0015] ;

[0016] For the wing root ratio, The aspect ratio is the wing section ratio.

[0017] Preferably, the parameters are calculated using the following formula. :

[0018] ;

[0019] in, ;

[0020] ;

[0021] ;

[0022] in, This indicates the location of the wing's aerodynamic pressure center. It is the sweep angle of the wing's half chord.

[0023] Preferably, in step S2, the lateral static stability derivative generated by the dihedral angle of the wing is calculated using the following formula. :

[0024] ;

[0025] in, The dihedral angle of the wing. For wing parameters;

[0026] ;

[0027] ;

[0028] in, The lift line slope of the Mach number M airfoil;

[0029] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0030] ;

[0031] Second correction parameter Calculated using the following formula:

[0032] ;

[0033] in, It is the sweep angle of the wing's quarter chord.

[0034] Preferably, in step S3, the lateral static stability derivative increment generated by the flap is calculated using the following formula. :

[0035] ;

[0036] in, The increase in lift coefficient caused by flap deployment. The factor influencing the fuselage's effect on the wing sweepback is... The spanwise position of the wing pressure center in the flap deployment configuration. The sweep angle of the wing's half chord is the parameter. In the given two-dimensional interpolation table, based on the given third correction parameter and wing root ratio The third correction parameter is obtained through interpolation. For wing aspect ratio The reciprocal of.

[0037] Preferably, the spanwise position In the given two-dimensional interpolation table, based on the given fourth correction parameter and wing root ratio The fourth correction parameter is obtained through interpolation. Calculated using the following formula:

[0038] ;

[0039] in, This refers to the spanwise position of the outer side of the trailing edge flap on the wing. This refers to the wingspan of the aircraft wing.

[0040] Preferably, the influence factor of the fuselage on the wing sweep effect is... In the given two-dimensional interpolation table, based on the given fifth correction parameter and wing aspect ratio Obtained by interpolation, where the fifth correction parameter Calculated using the following formula:

[0041] ;

[0042] in, It is the axial distance between the nose and the point where the wing tip chord is half the length of the fuselage.

[0043] The second aspect of this application provides a device for calculating the lateral static stability derivative of a takeoff and landing configuration wing, mainly comprising:

[0044] The module for determining the lateral static stability derivative generated by the wing plane parameters is used to determine the lateral static stability derivative generated by the wing plane parameters.

[0045] The module for determining the lateral static stability derivative generated by the dihedral angle of the wing is used to determine the lateral static stability derivative generated by the dihedral angle of the wing.

[0046] The lateral static stability derivative increment determination module is used to determine the lateral static stability derivative increment generated by the flap;

[0047] The module for determining the lateral static stability derivative of flap-extended configuration wings is used to take the sum of the lateral static stability derivatives generated by the wing plane parameters, the lateral static stability derivatives generated by the wing dihedral angle, and the lateral static stability derivative increments generated by the flaps as the lateral static stability derivatives of flap-extended configuration wings.

[0048] Preferably, in the module for determining the lateral static stability derivative generated by the wing plane parameters, the lateral static stability derivative generated by the wing plane parameters is calculated using the following formula:

[0049] ;

[0050] in, The lift coefficient, Let be the lateral static stability derivative of the incompressible flow of the wing. This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0051] Preferably, the parameters are calculated using the following formula. :

[0052] ;

[0053] in, ;

[0054] ;

[0055] For the wing root ratio, The aspect ratio is the wing section ratio.

[0056] Preferably, the parameters are calculated using the following formula. :

[0057] ;

[0058] in, ;

[0059] ;

[0060] ;

[0061] in, This indicates the location of the wing's aerodynamic pressure center. It is the sweep angle of the wing's half chord.

[0062] Preferably, in the module for determining the lateral static stability derivative generated by the dihedral angle on the wing, the lateral static stability derivative generated by the dihedral angle on the wing is calculated using the following formula. :

[0063] ;

[0064] in, The dihedral angle of the wing. For wing parameters;

[0065] ;

[0066] ;

[0067] in, The lift line slope of the Mach number M airfoil;

[0068] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0069] ;

[0070] Second correction parameter Calculated using the following formula:

[0071] ;

[0072] in, It is the sweep angle of the wing's quarter chord.

[0073] Preferably, in the lateral static stability derivative increment determination module, the lateral static stability derivative increment generated by the flap is calculated using the following formula. :

[0074] ;

[0075] in, The increase in lift coefficient caused by flap deployment. The factor influencing the fuselage's effect on the wing sweepback is... The spanwise position of the wing pressure center in the flap deployment configuration. The sweep angle of the wing's half chord is the parameter. In the given two-dimensional interpolation table, based on the given third correction parameter and wing root ratio The third correction parameter is obtained through interpolation. For wing aspect ratio The reciprocal of.

[0076] Preferably, the spanwise position In the given two-dimensional interpolation table, based on the given fourth correction parameter and wing root ratio The fourth correction parameter is obtained through interpolation. Calculated using the following formula:

[0077] ;

[0078] in, This refers to the spanwise position of the outer side of the trailing edge flap on the wing. This refers to the wingspan of the aircraft wing.

[0079] Preferably, the influence factor of the fuselage on the wing sweep effect is... In the given two-dimensional interpolation table, based on the given fifth correction parameter and wing aspect ratio Obtained by interpolation, where the fifth correction parameter Calculated using the following formula:

[0080] ;

[0081] in, It is the axial distance between the nose and the point where the wing tip chord is half the length of the fuselage.

[0082] 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 method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described above.

[0083] 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 lateral static stability derivative of a takeoff and landing configuration wing as described above.

[0084] The calculation model in this application reflects the influence of airfoil lift characteristics, wing dihedral angle, wing aspect ratio, tip-root ratio, wing sweep angle, flap span, flap lift coefficient increment, and wing pressure center position change on lateral static stability, and can accurately calculate the lateral static stability derivative of takeoff and landing configuration wings. Attached Figure Description

[0085] Figure 1 This is a flowchart of a preferred embodiment of the method for calculating the lateral static stability derivative of the takeoff and landing configuration wing of this application.

[0086] Figure 2 This is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of this application. Detailed Implementation

[0087] 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.

[0088] The first aspect of this application provides a method for calculating the lateral static stability derivative of a takeoff and landing configuration wing, such as... Figure 1 As shown, it mainly includes:

[0089] Step S1: Determine the lateral static stability derivative generated by the wing planar parameters;

[0090] Step S2: Determine the lateral static stability derivative generated by the dihedral angle on the wing;

[0091] Step S3: Determine the increment of the lateral static stability derivative generated by the flap;

[0092] Step S4: The sum of the lateral static stability derivatives generated by the wing plane parameters, the lateral static stability derivatives generated by the wing dihedral angle, and the lateral static stability derivatives generated by the flaps is taken as the lateral static stability derivative of the flap-out configuration wing.

[0093] The lateral static stability derivative calculation model for takeoff and landing configuration wings established in this application reflects the influence of airfoil lift characteristics, wing dihedral angle, wing aspect ratio, tip root ratio, wing sweep angle, flap span, flap lift coefficient increment, and wing pressure center position change on lateral static stability, and can accurately calculate the lateral static stability derivative of takeoff and landing configuration wings.

[0094] Step S1 provides a method for calculating the lateral static stability derivative generated by the wing plane parameters.

[0095] In some alternative implementations, in step S1, the lateral static stability derivatives generated by the wing plane parameters are calculated using the following formula:

[0096] ;

[0097] in, The lift coefficient, Let be the lateral static stability derivative of the incompressible flow of the wing. This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0098] In some alternative implementations, the parameters are calculated using the following formula. :

[0099] ;

[0100] in, ;

[0101] ;

[0102] For the wing root ratio, The aspect ratio is the wing section ratio.

[0103] In some alternative implementations, the parameters are calculated using the following formula. :

[0104] ;

[0105] in, ;

[0106] ;

[0107] ;

[0108] in, This indicates the location of the wing's aerodynamic pressure center. It is the sweep angle of the wing's half chord.

[0109] Step S2 provides a calculation model for the lateral static stability derivative generated by the dihedral angle on the wing.

[0110] In some alternative implementations, in step S2, the lateral static stability derivative generated by the dihedral angle of the wing is calculated using the following formula. :

[0111] ;

[0112] in, The dihedral angle of the wing. For wing parameters;

[0113] ;

[0114] ;

[0115] in, The lift line slope of the Mach number M airfoil;

[0116] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0117] ;

[0118] Second correction parameter Calculated using the following formula:

[0119] ;

[0120] in, It is the sweep angle of the wing's quarter chord.

[0121] In this embodiment, the three-dimensional interpolation table provides different wing tip root ratios. There is a corresponding two-dimensional interpolation table. Here, only the two-dimensional data table for λ=0.25 is given as an example, as shown in Table 1.

[0122] Table 1 Zv interpolation data (λ=0.5)

[0123]

[0124] Step S3 is used to calculate the lateral static stability derivative increment generated by the flap. .

[0125] In some alternative implementations, in step S3, the increment of the lateral static stability derivative generated by the flap is calculated using the following formula. :

[0126] ;

[0127] in, The increase in lift coefficient caused by flap deployment. The factor influencing the fuselage's effect on the wing sweepback is... The spanwise position of the wing pressure center in the flap deployment configuration. The sweep angle of the wing's half chord is the parameter. In the given two-dimensional interpolation table, based on the given third correction parameter and wing root ratio The third correction parameter is obtained through interpolation. For wing aspect ratio The reciprocal of.

[0128] In some alternative implementations, the wing span position In the given two-dimensional interpolation table, based on the given fourth correction parameter and wing root ratio The fourth correction parameter is obtained through interpolation. Calculated using the following formula:

[0129] ;

[0130] in, This refers to the spanwise position of the outer side of the trailing edge flap on the wing. This refers to the wingspan of the aircraft wing.

[0131] In some alternative implementations, the influence factor of the fuselage on the wing sweep effect In the given two-dimensional interpolation table, based on the given fifth correction parameter and wing aspect ratio Obtained by interpolation, where the fifth correction parameter Calculated using the following formula:

[0132] ;

[0133] in, It is the axial distance between the nose and the point where the wing tip chord is half the length of the fuselage.

[0134] The example aircraft has a wingspan of 26m, an aspect ratio of 7.6, a tip-to-root ratio of 0.246, a quarter-chord sweep angle of 30°, a half-chord sweep angle of 26.46°, and a dihedral of 3°. The distance from the nose to the half-chord length point of the wing tip chord along the fuselage axis is 16.5m, and the outer flap is located 8.8m across the wing span.

[0135] Calculation conditions: Flight Mach number is 0.2, and the lift line slope of the airfoil at Mach 0.2 is 7.6 / rsd. The lift coefficient of the 4.2° angle of attack wing is 0.5, and the lift coefficient increment after flap deployment is 0.8. The flow chart for the lateral static stability derivative of the flap-deployed wing is as follows:

[0136] (1) The lateral static stability derivative generated by the computer wing plane parameters is -0.0625 / rad;

[0137] (2) The lateral static stability derivative generated by the dihedral angle on the computer wing is -0.042 / rad;

[0138] (3) Calculate the lateral static stability derivative increment generated by the flap -0.0685 / rad;

[0139] (4) Determine the lateral static stability derivative of the wing with flaps extended: -0.173 / rad.

[0140] The second aspect of this application provides a device for calculating the lateral static stability derivative of a takeoff and landing configuration wing corresponding to the above method, mainly comprising:

[0141] The module for determining the lateral static stability derivative generated by the wing plane parameters is used to determine the lateral static stability derivative generated by the wing plane parameters.

[0142] The module for determining the lateral static stability derivative generated by the dihedral angle of the wing is used to determine the lateral static stability derivative generated by the dihedral angle of the wing.

[0143] The lateral static stability derivative increment determination module is used to determine the lateral static stability derivative increment generated by the flap;

[0144] The module for determining the lateral static stability derivative of flap-extended configuration wings is used to take the sum of the lateral static stability derivatives generated by the wing plane parameters, the lateral static stability derivatives generated by the wing dihedral angle, and the lateral static stability derivative increments generated by the flaps as the lateral static stability derivatives of flap-extended configuration wings.

[0145] In some alternative implementations, in the lateral static stability derivative determination module generated by the wing plane parameters, the lateral static stability derivative generated by the wing plane parameters is calculated using the following formula:

[0146] ;

[0147] in, The lift coefficient, Let be the lateral static stability derivative of the incompressible flow of the wing. This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

[0148] In some alternative implementations, the parameters are calculated using the following formula. :

[0149] ;

[0150] in, ;

[0151] ;

[0152] For the wing root ratio, The aspect ratio is the wing section ratio.

[0153] In some alternative implementations, the parameters are calculated using the following formula. :

[0154] ;

[0155] in, ;

[0156] ;

[0157] ;

[0158] in, This indicates the location of the wing's aerodynamic pressure center. It is the sweep angle of the wing's half chord.

[0159] In some alternative implementations, in the module for determining the lateral static stability derivative generated by the dihedral angle on the wing, the lateral static stability derivative generated by the dihedral angle on the wing is calculated using the following formula. :

[0160] ;

[0161] in, The dihedral angle of the wing. For wing parameters;

[0162] ;

[0163] ;

[0164] in, The lift line slope of the Mach number M airfoil;

[0165] In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula:

[0166] ;

[0167] Second correction parameter Calculated using the following formula:

[0168] ;

[0169] in, It is the sweep angle of the wing's quarter chord.

[0170] In some optional embodiments, in the lateral static stability derivative increment determination module, the lateral static stability derivative increment generated by the flap is calculated using the following formula. :

[0171] ;

[0172] in, The increase in lift coefficient caused by flap deployment. The factor influencing the fuselage's effect on the wing sweepback is... The spanwise position of the wing pressure center in the flap deployment configuration. The sweep angle of the wing's half chord is the parameter. In the given two-dimensional interpolation table, based on the given third correction parameter and wing root ratio The third correction parameter is obtained through interpolation. For wing aspect ratio The reciprocal of.

[0173] In some alternative implementations, the wing span position In the given two-dimensional interpolation table, based on the given fourth correction parameter and wing root ratio The fourth correction parameter is obtained through interpolation. Calculated using the following formula:

[0174] ;

[0175] in, This refers to the spanwise position of the outer side of the trailing edge flap on the wing. This refers to the wingspan of the aircraft wing.

[0176] In some alternative implementations, the influence factor of the fuselage on the wing sweep effect In the given two-dimensional interpolation table, based on the given fifth correction parameter and wing aspect ratio Obtained by interpolation, where the fifth correction parameter Calculated using the following formula:

[0177] ;

[0178] in, It is the axial distance between the nose and the point where the wing tip chord is half the length of the fuselage.

[0179] 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 lateral static stability derivative of a take-off and landing configuration wing as described above.

[0180] In a fourth aspect, this application provides a readable storage medium storing a computer program that, when executed by a processor, implements the method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as 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.

[0181] The following is for reference. Figure 2 It shows a schematic diagram of the structure of a computer device 400 suitable for implementing the embodiments of this application. Figure 2 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.

[0182] like Figure 2 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.

[0183] 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.

[0184] 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.

[0185] 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.

[0186] 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.

[0187] 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 lateral static stability derivative of a takeoff and landing configuration wing, characterized in that, include: Step S1: Determine the lateral static stability derivative generated by the wing planar parameters; Step S2: Determine the lateral static stability derivative generated by the dihedral angle on the wing; Step S3: Determine the increment of the lateral static stability derivative generated by the flap; Step S4: The sum of the lateral static stability derivatives generated by the wing plane parameters, the lateral static stability derivatives generated by the wing dihedral angle, and the lateral static stability derivatives generated by the flaps is taken as the lateral static stability derivative of the flap-out configuration wing.

2. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 1, characterized in that, In step S1, the lateral static stability derivatives generated by the computer wing plane parameters are calculated using the following formula: ； in, The lift coefficient, Let be the lateral static stability derivative of the incompressible flow of the wing. This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

3. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 2, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； For the wing root ratio, The aspect ratio is the wing section ratio.

4. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 3, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； ； in, This indicates the location of the wing's aerodynamic pressure center. It is the sweep angle of the wing's half chord.

5. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 1, characterized in that, In step S2, the lateral static stability derivative generated by the dihedral angle of the computer wing is calculated using the following formula. : ； in, The dihedral angle of the wing. For wing parameters; ； ； in, The lift line slope of the Mach number M airfoil; In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula: ； Second correction parameter Calculated using the following formula: ； in, It is the sweep angle of the wing's quarter chord.

6. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 1, characterized in that, In step S3, the increment of the lateral static stability derivative generated by the flap is calculated using the following formula. : ； in, The increase in lift coefficient caused by flap deployment. The factor influencing the fuselage's effect on the wing sweepback is... The spanwise position of the wing pressure center in the flap deployment configuration. The sweep angle is the half-chord sweep angle of the wing. In the given two-dimensional interpolation table, based on the given third correction parameter and wing root ratio The third correction parameter is obtained through interpolation. For wing aspect ratio The reciprocal of.

7. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 6, characterized in that, Wing span position In the given two-dimensional interpolation table, based on the given fourth correction parameter and wing root ratio The fourth correction parameter is obtained through interpolation. Calculated using the following formula: ； in, This refers to the spanwise position of the outer side of the trailing edge flap on the wing. This refers to the wingspan of the aircraft wing.

8. The method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 6, characterized in that, Factors influencing the fuselage's effect on wing sweepback In the given two-dimensional interpolation table, based on the given fifth correction parameter and wing aspect ratio Obtained by interpolation, where the fifth correction parameter Calculated using the following formula: ； in, It is the axial distance between the nose and the point where the wing tip chord is half the length of the fuselage.

9. A device for calculating the lateral static stability derivative of a takeoff and landing configuration wing, characterized in that, include: The module for determining the lateral static stability derivative generated by the wing plane parameters is used to determine the lateral static stability derivative generated by the wing plane parameters. The module for determining the lateral static stability derivative generated by the dihedral angle of the wing is used to determine the lateral static stability derivative generated by the dihedral angle of the wing. The lateral static stability derivative increment determination module is used to determine the lateral static stability derivative increment generated by the flap; The module for determining the lateral static stability derivative of flap-extended configuration wings is used to take the sum of the lateral static stability derivatives generated by the wing plane parameters, the lateral static stability derivatives generated by the wing dihedral angle, and the lateral static stability derivative increments generated by the flaps as the lateral static stability derivatives of flap-extended configuration wings.

10. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 9, characterized in that, In the module for determining the lateral static stability derivative generated by the wing plane parameters, the lateral static stability derivative generated by the wing plane parameters is calculated using the following formula: ； in, The lift coefficient, Let be the lateral static stability derivative of the incompressible flow of the wing. This is the correction for the lateral static stability derivative of the sweep angle of an incompressible flow wing.

11. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 10, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； For the wing root ratio, The aspect ratio is the wing section ratio.

12. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 11, characterized in that, Parameters are calculated using the following formula. : ； in, ; ； ； in, This indicates the location of the wing's aerodynamic pressure center. It is the sweep angle of the wing's half chord.

13. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 9, characterized in that, In the module for determining the lateral static stability derivative generated by the dihedral angle on the wing, the lateral static stability derivative generated by the dihedral angle on the wing is calculated using the following formula. : ； in, The dihedral angle of the wing. For wing parameters; ； ； in, The lift line slope of the Mach number M airfoil; In a given three-dimensional interpolation table, based on a given first correction parameter Second correction parameter and wing root ratio interpolate wing parameters The first correction parameter Calculated using the following formula: ； Second correction parameter Calculated using the following formula: ； in, It is the sweep angle of the wing's quarter chord.

14. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 9, characterized in that, In the lateral static stability derivative increment determination module, the lateral static stability derivative increment generated by the flap is calculated using the following formula. : ； in, The increase in lift coefficient caused by flap deployment. The factor influencing the fuselage's effect on the wing sweepback is... The spanwise position of the wing pressure center in the flap deployment configuration. The sweep angle is the half-chord sweep angle of the wing. In the given two-dimensional interpolation table, based on the given third correction parameter and wing root ratio The third correction parameter is obtained through interpolation. For wing aspect ratio The reciprocal of.

15. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 14, characterized in that, Wing span position In the given two-dimensional interpolation table, based on the given fourth correction parameter and wing root ratio The fourth correction parameter is obtained through interpolation. Calculated using the following formula: ； in, This refers to the spanwise position of the outer side of the trailing edge flap on the wing. This refers to the wingspan of the aircraft wing.

16. The device for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in claim 14, characterized in that, Factors influencing the fuselage's effect on wing sweepback In the given two-dimensional interpolation table, based on the given fifth correction parameter and wing aspect ratio Obtained by interpolation, where the fifth correction parameter Calculated using the following formula: ； in, It is the axial distance between the nose and the point where the wing tip chord is half the length of the fuselage.

17. 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 method for calculating the lateral static stability derivative of a takeoff and landing configuration wing as described in any one of claims 1-8.

18. 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 lateral static stability derivative of the take-off and landing configuration wing as described in any one of claims 1-8.

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