Method and device for calculating course static stability derivative of wing body assembly

Abstract

The invention belongs to the technical field of aircraft design, and relates to a method and a device for calculating a course static stability derivative of a wing body assembly. The method comprises the following steps: S1, determining a lateral force derivative of the wing body assembly; s2, determining a wing body assembly course static stability derivative relative to the center point of the fuselage; and S3, according to the wing body assembly lateral force derivative and the wing body assembly course static stability derivative relative to the center of gravity of the aircraft, determining a wing body assembly course static stability derivative relative to the center of gravity of the aircraft. The calculation model reflects the influence of the lateral projection area of the fuselage, the length of the fuselage, the height of the main control cross section of the fuselage, the width of the fuselage, the extension length of a wing, the area of the wing, the aspect ratio of the wing, the tip-root ratio, the installation position of the wing and the dihedral angle of the wing on the course static stability; the lateral force derivative, the lateral force pressure center position and the course static stability derivative of the wing body assembly 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 directional static stability derivative of a wing-body combination. Background Technology

[0002] The fuselage is a critical component generating directional instability, and the aerodynamic interference of the wing on the fuselage cannot be ignored. Calculating the directional static stability derivative of the wing-body assembly is essential for accurately analyzing the aircraft's directional static stability. Sensitive parameters for wing aerodynamic interference include: wing area, aspect ratio, tip-root ratio, mounting position, and dihedral angle. Sensitive parameters for fuselage lateral force and pressure center location include: fuselage lateral projected area, fuselage length, width and height of the cross-section at the wing-body junction, and height of the cross-section at 25% and 75% of the fuselage axial position. Due to the large number of parameters involved, the calculation model for the directional static stability derivative of the wing-body assembly is quite complex. How to accurately construct a calculation model for the directional static stability derivative of the wing-body assembly to guide the structural optimization of the wing-body assembly is a pressing 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 directional static stability derivative of a wing-body assembly, providing technical support for the calculation and evaluation of aircraft directional static stability.

[0004] The first aspect of this application provides a method for calculating the directional static stability derivative of a wing-body combination, mainly including:

[0005] Step S1: Determine the derivative of the lateral force of the wing-body combination;

[0006] Step S2: Determine the directional static stability derivative of the wing-body assembly relative to the fuselage center point;

[0007] Step S3: Determine the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity based on the lateral force derivative of the wing-body assembly and the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0008] Preferably, in step S1, the derivative of the lateral force of the wing-body combination is calculated using the following formula. :

[0009] ;

[0010] in, The height of the fuselage cross-section at the junction of the wing and fuselage. This refers to the lateral area of ​​the fuselage. For wing area, For wingspan, denoted as dihedral angle on the wing, and z is the height of the point at 1 / 4 chord length of the wing root chord from the fuselage centerline.

[0011] parameter 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 The interpolation calculation is obtained from the given second interpolation table;

[0012] ;

[0013] ;

[0014] Where d is the width of the fuselage cross-section.

[0015] Preferably, in step S2, the directional static stability derivative of the wing-body assembly relative to the fuselage center point is calculated using the following formula. :

[0016] ;

[0017] in, The height of the cross-section at 25% of the fuselage. The height of the fuselage at 75% of its cross-section. This refers to the fuselage length.

[0018] Preferably, in step S3, the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is calculated using the following formula. :

[0019] ;

[0020] in, This is the axial distance from the center of gravity to the nose and fuselage.

[0021] The second aspect of this application provides a device for calculating the directional static stability derivative of a wing-body combination, mainly comprising:

[0022] The lateral force derivative determination module for wing-body combination is used to determine the lateral force derivative of the wing-body combination.

[0023] The module for determining the directional static stability derivative of the wing-body assembly relative to the fuselage center point is used to determine the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0024] The module for determining the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is used to determine the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity based on the lateral force derivative of the wing-body assembly and the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0025] Preferably, in the wing-body combination lateral force derivative determination module, the wing-body combination lateral force derivative is calculated using the following formula. :

[0026] ;

[0027] in, The height of the fuselage cross-section at the junction of the wing and fuselage. This refers to the lateral area of ​​the fuselage. For wing area, For wingspan, denoted as dihedral angle on the wing, and z is the height of the point at 1 / 4 chord length of the wing root chord from the fuselage centerline.

[0028] parameter 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 The interpolation calculation is obtained from the given second interpolation table;

[0029] ;

[0030] ;

[0031] Where d is the width of the fuselage cross-section.

[0032] Preferably, in the wing-body assembly directional static stability derivative determination module relative to the fuselage center point, the wing-body assembly directional static stability derivative relative to the fuselage center point is calculated using the following formula. :

[0033] ;

[0034] in, The height of the cross-section at 25% of the fuselage. The height of the fuselage at 75% of its cross-section. This refers to the fuselage length.

[0035] Preferably, in the wing-body assembly directional static stability derivative determination module relative to the aircraft's center of gravity, the wing-body assembly directional static stability derivative is calculated using the following formula. :

[0036] ;

[0037] in, This is the axial distance from the center of gravity to the nose and fuselage.

[0038] 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 directional static stability derivative of a wing-body combination as described above.

[0039] 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 directional static stability derivative of a wing-body combination as described above.

[0040] The calculation model in this application reflects the influence of the fuselage lateral projected area, fuselage length, height of the main control cross section of the fuselage, fuselage width and wingspan, wing area, wing aspect ratio, tip-root ratio, wing mounting position and wing dihedral angle on directional static stability. It can accurately calculate the lateral force derivative, lateral force pressure center position and directional static stability derivative of the wing-fuselage assembly. Attached Figure Description

[0041] Figure 1 This is a flowchart of a preferred embodiment of the method for calculating the directional static stability derivative of the wing-body combination in this application.

[0042] Figure 2 This is a schematic diagram defining the structural parameters of the wing-body assembly in this application.

[0043] Figure 3 This application Figure 2 Side view of the embodiment shown.

[0044] Figure 4 This is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of this application. Detailed Implementation

[0045] 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.

[0046] The first aspect of this application provides a method for calculating the directional static stability derivative of a wing-body assembly, such as... Figure 1As shown, it mainly includes:

[0047] Step S1: Determine the derivative of the lateral force of the wing-body combination;

[0048] Step S2: Determine the directional static stability derivative of the wing-body assembly relative to the fuselage center point;

[0049] Step S3: Determine the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity based on the lateral force derivative of the wing-body assembly and the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0050] The directional static stability derivative calculation model for the wing-body combination established in this application reflects the influence of the fuselage lateral projected area, fuselage length, height of the main control cross section of the fuselage, fuselage width and wingspan, wing area, wing aspect ratio, tip root ratio, wing mounting position and wing dihedral angle on directional static stability.

[0051] Step S1 is used to calculate the derivative of the lateral force of the wing-body combination.

[0052] In some optional embodiments, in step S1, the derivative of the lateral force of the wing-body combination is calculated using the following formula. :

[0053] ;

[0054] Among them, reference Figure 2 and Figure 3 , The height of the fuselage cross-section at the junction of the wing and fuselage. This refers to the lateral area of ​​the fuselage. For wing area, For wingspan, denoted as dihedral angle on the wing, and z is the height of the point at 1 / 4 chord length of the wing root chord from the fuselage centerline.

[0055] parameter The parameters are calculated based on the interpolation values ​​of bd and zx in a given first interpolation table, as shown in Table 1. Based on the wing aspect ratio A and the wing tip root ratio The interpolation calculation is obtained by interpolation in a given second interpolation table, which is shown in the table below.

[0056] ;

[0057] ;

[0058] Where d is the width of the fuselage cross-section.

[0059] Table 1 Data required for interpolation calculation

[0060]

[0061] Table 2 Data required for interpolation calculation

[0062]

[0063] Step S2 is used to calculate the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0064] In some alternative implementations, in step S2, the directional static stability derivative of the wing-body assembly relative to the fuselage center point is calculated using the following formula. :

[0065] ;

[0066] in, The height of the cross-section at 25% of the fuselage. The height of the fuselage at 75% of its cross-section. This refers to the fuselage length.

[0067] Step S3 is used to calculate the directional static stability derivative of the wing-body combination relative to the aircraft's center of gravity.

[0068] In some alternative implementations, in step S3, the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is calculated using the following formula. :

[0069] ;

[0070] in, This is the axial distance from the center of gravity to the nose and fuselage.

[0071] The wing area of ​​the example aircraft is 149.6 m². 2 The fuselage has a wingspan of 32m, an aspect ratio of 6.85, a tip-root ratio of 0.47, a dihedral angle of 2.5°, and a wing mounting height of 1.3m. The fuselage is 36m long, with a cross-sectional width of 4m and a height of 4m. The height of the cross-section at both the 25% and 75% axial positions is 4m. The lateral projected area of ​​the fuselage is 122m². 2 .

[0072] Calculation conditions: The distance from the center of gravity to the fuselage axial direction is 19.4m. The flow chart for the directional static stability derivative of the wing-body combination is as follows:

[0073] (1) The derivative of the lateral force of the wing-body combination is -0.211 / rad.

[0074] (2) Calculate the directional static stability derivative of the wing-body assembly relative to the fuselage center point as -0.085 / rad.

[0075] (3) Calculate the directional static stability derivative of the wing-body combination relative to the center of gravity of the aircraft: -0.094 / rad.

[0076] The second aspect of this application provides a wing-body combination directional static stability derivative calculation device corresponding to the above method, mainly comprising:

[0077] The lateral force derivative determination module for wing-body combination is used to determine the lateral force derivative of the wing-body combination.

[0078] The module for determining the directional static stability derivative of the wing-body assembly relative to the fuselage center point is used to determine the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0079] The module for determining the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is used to determine the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity based on the lateral force derivative of the wing-body assembly and the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

[0080] In some optional embodiments, in the wing-body combination lateral force derivative determination module, the wing-body combination lateral force derivative is calculated using the following formula. :

[0081] ;

[0082] in, The height of the fuselage cross-section at the junction of the wing and fuselage. This refers to the lateral area of ​​the fuselage. For wing area, For wingspan, denoted as dihedral angle on the wing, and z is the height of the point at 1 / 4 chord length of the wing root chord from the fuselage centerline.

[0083] parameter 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 The interpolation calculation is obtained from the given second interpolation table;

[0084] ;

[0085] ;

[0086] Where d is the width of the fuselage cross-section.

[0087] In some optional embodiments, in the wing-body assembly directional static stability derivative determination module relative to the fuselage center point, the wing-body assembly directional static stability derivative relative to the fuselage center point is calculated using the following formula. :

[0088] ;

[0089] in, The height of the cross-section at 25% of the fuselage. The height of the fuselage at 75% of its cross-section. This refers to the fuselage length.

[0090] In some alternative implementations, in the wing-body assembly directional static stability derivative determination module relative to the aircraft's center of gravity, the wing-body assembly directional static stability derivative is calculated using the following formula. :

[0091] ;

[0092] in, This is the axial distance from the center of gravity to the nose and fuselage.

[0093] 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 directional static stability derivative of a wing-body combination as described above.

[0094] 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 directional static stability derivative of a wing-body assembly 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.

[0095] The following is for reference. Figure 4 It shows a schematic diagram of the structure of a computer device 400 suitable for implementing the embodiments of this application. Figure 4 The computer device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments described in this application.

[0096] like Figure 4As 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.

[0097] 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.

[0098] 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.

[0099] 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.

[0100] 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.

[0101] 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 directional static stability derivative of a wing-body composite, characterized in that, include: Step S1: Determine the derivative of the lateral force of the wing-body combination; Step S2: Determine the directional static stability derivative of the wing-body assembly relative to the fuselage center point; Step S3: Determine the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity based on the lateral force derivative of the wing-body assembly and the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

2. The method for calculating the directional static stability derivative of a wing-body assembly as described in claim 1, characterized in that, In step S1, the derivative of the lateral force of the wing-body combination is calculated using the following formula. : ； in, The height of the fuselage cross-section at the junction of the wing and fuselage. The side area of ​​the fuselage. For wing area, For wingspan, denoted as dihedral angle on the wing, and z is the height of the point at 1 / 4 chord length of the wing root chord from the fuselage centerline. parameter 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 The interpolation calculation is obtained from the given second interpolation table; ； ； Where d is the width of the fuselage cross-section.

3. The method for calculating the directional static stability derivative of a wing-body assembly as described in claim 2, characterized in that, In step S2, the directional static stability derivative of the wing-body assembly relative to the fuselage center point is calculated using the following formula. : ； in, The height of the cross-section at 25% of the fuselage. The height of the fuselage at 75% of its cross-section. This refers to the fuselage length.

4. The method for calculating the directional static stability derivative of a wing-body assembly as described in claim 3, characterized in that, In step S3, the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is calculated using the following formula. : ； in, This is the axial distance from the center of gravity to the nose and fuselage.

5. A device for calculating the directional static stability derivative of a wing-body combination, characterized in that, include: The lateral force derivative determination module for wing-body combination is used to determine the lateral force derivative of the wing-body combination. The module for determining the directional static stability derivative of the wing-body assembly relative to the fuselage center point is used to determine the directional static stability derivative of the wing-body assembly relative to the fuselage center point. The module for determining the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is used to determine the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity based on the lateral force derivative of the wing-body assembly and the directional static stability derivative of the wing-body assembly relative to the fuselage center point.

6. The method for calculating the directional static stability derivative of a wing-body assembly as described in claim 5, characterized in that, In the lateral force derivative determination module for the wing-body assembly, the lateral force derivative of the wing-body assembly is calculated using the following formula. : ； in, The height of the fuselage cross-section at the junction of the wing and fuselage. The side area of ​​the fuselage. For wing area, For wingspan, denoted as dihedral angle on the wing, and z is the height of the point at 1 / 4 chord length of the wing root chord from the fuselage centerline. parameter 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 The interpolation calculation is obtained from the given second interpolation table; ； ； Where d is the width of the fuselage cross-section.

7. The method for calculating the directional static stability derivative of a wing-body assembly as described in claim 6, characterized in that, In the module for determining the directional static stability derivative of the wing-body assembly relative to the fuselage center point, the directional static stability derivative of the wing-body assembly relative to the fuselage center point is calculated using the following formula. : ； in, The height of the cross-section at 25% of the fuselage. The height of the fuselage at 75% of its cross-section. This refers to the fuselage length.

8. The method for calculating the directional static stability derivative of a wing-body assembly as described in claim 7, characterized in that, In the module for determining the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity, the directional static stability derivative of the wing-body assembly relative to the aircraft's center of gravity is calculated using the following formula. : ； in, This is the axial distance from the center of gravity to the nose and fuselage.

9. 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 directional static stability derivative of the wing-body combination as described in any one of claims 1-4.

10. 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 directional static stability derivative of the wing-body combination as described in any one of claims 1-4.

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