Method and device for determining a stall angle of attack of a low-aspect-ratio wing

Abstract

The application belongs to the field of flight control technology, and particularly relates to a stall angle of attack determination method and device for a small aspect ratio wing. The method comprises the following steps: S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table respectively according to a wing root ratio; S2, determining a first interpolation parameter CAB1 according to the first correction coefficient and determining a second interpolation parameter CAB2 according to the second correction coefficient; S3, determining a basic value of the stall angle of attack of the wing in a third interpolation table according to the first interpolation parameter CAB1; S4, determining a stall angle of attack correction amount in a fourth interpolation table according to the second interpolation parameter CAB2; and S5, determining the stall angle of attack according to the basic value of the stall angle of attack of the wing and the stall angle of attack correction amount. The application has high calculation efficiency and controllable calculation precision for the stall angle of attack of the small aspect ratio wing.

Description

Technical Field

[0001] The present application belongs to the field of aircraft design technology, and in particular relates to a method and device for determining the stall angle of attack of a low-aspect-ratio wing. Background Art

[0002] The maximum lift coefficient and stall angle of attack are important parameters for evaluating fighter jet maneuverability. The design of an aircraft's flight envelope and pitch control rate requires accurate data on these parameters. Wing sweep angle, aspect ratio, and flight speed significantly influence the maximum lift coefficient and stall angle of attack of a low-aspect-ratio wing. The leading edge sharpness and location of maximum thickness are also sensitive to these factors. Furthermore, the influence of the wing's tip-to-root ratio is also significant. Existing theoretical algorithms do not consider these parameters, resulting in significant discrepancies between theoretically calculated values ​​and actual data, leading to low accuracy. Summary of the Invention

[0003] In order to solve the above problems, the present application provides a method and device for determining the stall angle of attack of a low-aspect-ratio wing, providing technical support for the wing configuration parameter design, airfoil sensitive parameter design, and lift and stall characteristics evaluation of the aircraft high-speed configuration of a low-aspect-ratio aircraft.

[0004] In a first aspect, the present application provides a method for determining the stall angle of attack of a low aspect ratio wing, the method mainly comprising:

[0005] Step S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 from a first interpolation table and a second interpolation table respectively according to the wing tip-to-root ratio λ;

[0006] Step S2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient;

[0007] Step S3: Determine the basic value of the wing stall angle of attack α in the third interpolation table according to the first interpolation parameter CAB1. maxb ;

[0008] Step S4: Determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2. max ;

[0009] Step S5: According to the basic value of the wing stall angle of attack α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0010] Preferably, in step S2, the first interpolation parameter CAB1 is determined by the following formula:

[0011]

[0012] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0013] Preferably, in step S2, the second interpolation parameter CAB2 is determined by the following formula:

[0014] CAB2=(C 2+1)ARtanΛ LE .

[0015] Preferably, in step S4, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is Mach number M a , the second interpolation parameter CAB2 and the stall angle correction value Δα max Constructed two-dimensional interpolation table;

[0016] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table. max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0017] Where, ASH = AR cosΛ LE (1+4λ 2 ).

[0018] A second aspect of the present application provides a device for determining the stall angle of attack of a low-aspect-ratio wing, comprising:

[0019] A correction coefficient interpolation module is used to interpolate a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table according to the wing tip root ratio λ;

[0020] an interpolation parameter calculation module, configured to determine a first interpolation parameter CAB1 according to a first correction coefficient, and to determine a second interpolation parameter CAB2 according to a second correction coefficient;

[0021] The wing stall angle of attack basic value determination module is used to determine the wing stall angle of attack basic value α in the third interpolation table according to the first interpolation parameter CAB1 maxb ;

[0022] A stall angle correction value determination module is used to determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2 max ;

[0023] The stall angle determination module is used to determine the stall angle of attack of the wing according to the basic value α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0024] Preferably, in the interpolation parameter calculation module, the first interpolation parameter CAB1 is determined by the following formula:

[0025]

[0026] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0027] Preferably, in the interpolation parameter calculation module, the second interpolation parameter CAB2 is determined by the following formula:

[0028] CAB2=(C2+1)ARtanΛ LE .

[0029] Preferably, in the stall angle correction value determination module, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is Mach number M a , the second interpolation parameter CAB2 and the stall angle correction value Δα max Constructed two-dimensional interpolation table;

[0030] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table. max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0031] Where, ASH = AR cosΛ LE (1+4λ2 ).

[0032] A third aspect of the present application provides a computer device, 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 determining the stall angle of attack of a low aspect ratio wing as described above.

[0033] In a fourth aspect, the present application provides a readable storage medium storing a computer program. When the computer program is executed by a processor, it is used to implement the method for determining the stall angle of attack of a low aspect ratio wing as described above.

[0034] Based on experimental data, this application deeply analyzes the effects of airfoil sensitive parameters, wing plan parameters, and flight speed on stall angle of attack. It also reflects the influence of wing configuration parameters and flight speed on stall angle of attack.

[0035] The present application has high calculation efficiency and controllable calculation accuracy for small aspect ratio stall angle of attack. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 This is a flow chart of a preferred embodiment of the method for determining the stall angle of attack of a low aspect ratio wing of the present application.

[0037] Figure 2 It is a structural diagram of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and should not be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in conjunction with the drawings.

[0039] The first aspect of the present application provides a method for determining the stall angle of attack of a low aspect ratio wing, such as Figure 1 As shown, the method mainly includes:

[0040] Step S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 from a first interpolation table and a second interpolation table respectively according to the wing tip-to-root ratio λ;

[0041] Step S2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient;

[0042] Step S3: Determine the basic value of the wing stall angle of attack α in the third interpolation table according to the first interpolation parameter CAB1. maxb ;

[0043] Step S4: Determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2. max ;

[0044] Step S5: According to the basic value of the wing stall angle of attack α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0045] The first correction coefficient C1 and the second correction coefficient C2 of step S1 of this application are both obtained by interpolating the single parameter of the wing tip root ratio λ. Table 1 below gives a first interpolation table for representing the relationship between the wing tip root ratio λ and the first correction coefficient C1, and Table 2 gives a second interpolation table for representing the relationship between the wing tip root ratio λ and the second correction coefficient C2.

[0046] Table 1 First interpolation table

[0047] λ C1 0 0 0.1 0.24 0.2 0.494 0.3 0.5 0.4 0.48 0.6 0.21 0.8 0.09 1 0

[0048] Table 2 Second interpolation table

[0049]

[0050]

[0051] In some optional implementations, in step S2, the first interpolation parameter CAB1 is determined by the following formula:

[0052]

[0053] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0054] In some optional implementations, in step S2, the second interpolation parameter CAB2 is determined by the following formula:

[0055] CAB2=(C2+1)ARtanΛ LE .

[0056] Then in step S3, the third interpolation table is shown in Table 3 below. According to the first interpolation parameter CAB1, the basic value of the wing stall angle of attack α can be directly interpolated. maxb .

[0057] Table 3 Data required for interpolation calculation of basic stall angle of attack values

[0058] CAB1 0 0.4 0.8 1 1.2 1.6 2 2.5 3 <![CDATA[α maxb ]]> 35 35 35 34 32 28 25 23 22

[0059] In some optional embodiments, in step S4, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is Mach number M a , the second interpolation parameter CAB2 and the stall angle correction value Δα max Constructed two-dimensional interpolation table;

[0060] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table. max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0061] Where, ASH = AR cosΛ LE (1+4λ 2) .

[0062] Table 4 gives the fourth ASH interpolation table, and Table 5 gives the fourth Mach number interpolation table. In Table 4, the first column of data is the ASH parameter, the second row of data is the second interpolation parameter CAB2, and the other data is the stall angle correction value Δα max In Table 5, the first column of data is the Mach number, the second row of data is the second interpolation parameter CAB2, and the other data are the stall angle correction value Δα max .

[0063] Table 4 Fourth ASH interpolation table

[0064]

[0065] Table 5 Interpolation table of the fourth Mach number

[0066]

[0067] This application uses supersonic lift calculation theory and a large number of wind tunnel tests to deeply analyze the effects of airfoil sensitive parameters, wing plane parameters and flight speed on the stall angle of attack based on the test data, thereby constructing the above-mentioned multiple interpolation tables. Based on these interpolation tables, relevant calculation parameters are interpolated to accurately reflect the influence of wing configuration on the stall angle of attack, thereby enabling more accurate calculation of the stall angle of attack and improving calculation accuracy and efficiency.

[0068] A second aspect of the present application provides a device for determining the stall angle of attack of a low aspect ratio wing corresponding to the above method, mainly comprising:

[0069] A correction coefficient interpolation module is used to interpolate a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table according to the wing tip root ratio λ;

[0070] an interpolation parameter calculation module, configured to determine a first interpolation parameter CAB1 according to a first correction coefficient, and to determine a second interpolation parameter CAB2 according to a second correction coefficient;

[0071] The wing stall angle of attack basic value determination module is used to determine the wing stall angle of attack basic value α in the third interpolation table according to the first interpolation parameter CAB1 maxb ;

[0072] A stall angle correction value determination module is used to determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2 max ;

[0073] The stall angle determination module is used to determine the stall angle of attack of the wing according to the basic value α maxb and the stall angle correction Δα max Determine the stall angle of attack α max :α max =α maxb +Δα max .

[0074] In some optional implementations, in the interpolation parameter calculation module, the first interpolation parameter CAB1 is determined by the following formula:

[0075]

[0076] When M a <1 o'clock, When M a ≥1, Among them, Λ LE is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number.

[0077] In some optional implementations, in the interpolation parameter calculation module, the second interpolation parameter CAB2 is determined by the following formula:

[0078] CAB2=(C2+1)ARtanΛ LE .

[0079] In some optional embodiments, in the stall angle correction value determination module, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table, wherein the fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is Mach number M a , the second interpolation parameter CAB2 and the stall angle correction value Δα max Constructed two-dimensional interpolation table;

[0080] When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value Δα is interpolated using the fourth ASH interpolation table. max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value Δα is interpolated using the fourth Mach number interpolation table. max ;

[0081] Where, ASH = AR cosΛ LE (1+4λ 2 ).

[0082] In a third aspect of the present application, a computer device 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 a method for determining a stall angle of attack of a wing with a low aspect ratio.

[0083] In a fourth aspect, the present application provides a readable storage medium storing a computer program that, when executed by a processor, implements the method for determining the stall angle of attack of a low-aspect-ratio wing as described above. The computer-readable storage medium may be included in the apparatus described in the above embodiments, or it may exist independently and not be incorporated into the apparatus. The computer-readable storage medium carries one or more programs, and when executed by the apparatus, the one or more programs process data according to the method described above.

[0084] Reference below Figure 2 , which shows a structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 2 The computer device shown is only an example and should not limit the functions and scope of use of the embodiments of the present application.

[0085] like Figure 2As shown, 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 portion 408 into a random access memory (RAM) 403. Various programs and data required for the operation of device 400 are also stored in RAM 403. CPU 401, ROM 402, and RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to bus 404.

[0086] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, and the like; an output section 407 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 408 including a hard disk; and a communication section 409 including a network interface card such as a LAN card or a modem. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as needed. Removable media 411, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 410 as needed, so that computer programs read therefrom can be installed into the storage section 408 as needed.

[0087] In particular, according to the embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the method of the present application are executed. It should be noted that the computer storage medium of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, but not limited to, a system, device or component of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection having one or more conductors, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this application, a computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction 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, which carries computer-readable program code. Such a propagated data signal may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transfer a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code embodied on a computer-readable medium may be transmitted using any suitable medium, including, but not limited to, wireless, wire, optical cable, RF, etc., or any suitable combination thereof.

[0088] The flow charts and block diagrams in the accompanying drawings illustrate the possible architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, program segment or a part of code, and the module, program segment or a part of code includes one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a sequence different from that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flow chart, and the combination of the boxes in the block diagram and / or flow chart can be implemented by a dedicated hardware-based system that performs the specified function or operation, or can be implemented by a combination of dedicated hardware and computer instructions.

[0089] The modules or units described in the embodiments of this application may be implemented in software or hardware. The modules or units described may also be provided in a processor, and the names of these modules or units do not, in certain circumstances, limit the modules or units themselves.

[0090] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for determining the stall angle of attack of a low aspect ratio wing, characterized in that: include: Step S1, interpolating a first correction coefficient C1 and a second correction coefficient C2 from a first interpolation table and a second interpolation table respectively according to the wing tip-to-root ratio λ; Step S2, determining a first interpolation parameter CAB1 according to the first correction coefficient, and determining a second interpolation parameter CAB2 according to the second correction coefficient; Step S3: Determine the basic value of the wing stall angle of attack α in the third interpolation table according to the first interpolation parameter CAB1. maxb ; Step S4: Determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2. max ; Step S5: Determine the stall angle of attack α based on the wing stall angle of attack basic value and the stall angle of attack correction value. max : α max =α maxb +△α max ； In step S2, the first interpolation parameter CAB1 is determined by the following formula: ； When M a <1 hour, , when M a ≥1, ,in, is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number; The second interpolation parameter CAB2 is determined by the following formula: 。 2. The method for determining the stall angle of attack of a low aspect ratio wing according to claim 1, wherein: In step S4, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table. The fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2, and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is Mach number M a , the second interpolation parameter CAB2 and the stall angle correction value △α max Constructed 2D interpolation; When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value is interpolated using the fourth ASH interpolation table. △α max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value △α is interpolated using the fourth Mach number interpolation table. max ; in, .

3. A device for determining the stall angle of attack of a low aspect ratio wing, characterized in that: include: A correction coefficient interpolation module is used to interpolate a first correction coefficient C1 and a second correction coefficient C2 in a first interpolation table and a second interpolation table according to the wing tip root ratio λ; an interpolation parameter calculation module, configured to determine a first interpolation parameter CAB1 according to a first correction coefficient, and to determine a second interpolation parameter CAB2 according to a second correction coefficient; The wing stall angle of attack basic value determination module is used to determine the wing stall angle of attack basic value α in the third interpolation table according to the first interpolation parameter CAB1 maxb ; A stall angle correction value determination module is used to determine the stall angle correction value Δα in the fourth interpolation table according to the second interpolation parameter CAB2 max ; The stall angle determination module is used to determine the stall angle α based on the wing stall angle basic value and the stall angle correction value. max : α max =α maxb +△α max ； Wherein, in the interpolation parameter calculation module, the first interpolation parameter CAB1 is determined by the following formula: ； When M a <1 hour, , when M a ≥1, ,in, is the leading edge sweep angle, AR is the aspect ratio, M a is the flight Mach number; The second interpolation parameter CAB2 is determined by the following formula: 。 4. The low aspect ratio wing stall angle determination device according to claim 3, characterized in that: In the stall angle correction value determination module, the fourth interpolation table includes a fourth ASH interpolation table and a fourth Mach number interpolation table. The fourth ASH interpolation table is a parameter ASH, a second interpolation parameter CAB2 and a stall angle correction value Δα. max The constructed two-dimensional interpolation table, the fourth Mach number interpolation table is Mach number M a , the second interpolation parameter CAB2 and the stall angle correction value △α max Constructed two-dimensional interpolation table; When the second interpolation parameter CAB2 does not exceed 4.2, the stall angle correction value is interpolated using the fourth ASH interpolation table. △α max When the second interpolation parameter CAB2 exceeds 4.2, the stall angle correction value △α is interpolated using the fourth Mach number interpolation table. max ; in, .

5. A computer device, characterized in that: The method comprises 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 determining the stall angle of attack of a low aspect ratio wing according to any one of claims 1 to 2.

6. A readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is used to implement the method for determining the stall angle of attack of a low aspect ratio wing according to any one of claims 1 to 2.

Images