Methods, devices, equipment, and media for determining the aerodynamic characteristics of aircraft

Abstract

This application provides a method, apparatus, device, and medium for determining aerodynamic characteristic parameters of an aircraft, relating to the field of data processing technology. The method acquires multiple airfoil parameter sets, as well as the airfoil shape parameters and control parameters of the aircraft under test. Based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set, it determines the target airfoil parameter set corresponding to the aircraft under test. Based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset, it determines a reference subset from the multiple target airfoil parameter subsets. Based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, it determines the aerodynamic characteristic parameters of the aircraft under test. By finding a similar reference subset from multiple known airfoil parameter sets and obtaining the aerodynamic characteristic parameters of the aircraft under test from the reference subset, the efficiency of determining the aerodynamic characteristic parameters of an aircraft can be improved.

Description

Technical Field

[0001] This application relates to the field of data processing technology, specifically to a method, apparatus, equipment, and medium for determining aerodynamic characteristic parameters of an aircraft. Background Technology

[0002] Evaluating the aerodynamic benefits of plasma active flow control (PAFC) is an important research topic in aerospace, automotive, and other fluid dynamics-related fields. Assessing the aerodynamic benefits of PAFC helps improve aircraft performance. By optimizing aerodynamic performance, reducing energy consumption, simplifying structures, and adapting to future design requirements, plasma control technology has broad application prospects in the aerospace field.

[0003] Currently, there are two main methods for evaluating the aerodynamic benefits of plasma active flow control during the conceptual design phase of aircraft: (1) analysis through computational fluid dynamics (CFD); and (2) experiments through wind tunnel testing. However, both methods require a defined aircraft aerodynamic layout as input. Once the aircraft aerodynamic layout is modified, the mesh must be redesigned to conduct a new round of CFD calculations, and the aircraft model must be reworked to conduct a new round of wind tunnel tests. The time and economic costs of iterative optimization design of the aircraft layout are extremely high. Summary of the Invention

[0004] This application provides a method, apparatus, equipment, and medium for determining the aerodynamic characteristic parameters of an aircraft, which can determine the aerodynamic characteristic parameters of an aircraft, reduce costs, and increase the speed of determining the aerodynamic characteristic parameters of an aircraft.

[0005] This application provides a method for determining the aerodynamic characteristic parameters of an aircraft, including:

[0006] Multiple airfoil parameter sets are acquired, along with the wing shape parameters and control parameters of the aircraft under test. Each airfoil parameter set corresponds to a wingspan range, and the wingspan ranges corresponding to each airfoil parameter set are different. Each airfoil parameter set includes at least two airfoil parameter subsets, and each airfoil parameter subset corresponds to different wing shape parameters. Each airfoil parameter subset includes the correspondence between control parameters and aerodynamic characteristic parameters.

[0007] Based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set, the target airfoil parameter set corresponding to the aircraft under test is determined.

[0008] Based on the wing shape parameters of the aircraft under test and the wing shape parameters of the target airfoil parameter subset, a reference subset is determined from multiple target airfoil parameter subsets; the target airfoil parameter subset is the airfoil parameter subset of the target airfoil parameter set.

[0009] Based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, the aerodynamic characteristic parameters of the aircraft under test are determined.

[0010] In one embodiment of this application, determining the target airfoil parameter set corresponding to the aircraft under test based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set includes:

[0011] When the wingspan of the aircraft under test belongs to the target wingspan range, the set of airfoil parameters corresponding to the target wingspan range is determined as the target airfoil parameter set;

[0012] When the wingspan of the aircraft under test does not belong to any wingspan range, and the wingspan of the aircraft under test is located between two wingspan ranges, the set of airfoil parameters corresponding to the two wingspan ranges is determined as the target airfoil parameter set.

[0013] In one embodiment of this application, a reference subset is determined from multiple subsets of target airfoil parameters based on the wing shape parameters of the aircraft under test and the wing shape parameters of a subset of target airfoil parameters, including:

[0014] Based on the airfoil shape parameters of each target airfoil subset and the airfoil shape parameters of the aircraft under test, determine the parametric distance between each target airfoil subset and the aircraft under test;

[0015] If a target airfoil parameter set exists, then the subset of target airfoil parameters corresponding to the minimum and second minimum parameter distances is determined as the reference subset;

[0016] If there are two sets of target airfoil parameters, then the subset of target airfoil parameters corresponding to the minimum parameter distance in each set is determined as the reference subset.

[0017] In one embodiment of this application, the airfoil shape parameters include aspect ratio, sweep angle, and taper ratio. Determining the parametric distance between each target airfoil subset and the aircraft under test based on the airfoil shape parameters of each target airfoil subset and the aircraft under test includes:

[0018] For any subset of target airfoils: determine the aspect ratio difference, sweep angle difference, and taper ratio difference between the subset of target airfoils and the aircraft under test, and determine the parameter distance based on the aspect ratio difference, sweep angle difference, and taper ratio difference.

[0019] In one embodiment of this application, the control parameters include flight parameters and plasma-induced momentum coefficient. Based on the correspondence between the control parameters of the spacecraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, the aerodynamic characteristic parameters of the spacecraft under test are determined, including:

[0020] For any reference subset: Based on the reference subset and the flight parameters of the aircraft under test, determine the first aerodynamic characteristic parameter when no plasma flow control measures are applied; based on the reference subset, the flight parameters of the aircraft under test, and the plasma-induced momentum coefficient, determine the second aerodynamic characteristic parameter; based on the second aerodynamic characteristic parameter and the first aerodynamic characteristic parameter, determine the parameter increment; the plasma-induced momentum coefficient is 0 when no plasma flow control measures are applied; the flight parameters include the incoming Mach number, angle of attack, and control surface deflection angle;

[0021] The aerodynamic characteristic parameter increments are determined based on the parameter increments corresponding to each reference subset and the parameter distances between each reference subset and the aircraft under test.

[0022] The aerodynamic characteristic parameters of the test vehicle are determined based on the aerodynamic characteristic parameter increments and the initial aerodynamic characteristic parameters of the test vehicle when no plasma flow control measures are applied.

[0023] In one embodiment of this application, the aerodynamic characteristic parameter increment is determined based on the parameter increment corresponding to each of the reference subsets and the parameter distance between each reference subset and the aircraft under test, including:

[0024] The first weighting value and the second weighting value are determined based on the parameter distance between each reference subset and the aircraft under test;

[0025] The aerodynamic characteristic parameter increment is determined based on the first weighted value, the second weighted value, and the parameter increment corresponding to each of the reference subsets.

[0026] In one embodiment of this application, the aerodynamic characteristic parameters include lift coefficient, drag coefficient, pitching moment coefficient, side force coefficient, roll moment coefficient, and yaw moment coefficient.

[0027] To achieve the above and other related objectives, this application provides an apparatus for determining the aerodynamic characteristic parameters of an aircraft, comprising:

[0028] The data acquisition module is used to acquire multiple airfoil parameter sets, as well as the wing shape parameters and control parameters of the aircraft under test; each airfoil parameter set corresponds to a wingspan range, and the wingspan ranges corresponding to each airfoil parameter set are different. Each airfoil parameter set includes at least two airfoil parameter subsets, each airfoil parameter subset corresponds to different wing shape parameters, and each airfoil parameter subset includes the correspondence between control parameters and aerodynamic characteristic parameters.

[0029] The set determination module is used to determine the target airfoil parameter set corresponding to the aircraft under test based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set;

[0030] The subset determination module is used to determine a reference subset from multiple target airfoil parameter subsets based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset; the target airfoil parameter subset is the airfoil parameter subset of the target airfoil parameter set;

[0031] The parameter determination module is used to determine the aerodynamic characteristic parameters of the aircraft under test based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset.

[0032] To achieve the above and other related objectives, this application also provides an electronic device, the electronic device comprising:

[0033] One or more processors;

[0034] Memory used to store the executable program code of the processor;

[0035] The processor is configured to execute the program code to implement the above-described method for determining the aerodynamic characteristic parameters of an aircraft.

[0036] To achieve the above and other related objectives, this application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a computer processor, causes the computer to perform one or more of the aforementioned methods for determining aerodynamic characteristic parameters of an aircraft.

[0037] As described above, the method, apparatus, equipment, and medium for determining the aerodynamic characteristic parameters of an aircraft provided in this application have the following beneficial effects:

[0038] This application discloses a method for determining aerodynamic characteristic parameters of an aircraft. This method acquires multiple airfoil parameter sets, along with the airfoil shape parameters and control parameters of the aircraft under test. Based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set, a target airfoil parameter set corresponding to the aircraft under test is determined. Based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset, a reference subset is determined from the multiple target airfoil parameter subsets. Based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, the aerodynamic characteristic parameters of the aircraft under test are determined. By finding a similar reference subset from multiple known airfoil parameter sets and obtaining the aerodynamic characteristic parameters of the aircraft under test from the reference subset, the efficiency of determining the aerodynamic characteristic parameters of the aircraft can be improved.

[0039] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0040] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings:

[0041] Figure 1 This is a flowchart illustrating a method for determining aerodynamic characteristic parameters of an aircraft, as shown in an exemplary embodiment of this application;

[0042] Figure 2 This is a schematic diagram illustrating the set of target airfoil parameters in an exemplary embodiment of this application;

[0043] Figure 3 This is a schematic diagram illustrating the target airfoil parameter set, as shown in another exemplary embodiment of this application;

[0044] Figure 4 This is a structural block diagram of an aircraft aerodynamic characteristic parameter determination device, as illustrated in an exemplary embodiment of this application. Detailed Implementation

[0045] The embodiments of this application will be described below with reference to the accompanying drawings and preferred embodiments. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. This application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be understood that the preferred embodiments are only for illustrating this application and are not intended to limit the scope of protection of this application.

[0046] It should be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. Therefore, the drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0047] In the following description, numerous details are explored to provide a more thorough explanation of embodiments of the present application. However, it will be apparent to those skilled in the art that embodiments of the present application may be practiced without these specific details. In other embodiments, well-known structures and devices are shown in block diagram form rather than in detail to avoid obscuring embodiments of the present application.

[0048] Please see Figure 1 , Figure 1 This is a flowchart illustrating a method for determining aerodynamic characteristic parameters of an aircraft, as shown in an exemplary embodiment of this application. (Reference) Figure 1 It can be seen that the method for determining the aerodynamic characteristic parameters of this aircraft may include:

[0049] Step S110: Obtain multiple airfoil parameter sets, as well as the wing surface shape parameters and control parameters of the aircraft under test.

[0050] Each airfoil parameter set corresponds to a wingspan range, and the wingspan ranges corresponding to each airfoil parameter set are different. Each airfoil parameter set includes at least two airfoil parameter subsets, and each airfoil parameter subset corresponds to different airfoil shape parameters. Each airfoil parameter subset includes the correspondence between control parameters and aerodynamic characteristic parameters.

[0051] In one embodiment of this application, when determining the aerodynamic characteristic parameters of an aircraft, multiple airfoil parameter sets, as well as the wing shape parameters and control parameters of the aircraft under test, can be obtained first. Designers can pre-determine multiple airfoil parameter sets based on known typical aircraft configurations. Each aircraft configuration corresponds to a wing shape parameter; that is, a corresponding subset of airfoil parameters can be determined based on different aircraft configurations. Each airfoil parameter set corresponds to a wingspan range, and this airfoil parameter set can include multiple known typical aircraft configurations corresponding to airfoil parameter subsets. The wingspan corresponding to each airfoil parameter subset belongs to the corresponding wingspan range. The aerodynamic characteristic parameters of each known typical aircraft configuration are calibrated under different control parameters to obtain each airfoil parameter subset. A typical aircraft configuration can include the arrangement of major components such as wings, engines, and tail fins.

[0052] It should be noted that the wing shape parameters may include aspect ratio, sweep angle, and taper ratio, and the control parameters may include flight parameters and plasma-induced momentum coefficient. The flight parameters may include incoming Mach number, angle of attack, and control surface deflection angle.

[0053] For example, the division of wingspan ranges can be based on different aircraft models. For instance, three wingspan ranges can be defined: a large aircraft wingspan range, a medium aircraft wingspan range, and a small aircraft wingspan range. The small aircraft wingspan range can be... The wingspan range of a medium-sized aircraft can be The wingspan range of large aircraft can be Other wingspan ranges can also be set based on the wingspan of known typical aircraft configurations.

[0054] Step S120: Determine the target airfoil parameter set corresponding to the aircraft under test based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set.

[0055] In one embodiment of this application, the target airfoil parameter set corresponding to the aircraft under test can be determined based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set. After determining the target airfoil parameter set, the aerodynamic characteristic parameters of the aircraft can be determined based on each subset of airfoil parameters in the target airfoil parameter set.

[0056] For example, the airfoil parameter set may include three sets, each corresponding to a wingspan range of a large aircraft, a medium aircraft, and a small aircraft, respectively. The wingspan of the aircraft under test can be classified into five categories: the wingspan of the aircraft under test belongs to the small aircraft wingspan range; the wingspan of the aircraft under test is located between the small and medium aircraft wingspan ranges; the wingspan of the aircraft under test belongs to the medium aircraft wingspan range; the wingspan of the aircraft under test is located between the medium and large aircraft wingspan ranges; and the wingspan of the aircraft under test belongs to the large aircraft wingspan range.

[0057] Step S130: Determine a reference subset from multiple target airfoil parameter subsets based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset.

[0058] The target airfoil parameter subset is a subset of the airfoil parameters of the target airfoil parameter set.

[0059] In one embodiment of this application, a reference subset can be determined from multiple subsets of target airfoil parameters based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset. The reference subset is the subset of all target airfoil parameter subsets that most closely resembles the aerodynamic characteristic parameters of the aircraft under test.

[0060] Step S140: Determine the aerodynamic characteristic parameters of the aircraft under test based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset.

[0061] In one embodiment of this application, the aerodynamic characteristic parameters of the aircraft under test can be determined based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset.

[0062] It should be noted that each step in the method for determining the aerodynamic characteristic parameters of an aircraft provided in this application embodiment can be executed by a terminal, a server, or a server cluster.

[0063] In one embodiment, step S120, which determines the target airfoil parameter set corresponding to the aircraft under test based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set, may include steps S121 and S122.

[0064] Step S121: When the wingspan of the aircraft under test belongs to the target wingspan range, the set of airfoil parameters corresponding to the target wingspan range is determined as the target airfoil parameter set.

[0065] In one embodiment of this application, when the wingspan of the aircraft under test belongs to the target wingspan range, the set of airfoil parameters corresponding to the target wingspan range can be determined as the target airfoil parameter set.

[0066] For example, the wingspan ranges are the wingspan ranges for large aircraft, medium aircraft, and small aircraft. The cases where the wingspan of the aircraft under test falls within the target wingspan range include: the wingspan of the aircraft under test falling within the small aircraft wingspan range, the wingspan of the aircraft under test falling within the medium aircraft wingspan range, and the wingspan of the aircraft under test falling within the large aircraft wingspan range.

[0067] Step S122: When the wingspan of the aircraft under test does not belong to any wingspan range, and the wingspan of the aircraft under test is located between two wingspan ranges, the set of airfoil parameters corresponding to the two wingspan ranges is determined as the target airfoil parameter set.

[0068] In one embodiment of this application, when the wingspan of the aircraft under test does not belong to any wingspan range and the wingspan of the aircraft under test is located between two wingspan ranges, the set of airfoil parameters corresponding to the two wingspan ranges can be determined as the target airfoil parameter set.

[0069] For example, the wingspan ranges are the wingspan ranges for large aircraft, medium aircraft, and small aircraft. The case where the wingspan of the aircraft under test does not belong to any of the wingspan ranges, and the wingspan of the aircraft under test is located between two wingspan ranges, can include: the wingspan of the aircraft under test being located between the wingspan ranges for small and medium aircraft, or the wingspan of the aircraft under test being located between the wingspan ranges for medium and large aircraft.

[0070] In one embodiment, step S130, which involves determining a reference subset from multiple target airfoil parameter subsets based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset, may include steps S131 to S133.

[0071] Step S131: Determine the parameter distance between each target airfoil subset and the aircraft under test based on the airfoil shape parameters of each target airfoil subset and the airfoil shape parameters of the aircraft under test.

[0072] In one embodiment of this application, the parametric distance between each target airfoil subset and the aircraft under test can be determined based on the airfoil shape parameters of each target airfoil subset and the airfoil shape parameters of the aircraft under test.

[0073] In one embodiment, the airfoil shape parameters include aspect ratio, sweep angle, and taper ratio. Based on the airfoil shape parameters of each target airfoil subset and the airfoil shape parameters of the aircraft under test, the parametric distance between each target airfoil subset and the aircraft under test is determined. This includes: for any target airfoil subset: determining the difference in aspect ratio, sweep angle, and taper ratio between the target airfoil subset and the aircraft under test, and determining the parametric distance based on these differences. The parametric distance can characterize the degree of similarity between the airfoil of the aircraft under test and the corresponding airfoil of the target airfoil subset.

[0074] For example, the formula for determining the parameter distance may include:

[0075] ;

[0076] in, Indicates the first The parameter distance of a subset of target airfoils Indicates the first The difference in aspect ratio between a subset of target airfoils and the aircraft under test Indicates the first The difference in sweep angle between a subset of target airfoils and the aircraft under test Indicates the first The difference in the taper ratio between a subset of target airfoils and the aircraft under test This indicates the number of target airfoil subsets.

[0077] It should be noted that aspect ratio, sweep angle, and taper ratio are basic aerodynamic layout characteristic parameters of an aircraft. In other words, once the aspect ratio, sweep angle, and taper ratio are determined, the different types of aircraft and their appearance can be determined.

[0078] Step S132: If there is a target airfoil parameter set, then the subset of target airfoil parameters corresponding to the minimum and second minimum parameter distances are determined as the reference subset.

[0079] In one embodiment of this application, the number of reference subsets can be two. After sorting the parameter distances, the target airfoil parameter subsets corresponding to the minimum and second minimum parameter distances can be determined as the reference subsets. The second minimum value is the second smallest value among the parameter distances.

[0080] For example, please refer to Figure 2 This is a schematic diagram illustrating a target airfoil parameter set, as shown in an exemplary embodiment of this application. Indicates the aspect ratio. Indicates the sweep angle. Indicates the tapering ratio, The symbol represents the set of target airfoil parameters. The circle represents the airfoil shape parameters of a subset of the target airfoil, and the star represents the airfoil shape parameters of the aircraft under test. Indicates the first The parameter distance of a subset of target airfoils ( (You can choose) and The corresponding subset of target airfoil parameters is the baseline subset.

[0081] Step S133: If there are two sets of target airfoil parameters, then the subset of target airfoil parameters corresponding to the minimum parameter distance in each set is determined as the reference subset.

[0082] In one embodiment of this application, if there are two sets of target airfoil parameters, each subset of the target airfoil in each set can determine a parameter distance with the aircraft under test. In this case, the subset of target airfoil parameters corresponding to the minimum parameter distance among the parameter distances of each set of target airfoil parameters can be determined as a reference subset. That is, a reference subset can be determined in each of the two sets of target airfoil parameters. The total number of reference subsets is 2.

[0083] For example, please refer to Figure 3 This is a schematic diagram illustrating the target airfoil parameter set, as shown in another exemplary embodiment of this application. Indicates the aspect ratio. Indicates the sweep angle. Indicates the tapering ratio, , The symbol represents the set of target airfoil parameters. The circle represents the airfoil shape parameters of a subset of the target airfoil, and the star represents the airfoil shape parameters of the aircraft under test. Indicates the first The parameter distance of a subset of target airfoils ( (You can choose) and The corresponding subset of target airfoil parameters is the baseline subset.

[0084] In one embodiment, the control parameters include flight parameters and plasma-induced momentum coefficient. Step S140, which determines the aerodynamic characteristic parameters of the aircraft under test based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, may include steps S141 to S143.

[0085] Step S141: For any reference subset: Based on the reference subset and the flight parameters of the aircraft under test, determine the first aerodynamic characteristic parameter when no plasma flow control measures are applied; Based on the reference subset, the flight parameters of the aircraft under test, and the plasma induced momentum coefficient, determine the second aerodynamic characteristic parameter; Based on the second aerodynamic characteristic parameter and the first aerodynamic characteristic parameter, determine the parameter increment.

[0086] When no plasma flow control measures are applied, the plasma-induced momentum coefficient is 0; the flight parameters include the incoming Mach number, angle of attack, and control surface deflection angle.

[0087] In one embodiment of this application, for any reference subset: based on the flight parameters of the aircraft under test, interpolation and table lookup are performed in the reference subset to determine the first aerodynamic characteristic parameter when the plasma-induced momentum coefficient is 0. Then, based on the reference subset, the flight parameters of the aircraft under test, and the plasma-induced momentum coefficient, interpolation and table lookup are performed in the reference subset to determine the second aerodynamic characteristic parameter. The difference between the second aerodynamic characteristic parameter and the first aerodynamic characteristic parameter can be determined as the parameter increment.

[0088] For example, aerodynamic characteristic parameters may include lift coefficient, drag coefficient, pitching moment coefficient, side force coefficient, roll moment coefficient, and yaw moment coefficient. Correspondingly, parameter increments may also include increments in lift coefficient, drag coefficient, pitching moment coefficient, side force coefficient, roll moment coefficient, and yaw moment coefficient. The parameter increments corresponding to each benchmark subset can be characterized as... , ,in, Indicates the application of plasma flow control measures. Aerodynamic characteristic parameters corresponding to each reference subset Indicates the situation when no plasma flow control measures are applied. Aerodynamic characteristic parameters corresponding to a subset of references.

[0089] Specifically:

[0090] ;

[0091] in, Indicates the first The lift coefficient increment corresponding to each reference subset Indicates the application of plasma flow control measures. The lift coefficients corresponding to each reference subset Indicates the situation when no plasma flow control measures are applied. The lift coefficients corresponding to each reference subset;

[0092] ;

[0093] in, Indicates the first The drag coefficient increment corresponding to each benchmark subset Indicates the application of plasma flow control measures. The drag coefficient corresponding to each benchmark subset Indicates the situation when no plasma flow control measures are applied. The drag coefficients corresponding to each benchmark subset;

[0094] ;

[0095] in, Indicates the first The pitch moment coefficient increment corresponding to each reference subset Indicates the application of plasma flow control measures. Pitch moment coefficients corresponding to each reference subset Indicates the situation when no plasma flow control measures are applied. Pitch moment coefficients corresponding to each reference subset;

[0096] ;

[0097] in, Indicates the first The side force coefficient increments corresponding to each reference subset Indicates the application of plasma flow control measures. Side force coefficients corresponding to each reference subset Indicates the situation when no plasma flow control measures are applied. Side force coefficients corresponding to each reference subset;

[0098] ;

[0099] in, Indicates the first The increment of the rolling moment coefficient corresponding to each reference subset Indicates the application of plasma flow control measures. Rolling moment coefficients corresponding to each reference subset Indicates the situation when no plasma flow control measures are applied. Rolling moment coefficients corresponding to each reference subset;

[0100] ;

[0101] in, Indicates the first The yaw moment coefficient increment corresponding to each reference subset Indicates the application of plasma flow control measures. Yaw moment coefficients corresponding to each reference subset Indicates the situation when no plasma flow control measures are applied. Yaw moment coefficients corresponding to each reference subset.

[0102] Step S142: Determine the aerodynamic characteristic parameter increments based on the parameter increments corresponding to each reference subset and the parameter distances between each reference subset and the aircraft under test.

[0103] In one embodiment of this application, the aerodynamic characteristic parameter increment can be determined based on the parameter increment corresponding to each reference subset and the parameter distance between each reference subset and the aircraft under test.

[0104] In one embodiment, step S142 may include: determining a first weighting value and a second weighting value based on the parameter distance between each reference subset and the aircraft under test; and determining the aerodynamic characteristic parameter increment based on the first weighting value, the second weighting value, and the parameter increment corresponding to each reference subset.

[0105] For example, the formula for determining the first weighting value may include:

[0106] ;

[0107] in, Indicates the first weighted value. This represents the parametric distance between the first reference subset and the aircraft under test. Indicates the first The parameter distance between a reference subset and the aircraft under test.

[0108] For example, the formula for determining the second weighting value may include:

[0109] ;

[0110] in, This represents the second weighted value. This represents the parametric distance between the second reference subset and the aircraft under test.

[0111] For example, the formula for determining the increment of aerodynamic characteristic parameters may include:

[0112] ;

[0113] in, This represents the increment of aerodynamic characteristic parameters. This represents the parameter increment corresponding to the first baseline subset. This represents the parameter increment corresponding to the second baseline subset.

[0114] Step S143: Determine the aerodynamic characteristic parameters of the test vehicle based on the aerodynamic characteristic parameter increments and the initial aerodynamic characteristic parameters of the test vehicle when no plasma flow control measures are applied.

[0115] In one embodiment of this application, the aerodynamic characteristics of the aircraft under test (AUT) can be determined based on the aerodynamic characteristic parameter increments and the initial aerodynamic characteristic parameters of the AUT without plasma flow control measures. The sum of the aerodynamic characteristic parameter increments and the initial aerodynamic characteristic parameters can be used to determine the aerodynamic characteristic parameters of the AUT. Designers can pre-determine the initial aerodynamic characteristic parameters of the AUT without plasma flow control measures.

[0116] It should be noted that the method for determining aerodynamic characteristic parameters of aircraft provided in this application embodiment can easily determine the aerodynamic characteristic parameters under different design conditions when designing aircraft with different configurations. When changing the aerodynamic layout of the aircraft, it is not necessary to modify a new aircraft model for each aerodynamic layout design, which reduces the time for determining aerodynamic characteristic parameters and improves the efficiency of determining aerodynamic characteristic parameters.

[0117] Figure 4 This is a block diagram illustrating an aircraft aerodynamic characteristic parameter determination device, as shown in an exemplary embodiment of this application. Figure 4 As shown, the exemplary aircraft aerodynamic characteristic parameter determination device 400 includes:

[0118] The data acquisition module 410 is used to acquire multiple airfoil parameter sets, as well as the wing shape parameters and control parameters of the aircraft under test. Each airfoil parameter set corresponds to a wingspan range, and the wingspan ranges corresponding to each airfoil parameter set are different. Each airfoil parameter set includes at least two airfoil parameter subsets, and each airfoil parameter subset corresponds to different wing shape parameters. Each airfoil parameter subset includes the correspondence between control parameters and aerodynamic characteristic parameters.

[0119] The set determination module 420 is used to determine the target airfoil parameter set corresponding to the aircraft under test based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set.

[0120] The subset determination module 430 is used to determine a reference subset from multiple target airfoil parameter subsets based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset; the target airfoil parameter subset is a subset of the airfoil parameters of the target airfoil parameter set.

[0121] The parameter determination module 440 is used to determine the aerodynamic characteristic parameters of the aircraft under test based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset.

[0122] It should be noted that the aerodynamic characteristic parameter determination device for aircraft provided in the above embodiments and the aerodynamic characteristic parameter determination method for aircraft provided in the above embodiments belong to the same concept. The specific operation methods of each module and unit have been described in detail in the method embodiments and will not be repeated here. In practical applications, the aerodynamic characteristic parameter determination device for aircraft provided in the above embodiments can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above. This is not a limitation here.

[0123] Embodiments of this application also provide an electronic device, including: one or more processors; and a storage device for storing one or more programs, which, when executed by one or more processors, cause the electronic device to implement the aircraft aerodynamic characteristic parameter determination method provided in the above embodiments.

[0124] Another aspect of this application provides a computer-readable storage medium storing a computer program thereon, which, when executed by a computer's processor, causes the computer to perform the aircraft aerodynamic characteristic parameter determination method provided in the above embodiments. This computer-readable storage medium may be included in the electronic device described in the above embodiments, or it may exist independently and not incorporated into the electronic device.

[0125] Another aspect of this application provides a computer program product or computer program including computer instructions stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium and executes the computer instructions, causing the computer device to perform the aircraft aerodynamic characteristic parameter determination method provided in the various embodiments described above.

[0126] In the embodiments of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The terms "comprising" and "including" as used throughout the specification and claims are open-ended terms and should therefore be interpreted as "comprising but not limited to".

[0127] The above embodiments are merely illustrative of the principles and effects of this application and are not intended to limit this application. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this application should still be covered by the claims of this application.

Claims

1. A method for determining aerodynamic characteristic parameters of an aircraft, characterized in that, include: Multiple airfoil parameter sets are acquired, along with the wing shape parameters and control parameters of the aircraft under test. Each airfoil parameter set corresponds to a wingspan range, and the wingspan ranges corresponding to each airfoil parameter set are different. Each airfoil parameter set includes at least two airfoil parameter subsets, and each airfoil parameter subset corresponds to different wing shape parameters. Each airfoil parameter subset includes the correspondence between control parameters and aerodynamic characteristic parameters. Based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set, the target airfoil parameter set corresponding to the aircraft under test is determined. Based on the wing shape parameters of the aircraft under test and the wing shape parameters of the target airfoil parameter subset, a reference subset is determined from multiple target airfoil parameter subsets; The target airfoil parameter subset is a subset of the airfoil parameters of the target airfoil parameter set; Based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, the aerodynamic characteristic parameters of the aircraft under test are determined.

2. The method for determining the aerodynamic characteristic parameters of an aircraft according to claim 1, characterized in that, Based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set, the target airfoil parameter set corresponding to the aircraft under test is determined, including: When the wingspan of the aircraft under test belongs to the target wingspan range, the set of airfoil parameters corresponding to the target wingspan range is determined as the target airfoil parameter set; When the wingspan of the aircraft under test does not belong to any wingspan range, and the wingspan of the aircraft under test is located between two wingspan ranges, the set of airfoil parameters corresponding to the two wingspan ranges is determined as the target airfoil parameter set.

3. The method for determining the aerodynamic characteristic parameters of an aircraft according to claim 2, characterized in that, Based on the wing shape parameters of the aircraft under test and the wing shape parameters of the target airfoil parameter subset, a reference subset is determined from multiple target airfoil parameter subsets, including: Based on the airfoil shape parameters of each target airfoil subset and the airfoil shape parameters of the aircraft under test, determine the parametric distance between each target airfoil subset and the aircraft under test; If a target airfoil parameter set exists, then the subset of target airfoil parameters corresponding to the minimum and second minimum parameter distances is determined as the reference subset; If there are two sets of target airfoil parameters, then the subset of target airfoil parameters corresponding to the minimum parameter distance in each set is determined as the reference subset.

4. The method for determining the aerodynamic characteristic parameters of an aircraft according to claim 3, characterized in that, The airfoil shape parameters include aspect ratio, sweep angle, and taper ratio. Based on the airfoil shape parameters of each target airfoil subset and the airfoil shape parameters of the aircraft under test, the parametric distances between each target airfoil subset and the aircraft under test are determined, including: For any subset of target airfoils: determine the aspect ratio difference, sweep angle difference, and taper ratio difference between the subset of target airfoils and the aircraft under test, and determine the parameter distance based on the aspect ratio difference, sweep angle difference, and taper ratio difference.

5. The method for determining the aerodynamic characteristic parameters of an aircraft according to claim 3, characterized in that, The control parameters include flight parameters and plasma-induced momentum coefficient. Based on the correspondence between the control parameters of the spacecraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset, the aerodynamic characteristic parameters of the spacecraft under test are determined, including: For any reference subset: Based on the reference subset and the flight parameters of the aircraft under test, determine the first aerodynamic characteristic parameter when no plasma flow control measures are applied; based on the reference subset, the flight parameters of the aircraft under test, and the plasma-induced momentum coefficient, determine the second aerodynamic characteristic parameter; based on the second aerodynamic characteristic parameter and the first aerodynamic characteristic parameter, determine the parameter increment; the plasma-induced momentum coefficient is 0 when no plasma flow control measures are applied; the flight parameters include the incoming Mach number, angle of attack, and control surface deflection angle; The aerodynamic characteristic parameter increments are determined based on the parameter increments corresponding to each reference subset and the parameter distances between each reference subset and the aircraft under test. The aerodynamic characteristic parameters of the test vehicle are determined based on the aerodynamic characteristic parameter increments and the initial aerodynamic characteristic parameters of the test vehicle when no plasma flow control measures are applied.

6. The method for determining the aerodynamic characteristic parameters of an aircraft according to claim 5, characterized in that, Based on the parameter increments corresponding to each of the aforementioned reference subsets and the parameter distances between each reference subset and the aircraft under test, the aerodynamic characteristic parameter increments are determined, including: The first weighting value and the second weighting value are determined based on the parameter distance between each reference subset and the aircraft under test; The aerodynamic characteristic parameter increment is determined based on the first weighted value, the second weighted value, and the parameter increment corresponding to each of the reference subsets.

7. The method for determining the aerodynamic characteristic parameters of an aircraft according to any one of claims 1 to 6, characterized in that, The aerodynamic characteristic parameters include lift coefficient, drag coefficient, pitching moment coefficient, side force coefficient, roll moment coefficient, and yaw moment coefficient.

8. A device for determining aerodynamic characteristic parameters of an aircraft, characterized in that, include: The data acquisition module is used to acquire multiple airfoil parameter sets, as well as the wing shape parameters and control parameters of the aircraft under test; each airfoil parameter set corresponds to a wingspan range, and the wingspan ranges corresponding to each airfoil parameter set are different. Each airfoil parameter set includes at least two airfoil parameter subsets, each airfoil parameter subset corresponds to different wing shape parameters, and each airfoil parameter subset includes the correspondence between control parameters and aerodynamic characteristic parameters. The set determination module is used to determine the target airfoil parameter set corresponding to the aircraft under test based on the wingspan of the aircraft under test and the wingspan range of each airfoil parameter set; The subset determination module is used to determine a reference subset from multiple target airfoil parameter subsets based on the airfoil shape parameters of the aircraft under test and the airfoil shape parameters of the target airfoil parameter subset; The target airfoil parameter subset is a subset of the airfoil parameters of the target airfoil parameter set; The parameter determination module is used to determine the aerodynamic characteristic parameters of the aircraft under test based on the correspondence between the control parameters of the aircraft under test and the control parameters and aerodynamic characteristic parameters in the reference subset.

9. An electronic device, characterized in that, The electronic device includes: One or more processors; Memory used to store the executable program code of the processor; The processor is configured to execute the program code to implement the method for determining aerodynamic characteristic parameters of an aircraft as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, It stores a computer program, which, when executed by the computer's processor, causes the computer to perform the method for determining the aerodynamic characteristic parameters of an aircraft as described in any one of claims 1 to 7.

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