Method, device, equipment and storage medium for quickly generating aerodynamic data of a body of revolution aircraft

Abstract

The present application discloses a method, device, equipment and storage medium for quickly generating aerodynamic data of a body of revolution aircraft, relating to the technical field of aircraft aerodynamic characteristic calculation, including: selecting a reference configuration aircraft with a body of revolution and an X-type tail rudder from a preset aerodynamic database based on the target user requirements, and determining the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated; determining the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the non-rudder deflection state based on the first aerodynamic data, and changing the body of revolution in the reference configuration aircraft into the body of revolution to be detected to obtain the target aircraft to be detected; simulating the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the non-rudder deflection state, and determining the target aerodynamic data in the flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data. In this way, the prediction efficiency of the aerodynamic characteristics of the body of revolution aircraft can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft aerodynamic characteristic calculation, and particularly to a method, device, equipment and storage medium for quickly generating aerodynamic data of a body of revolution aircraft. Background Art

[0002] The body of revolution and the X-type tail rudder configuration are one of the main configurations of aircraft. Quickly and accurately obtaining aerodynamic characteristic data under different flight states is of great significance for the flight performance evaluation, design and research and development of aircraft with the body of revolution and X-type tail rudder configurations. Traditional methods for obtaining aircraft aerodynamic data include wind tunnel tests, flight tests, numerical calculations, engineering calculations, etc. Wind tunnel tests and flight tests are costly and have a long data acquisition cycle; numerical calculations can obtain relatively accurate data in a relatively short time, but they require a large amount of computing resources, and the calculation time still cannot meet the current demand for real-time acquisition of aerodynamic characteristic data; engineering calculation methods are fast, but the calculation accuracy cannot meet the requirements of aircraft design and evaluation. With the development of intelligent technology, prediction technologies based on artificial intelligence have been gradually developed. However, due to reasons such as complex configurations and multiple flight states of aircraft with the body of revolution and X-type tail rudder configurations, their data samples have high-dimensional non-linear characteristics, resulting in a large dependence on and demand for sample data by current artificial intelligence methods, high modeling costs, and the calculation costs of the required samples may also be unaffordable.

[0003] As can be seen from the above, for aircraft with the body of revolution and X-type tail rudder configurations, solving the problem of quickly generating aerodynamic data under limited computing resources and improving the prediction efficiency of the aerodynamic characteristics of the body of revolution and X-type tail rudder configurations are problems to be solved. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a method, device, equipment and storage medium for quickly generating aerodynamic data of a body of revolution aircraft, which can improve the prediction efficiency of the aerodynamic characteristics of the body of revolution aircraft. The specific solutions are as follows:

[0005] In the first aspect, the present application discloses a method for quickly generating aerodynamic data of a body of revolution aircraft, including:

[0006] Selecting a reference configuration aircraft with a body of revolution and an X-type tail rudder from a preset aerodynamic database based on the target user's needs, and determining the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated;

[0007] Determining the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the non-rudder deflection state in the flight state to be evaluated based on the first aerodynamic data, and changing the body of revolution in the reference configuration aircraft to a body of revolution to be detected to obtain a target aircraft to be detected;

[0008] Determine the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the state of no rudder deflection by using a preset numerical simulation method, and determine the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data.

[0009] Optionally, the determining the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated includes:

[0010] Determine the flight state to be evaluated and the target rudder deflection state based on the target user requirements, and obtain the first reference aerodynamic data corresponding to the reference configuration aircraft in the flight state to be evaluated and the target rudder deflection state from the preset aerodynamic database;

[0011] Obtain the second reference aerodynamic data corresponding to the reference configuration aircraft in the flight state to be evaluated and the state of no rudder deflection from the preset aerodynamic database.

[0012] Optionally, the flight state to be evaluated is determined by the flight Mach number, the flight angle of attack, and the flight sideslip angle; the target rudder deflection state is determined by the pitch rudder deflection angle, the yaw rudder deflection angle, and the roll rudder deflection angle; the aerodynamic data is six-component aerodynamic characteristic data, including: axial force coefficient, normal force coefficient, side force coefficient, roll moment, yaw moment, and pitch moment.

[0013] Optionally, the determining the corresponding aerodynamic data difference between the reference configuration aircraft in the flight state to be evaluated, the target rudder deflection state, and the state of no rudder deflection based on the first aerodynamic data includes:

[0014] Determine the aerodynamic data difference corresponding to the target rudder deflection angle difference based on the difference between the first reference aerodynamic data and the second reference aerodynamic data; the target rudder deflection angle difference is the difference in rudder deflection angles between the target rudder deflection state and the state of no rudder deflection.

[0015] Optionally, the using a preset numerical simulation method to determine the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the state of no rudder deflection includes:

[0016] Use pre-designed computational fluid dynamics software to simulate and calculate the six-component aerodynamic characteristic data of the target aircraft to be detected in the flight state to be evaluated and the state of no rudder deflection to obtain the second aerodynamic data.

[0017] Optionally, the determining the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data includes:

[0018] Substitute the pneumatic data difference and the second pneumatic data into a preset target pneumatic data calculation formula to obtain the target pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state; the target pneumatic data calculation formula is a summation formula constructed based on the pneumatic data difference and the second pneumatic data.

[0019] Optionally, after determining the target pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the pneumatic data difference and the second pneumatic data, the following is further included:

[0020] Based on pre-designed computational fluid dynamics software, calculate the third pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state, and determine whether the difference between the third pneumatic data and the target pneumatic data meets the preset data simulation conditions;

[0021] If the difference meets the preset data simulation conditions, it is determined that the target pneumatic data conforms to the preset aerodynamic data generation standard for axisymmetric bodies.

[0022] In a second aspect, the present application discloses a device for quickly generating aerodynamic data of an axisymmetric body aircraft, including:

[0023] A first pneumatic data determination module, configured to select a reference configuration aircraft with an axisymmetric body and an X-type tail rudder from a preset pneumatic database based on target user requirements, and determine the first pneumatic data of the reference configuration aircraft in the flight state to be evaluated;

[0024] A to-be-detected aircraft construction module, configured to determine the pneumatic data difference corresponding to the reference configuration aircraft in the flight state to be evaluated, between the target rudder deflection state and the non-rudder deflection state based on the first pneumatic data, and change the axisymmetric body in the reference configuration aircraft to a to-be-detected axisymmetric body to obtain a target aircraft to be detected;

[0025] A target pneumatic data generation module, configured to use a preset numerical simulation method to determine the second pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the non-rudder deflection state, and determine the target pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the pneumatic data difference and the second pneumatic data.

[0026] In a third aspect, the present application discloses an electronic device, including:

[0027] A memory, configured to store a computer program;

[0028] A processor, configured to execute the computer program to implement the foregoing method for quickly generating aerodynamic data of an axisymmetric body aircraft.

[0029] In a fourth aspect, the present application discloses a computer-readable storage medium for storing a computer program, which, when executed by a processor, implements the foregoing method for rapidly generating aerodynamic data of a body of revolution aircraft.

[0030] It can be seen that in the present application, a reference configuration aircraft with a body of revolution and an X-type tail rudder is selected from a preset aerodynamic database based on the target user's requirements, and the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated is determined; based on the first aerodynamic data, the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the non-rudder deflection state in the flight state to be evaluated is determined, and the body of revolution in the reference configuration aircraft is changed to the body of revolution to be detected to obtain the target aircraft to be detected; the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the non-rudder deflection state is determined by using a preset numerical simulation method, and the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state is determined according to the aerodynamic data difference and the second aerodynamic data. In this way, under the condition of obtaining a limited number of high-dimensional samples, based on the data in the reference configuration database, through extrapolation calculation, the aerodynamic data of the target aircraft to be detected corresponding to the new configuration can be rapidly generated. The aerodynamic data can be rapidly generated under the condition of limited computing resources, the prediction efficiency of the aerodynamic characteristics of the body of revolution and the X-type tail rudder configuration can be improved, and thus the design iteration cycle of this type of aircraft can be shortened. Description of the Drawings

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present invention, and those of ordinary skill in the art can also obtain other drawings according to the provided drawings without creative efforts.

[0032] Figure 1 It is a flowchart of a method for rapidly generating aerodynamic data of a body of revolution aircraft disclosed in the present application;

[0033] Figure 2 It is a schematic diagram of a reference configuration aircraft with a body of revolution and an X-type tail rudder disclosed in the present application;

[0034] Figure 3 It is a schematic diagram of a new configuration aircraft with a body of revolution and an X-type tail rudder disclosed in the present application;

[0035] Figure 4 It is a schematic diagram of the structure of a device for rapidly generating aerodynamic data of a body of revolution aircraft disclosed in the present application;

[0036] Figure 5 A structural diagram of an electronic device disclosed in this application. Specific implementation manners

[0037] Next, the technical solutions in the embodiments of this application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of this application.

[0038] With the development of intelligent technology, prediction technologies based on artificial intelligence have been gradually developed. However, due to the complex configuration and multiple flight states of vehicles with a body of revolution and an X-type tail rudder configuration, their data samples have high-dimensional non-linear characteristics, resulting in a large dependence on and high demand for sample data by current artificial intelligence methods, high modeling costs, and the computational costs of the required samples may also be unaffordable. Therefore, this application will specifically introduce a method for quickly generating aerodynamic data of a vehicle with a body of revolution, which can quickly generate aerodynamic data under the condition of limited computing resources.

[0039] See Figure 1 As shown, an embodiment of this application discloses a method for quickly generating aerodynamic data of a vehicle with a body of revolution, including:

[0040] Step S11: Select a reference configuration vehicle with a body of revolution and an X-type tail rudder from a preset aerodynamic database based on the target user's requirements, and determine the first aerodynamic data of the reference configuration vehicle in the flight state to be evaluated.

[0041] In this embodiment, the determination of the first aerodynamic data of the reference configuration vehicle in the flight state to be evaluated includes: determining the flight state to be evaluated and the target rudder deflection state based on the target user's requirements, and obtaining the first reference aerodynamic data of the reference configuration vehicle corresponding to the flight state to be evaluated and the target rudder deflection state from the preset aerodynamic database; obtaining the second reference aerodynamic data of the reference configuration vehicle corresponding to the flight state to be evaluated and the non-rudder deflection state from the preset aerodynamic database. Among them, the flight state to be evaluated is determined by the flight Mach number, flight angle of attack, and flight sideslip angle; the target rudder deflection state is determined by the pitch rudder deflection angle, yaw rudder deflection angle, and roll rudder deflection angle; the aerodynamic data is six-component aerodynamic characteristic data, including: axial force coefficient, normal force coefficient, side force coefficient, roll moment, yaw moment, and pitch moment. Specifically, from the existing aerodynamic database, according to the user's requirements, a vehicle with a body of revolution and an X-type tail rudder is selected as the reference configuration. In actual operation, it can be selected, for example Figure 2The reference configuration aircraft with a body of revolution and an X-type tail rudder is shown. Then, according to the user's requirements, the flight states and rudder deflection states to be evaluated for the new configuration are determined. Among them, a single flight state is determined by three parameters: flight Mach number Ma, flight angle of attack α, and flight sideslip angle β, and the rudder deflection state is jointly determined by three parameters: pitch rudder deflection angle Dz, yaw rudder deflection angle Dy, and roll rudder deflection angle Dx. When Dz, Dy, and Dx all take the value of 0, it is the state of no rudder deflection. Obtain the six-component aerodynamic characteristic data corresponding to the flight state of the reference configuration from the existing database. The six-component aerodynamic characteristic data corresponding to each group of flight states and rudder deflection states includes the axial force coefficient C A , normal force coefficient C N , side force coefficient C Z , roll moment M X , yaw moment M Y , and pitch moment M Z . In the same flight state, the aerodynamic data of the aircraft in the state of no rudder deflection must be included. For example, the flight states and rudder deflection states to be evaluated for the determined new configuration are shown in Table 1 below:

[0042] Table 1

[0043]

[0044] The six-component aerodynamic characteristic data corresponding to the flight state of the reference configuration obtained from the existing database includes the axial force coefficient C A , normal force coefficient C N , side force coefficient C Z , roll moment M X , yaw moment M Y , and pitch moment M Z , as shown in Table 2 below:

[0045] Table 2

[0046]

[0047] Step S12: Determine the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the state of no rudder deflection in the to-be-evaluated flight state based on the first aerodynamic data, and change the body of revolution in the reference configuration aircraft to the to-be-detected body of revolution to obtain the target to-be-detected aircraft.

[0048] In this embodiment, determining the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the non-rudder deflection state under the to-be-evaluated flight state based on the first aerodynamic data includes: determining the aerodynamic data difference corresponding to the target rudder deflection angle difference based on the difference between the first reference aerodynamic data and the second reference aerodynamic data; the target rudder deflection angle difference is the difference in rudder deflection angles between the target rudder deflection state and the non-rudder deflection state. Specifically, calculate the aerodynamic data difference at different rudder deflection angles in different flight states of the reference configuration according to the following formula. The specific calculation method is to calculate each aerodynamic data difference at each rudder deflection angle for each set of flight states Ma, α, β:

[0049] ;

[0050] ;

[0051] where, ∆C A represents the axial force coefficient difference, ∆C N represents the normal force coefficient difference, ∆C Z represents the side force coefficient difference, ∆M X represents the rolling moment difference, ∆M Y represents the yaw moment difference, ∆M Z represents the pitch moment difference; C A0 , C N0 and C Z0 represent the axial force coefficient, normal force coefficient, and side force coefficient in the non-rudder deflection state respectively; M X0 , M Y0 and M Z0 represent the rolling moment, yaw moment, and pitch moment in the non-rudder deflection state respectively. δ represents the rudder deflection angle, and for each set of rudder deflection states, only one of Dz, Dy, and Dx takes the value of δ, and the remaining variables take the value of 0. According to the example in step S11, the aerodynamic data difference at different rudder deflection angles in different flight states of the reference configuration. The specific calculation results are shown in Table 3 below:

[0052] Table 3

[0053]

[0054] Then, under the condition that the X-shaped tail rudder configuration remains unchanged, change the aerodynamic shape parameters of the fuselage part of the aircraft to obtain a new fuselage and the aerodynamic shape of the X-shaped tail rudder. In actual operation, the aerodynamic shape parameters of the fuselage part of the aircraft can be changed to obtain a new fuselage and the aerodynamic shape of the X-shaped tail rudder as shown in Figure 3

[0055] ​Step S13: Determine the second aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the rudder-zero state by using a preset numerical simulation method, and determine the target aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data.

[0056] In this embodiment, the step of determining the second aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the rudder-zero state by using a preset numerical simulation method includes: simulating and calculating the six-component aerodynamic characteristic data of the target aircraft to be detected in the to-be-evaluated flight state and the rudder-zero state by using pre-designed computational fluid dynamics software to obtain the second aerodynamic data. Specifically, for the aerodynamic shape of the new body of revolution aircraft, numerical simulation CFD (Computational Fluid Dynamics) software is used to calculate the six-component aerodynamic characteristic data of the aircraft in the rudder-zero flight state under different flight Mach numbers Ma, flight angles of attack α, and flight sideslip angles β, including the axial force coefficient C A , the normal force coefficient C N , the side force coefficient C Z , the rolling moment M X , the yawing moment M Y , and the pitching moment M Z . In actual operation, for example, numerical simulation CFD software is used to calculate the six-component aerodynamic characteristic data of the aircraft in the rudder-zero flight state under different flight Mach numbers Ma, flight angles of attack α, and flight sideslip angles β. In this embodiment, the NNW-Flowstar software is used, which can better calculate the aerodynamic characteristics of the aircraft, the multi-body separation characteristics, and the internal and external flow coupling characteristics. The specific calculation results are shown in Table 4:

[0057] Table 4

[0058]

[0059] Then, based on the assumption that the rudder effectiveness of the benchmark configuration is the same as that of the new body of revolution configuration, the aerodynamic data of the new body of revolution aircraft is calculated. Specifically, the step of determining the target aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data includes: substituting the aerodynamic data difference and the second aerodynamic data into a preset target aerodynamic data calculation formula to obtain the target aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the target rudder deflection state; the target aerodynamic data calculation formula is a summation formula constructed based on the aerodynamic data difference and the second aerodynamic data. The specific calculation method is as follows:

[0060] ;

[0061] ;

[0062] Among them, ∆C A represents the difference in axial force coefficient, ∆C N represents the difference in normal force coefficient, ∆C Z represents the difference in lateral force coefficient, ∆M X represents the difference in rolling moment, ∆M Y represents the difference in yaw moment, ∆M Z represents the difference in pitch moment. The values of these six differences are all calculated in step S12. C A0_new , C N0_new and C Z0_new respectively represent the axial force coefficient, normal force coefficient and lateral force coefficient of the new body of revolution configuration without rudder deflection; M X0_new , M Y0_new and M Z0_new respectively represent the rolling moment, yaw moment and pitch moment of the new body of revolution configuration without rudder deflection. C A_new , C N_new and C Z_new respectively represent the axial force coefficient, normal force coefficient and lateral force coefficient of the new body of revolution configuration under the rudder deflection angle δ; M X_new , M Y_new and M Z_new respectively represent the rolling moment, yaw moment and pitch moment of the new body of revolution configuration under the rudder deflection angle δ. δ represents the rudder deflection angle, and in each set of rudder deflection states, only one of Dz, Dy and Dx takes the value of δ, and the remaining variables take the value of 0. In actual operation, the predicted aerodynamic data of the new configuration are as shown in Table 5 below:

[0063] Table 5

[0064]

[0065] In this embodiment, after determining the target aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data, it further includes: based on a pre-designed computational fluid dynamics software, obtaining the third aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the target rudder deflection state, and determining whether the difference between the third aerodynamic data and the target aerodynamic data meets a preset data simulation condition; if the difference meets the preset data simulation condition, it is determined that the target aerodynamic data meets the preset aerodynamic data generation standard for the body of revolution aircraft. That is, by using CFD to calculate the aerodynamic data of the new body of revolution under different flight states and different rudder deflection angles, and comparing with the data generated by the present invention, the comparison results are as shown in Table 6 below:

[0066] Table 6

[0067]

[0068] As can be seen from the above simulation analysis, by using the method of the present invention, under the condition of obtaining finite high-dimensional samples, based on the data in the reference configuration database, through extrapolation calculation, the aerodynamic data of the new configuration can be quickly generated, and the generated aerodynamic data has a small error compared with the CFD calculation results, meeting the accuracy requirements of aircraft design.

[0069] It can be seen that in this embodiment, based on the target user's needs, a reference configuration aircraft with a body of revolution and an X-type tail rudder is selected from the preset aerodynamic database, and the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated is determined; based on the first aerodynamic data, the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the non-rudder deflection state in the flight state to be evaluated is determined, and the body of revolution in the reference configuration aircraft is changed to the body of revolution to be detected to obtain the target aircraft to be detected; the preset numerical simulation method is used to determine the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the non-rudder deflection state, and the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state is determined according to the aerodynamic data difference and the second aerodynamic data. In this way, under the condition of obtaining finite high-dimensional samples, based on the data in the reference configuration database, through extrapolation calculation, the aerodynamic data of the target aircraft to be detected corresponding to the new configuration can be quickly generated. Aerodynamic data can be quickly generated under the condition of limited computing resources, improving the prediction efficiency of the aerodynamic characteristics of the body of revolution and X-type tail rudder configurations, and thus reducing the design iteration cycle of this type of aircraft.

[0070] Reference Figure 4 As described above, the embodiment of the present application also correspondingly discloses a device for quickly generating aerodynamic data of a body of revolution aircraft, including:

[0071] A first aerodynamic data determination module 11, configured to select a reference configuration aircraft with a body of revolution and an X-type tail rudder from a preset aerodynamic database based on target user requirements, and determine the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated;

[0072] A to-be-detected aircraft construction module 12, configured to determine the aerodynamic data difference corresponding to the reference configuration aircraft between the target rudder deflection state and the non-rudder deflection state in the flight state to be evaluated based on the first aerodynamic data, and change the body of revolution in the reference configuration aircraft to the body of revolution to be detected to obtain the target aircraft to be detected;

[0073] The target aerodynamic data generation module 13 is used to determine the second aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the no-rudder-deflection state by using a preset numerical simulation method, and determine the target aerodynamic data of the target aircraft to be detected in the to-be-evaluated flight state and the target rudder-deflection state according to the aerodynamic data difference and the second aerodynamic data.

[0074] It can be seen that in this embodiment, under the condition of obtaining a finite number of high-dimensional samples, based on the data in the reference configuration database, through extrapolation calculation, the aerodynamic data of the target aircraft to be detected corresponding to the new configuration can be quickly generated. The aerodynamic data can be quickly generated under the condition of limited computing resources, improving the prediction efficiency of the aerodynamic characteristics of the body of revolution and the X-type tail rudder configuration, and thus reducing the design iteration cycle of this type of aircraft.

[0075] In some specific embodiments, the first aerodynamic data determination module 11 may specifically include:

[0076] The first reference aerodynamic data determination unit is used to determine the to-be-evaluated flight state and the target rudder-deflection state based on the target user requirements, and obtain the first reference aerodynamic data corresponding to the reference configuration aircraft in the to-be-evaluated flight state and the target rudder-deflection state from the preset aerodynamic database;

[0077] The second reference aerodynamic data determination unit is used to obtain the second reference aerodynamic data corresponding to the reference configuration aircraft in the to-be-evaluated flight state and the no-rudder-deflection state from the preset aerodynamic database.

[0078] In some specific embodiments, the to-be-detected aircraft construction module 12 may specifically include:

[0079] The rudder-deflection angle difference determination unit is used to determine the aerodynamic data difference corresponding to the target rudder-deflection angle difference based on the difference between the first reference aerodynamic data and the second reference aerodynamic data; the target rudder-deflection angle difference is the difference in the rudder-deflection angle between the target rudder-deflection state and the no-rudder-deflection state.

[0080] In some specific embodiments, the target aerodynamic data generation module 13 may specifically include:

[0081] The second aerodynamic data determination unit is used to perform simulation calculations on the six-component aerodynamic characteristic data of the target aircraft to be detected in the to-be-evaluated flight state and the no-rudder-deflection state by using pre-designed computational fluid dynamics software to obtain the second aerodynamic data.

[0082] In some specific embodiments, the target aerodynamic data generation module 13 may specifically include:

[0083] A data calculation unit is configured to substitute the pneumatic data difference and the second pneumatic data into a preset target pneumatic data calculation formula to obtain the target pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state; the target pneumatic data calculation formula is a summation formula constructed based on the pneumatic data difference and the second pneumatic data.

[0084] In some specific embodiments, the axisymmetric body aircraft pneumatic data rapid generation device may further include:

[0085] A data judgment module is configured to, based on a pre-designed computational fluid dynamics software, obtain the third pneumatic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state, and judge whether the difference between the third pneumatic data and the target pneumatic data meets a preset data simulation condition;

[0086] A data determination module is configured to, if the difference meets the preset data simulation condition, determine that the target pneumatic data meets the preset axisymmetric body aircraft pneumatic data generation standard.

[0087] Furthermore, an embodiment of the present application also discloses an electronic device, Figure 5 which is a structural diagram of an electronic device 20 shown according to an exemplary embodiment. The content in the figure should not be considered as any limitation to the scope of use of the present application.

[0088] Figure 5 This is a schematic structural diagram of an electronic device 20 provided by an embodiment of the present application. The electronic device 20 may specifically include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. Among them, the memory 22 is used to store a computer program, and the computer program is loaded and executed by the processor 21 to implement the relevant steps in the axisymmetric body aircraft pneumatic data rapid generation method disclosed in any of the foregoing embodiments. Additionally, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0089] In this embodiment, the power supply 23 is used to provide operating voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and external devices, and the communication protocol it follows is any communication protocol applicable to the technical solution of the present application, and specific limitations are not imposed here; the input / output interface 25 is used to obtain external input data or output data to the outside, and its specific interface type can be selected according to specific application requirements, and no specific limitations are made here.

[0090] In addition, as a carrier for storing resources, the memory 22 can be a read-only memory, a random access memory, a magnetic disk, an optical disk, etc. The resources stored thereon can include an operating system 221, a computer program 222, etc., and the storage method can be transient storage or permanent storage.

[0091] Among them, the operating system 221 is used to manage and control each hardware device and the computer program 222 on the electronic device 20, and it can be Windows Server, Netware, Unix, Linux, etc. In addition to the computer program that can be used to complete the method for quickly generating the aerodynamic data of the solid of revolution aircraft executed by the electronic device 20 disclosed in any of the foregoing embodiments, the computer program 222 can further include computer programs that can be used to complete other specific tasks.

[0092] Furthermore, the present application also discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the method for quickly generating the aerodynamic data of the solid of revolution aircraft disclosed above is implemented. For the specific steps of this method, reference can be made to the corresponding content disclosed in the foregoing embodiments, and details will not be repeated here.

[0093] In this specification, each embodiment is described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. For the same or similar parts among the embodiments, reference can be made to each other. For the device disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple, and reference can be made to the description in the method part for related parts.

[0094] Those skilled in the art can further realize that the units and algorithm steps of each example described in combination with the embodiments disclosed in this article can be implemented by electronic hardware, computer software, or a combination of the two. To clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described according to functions in the above description. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of this application.

[0095] The steps of the method or algorithm described in combination with the embodiments disclosed in this article can be directly implemented by hardware, a software module executed by a processor, or a combination of the two. The software module can be placed in a random access memory (RAM), internal memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, register, hard disk, removable disk, CD-ROM, or any other form of storage medium well-known in the technical field.

[0096] Finally, it should also be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising said element.

[0097] The technical solutions provided in this application have been introduced in detail above. Specific examples are used in this text to elaborate on the principles and implementation manners of this application. The description of the above embodiments is only used to help understand the method and its core idea of this application; at the same time, for those of ordinary skill in the art, according to the idea of this application, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to this application.

Claims

1. A method for quickly generating aerodynamic data of a rotating body aircraft, characterized in that: include: Based on the target user's needs, a reference configuration aircraft having a rotating body and an X-shaped tail rudder is selected from a preset aerodynamic database, and first aerodynamic data of the reference configuration aircraft in a flight state to be evaluated is determined; Determine the aerodynamic data difference between the reference configuration aircraft in the flight state to be evaluated, the target rudder deviation state and the no-rudder deviation state based on the first aerodynamic data, and change the rotational body in the reference configuration aircraft to the rotational body to be detected to obtain the target aircraft to be detected; Determine the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the no-rudder state by using a preset numerical simulation method, and determine the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder state according to the aerodynamic data difference and the second aerodynamic data; Wherein, the determining of the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the rudderless state by using a preset numerical simulation method includes: Using preset computational fluid dynamics software, a simulation calculation is performed on the six-component data of the aerodynamic characteristics of the target aircraft to be detected in the flight state to be evaluated and the rudderless state to obtain second aerodynamic data; Wherein, determining the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data includes: The aerodynamic data difference and the second aerodynamic data are substituted into a preset target aerodynamic data calculation formula to obtain the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deviation state; the target aerodynamic data calculation formula is a summation formula constructed based on the aerodynamic data difference and the second aerodynamic data.

2. The method for rapidly generating aerodynamic data of a rotating body aircraft according to claim 1, characterized in that: The determining of first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated includes: Determine the flight state to be evaluated and the target rudder deflection state based on the target user demand, and obtain first reference aerodynamic data of the reference configuration aircraft corresponding to the flight state to be evaluated and the target rudder deflection state from the preset aerodynamic database; Second reference aerodynamic data corresponding to the reference configuration aircraft in the flight state to be evaluated and the rudderless state are obtained from the preset aerodynamic database.

3. The method for rapidly generating aerodynamic data of a rotating body aircraft according to claim 2, characterized in that: The flight state to be evaluated is determined by the flight Mach number, the flight angle of attack and the flight sideslip angle; the target rudder deflection state is determined by the pitch rudder deflection angle, the yaw rudder deflection angle and the roll rudder deflection angle; the aerodynamic data is six-component data of aerodynamic characteristics, including: axial force coefficient, normal force coefficient, lateral force coefficient, rolling moment, yaw moment and pitching moment.

4. The method for rapidly generating aerodynamic data of a rotating body aircraft according to claim 2, characterized in that: The step of determining the aerodynamic data difference corresponding to the target rudder deviation state and the no rudder deviation state of the reference configuration aircraft under the flight state to be evaluated based on the first aerodynamic data comprises: An aerodynamic data difference corresponding to a target rudder angle difference is determined based on a difference between the first reference aerodynamic data and the second reference aerodynamic data; the target rudder angle difference is a rudder angle difference between the target rudder angle state and the no rudder angle state.

5. The method for rapidly generating aerodynamic data of a rotating body aircraft according to any one of claims 1 to 4, characterized in that: After determining the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data, the method further includes: Based on the preset computational fluid dynamics software, the third aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state are evaluated, and it is determined whether the difference between the third aerodynamic data and the target aerodynamic data meets the preset data simulation condition; If the difference satisfies the preset data simulation condition, it is determined that the target aerodynamic data meets the preset aerodynamic data generation standard for the rotating body aircraft.

6. A device for quickly generating aerodynamic data of a rotating body aircraft, characterized in that: include: a first aerodynamic data determination module, configured to select a reference configuration aircraft having a rotating body and an X-shaped tail rudder from a preset aerodynamic database based on target user requirements, and determine first aerodynamic data of the reference configuration aircraft in a flight state to be evaluated; a test aircraft construction module, configured to determine, based on the first aerodynamic data, a corresponding aerodynamic data difference between the reference configuration aircraft in the flight state to be evaluated, the target rudder deviation state and the no-rudder deviation state, and to change the rotational body in the reference configuration aircraft into the test rotational body to obtain the target test aircraft; a target aerodynamic data generating module, used for determining the second aerodynamic data of the target to-be-detected aircraft in the flight state to be evaluated and the state without rudder deviation by using a preset numerical simulation method, and determining the target aerodynamic data of the target to-be-detected aircraft in the flight state to be evaluated and the target rudder deviation state according to the aerodynamic data difference and the second aerodynamic data; Wherein, the determining of the second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the rudderless state by using a preset numerical simulation method includes: Using preset computational fluid dynamics software, a simulation calculation is performed on the six-component data of the aerodynamic characteristics of the target aircraft to be detected in the flight state to be evaluated and the rudderless state to obtain second aerodynamic data; Wherein, determining the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data includes: The aerodynamic data difference and the second aerodynamic data are substituted into a preset target aerodynamic data calculation formula to obtain the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deviation state; the target aerodynamic data calculation formula is a summation formula constructed based on the aerodynamic data difference and the second aerodynamic data.

7. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is used to execute the computer program to implement the method for quickly generating aerodynamic data of a rotating body aircraft as described in any one of claims 1 to 5.

8. A computer-readable storage medium, characterized in that: Used to store a computer program, which, when executed by a processor, implements the method for quickly generating aerodynamic data of a rotating body aircraft as described in any one of claims 1 to 5.

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