Method, device and equipment for rapidly generating aerodynamic data of gyroid aircraft and storage medium

Abstract

The invention discloses a method, device and equipment for rapidly generating aerodynamic data of a revolution body aircraft and a storage medium, and relates to the technical field of aircraft aerodynamic characteristic calculation, and the method comprises the steps: selecting one type of aircraft with a reference configuration having a revolution body and an X-shaped tail vane from a preset aerodynamic database based on the demand of a target user, determining first pneumatic data of the reference configuration aircraft in a to-be-evaluated flight state; based on the first pneumatic data, determining a corresponding pneumatic data difference between a target rudder deflection state and a rudder deflection-free state of the reference configuration aircraft, and changing a revolution body in the reference configuration aircraft into a revolution body to be detected to obtain a target aircraft to be detected; and simulating second aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the rudder deflection-free state, and determining 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. Therefore, the aerodynamic characteristic prediction efficiency of the rotary body aircraft can be improved.

Description

Technical Field

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

[0002] The rotational body and X-type tail rudder configuration are one of the main configurations of aircraft. Rapidly and accurately obtaining aerodynamic characteristic data under different flight states is of great significance to the flight performance evaluation and design and development of rotational body and X-type tail rudder configuration aircraft. 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 expensive and have a long data acquisition cycle; numerical calculations can obtain relatively accurate data in a relatively short time, but their computing resource requirements are large, 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 needs of aircraft design and evaluation. With the development of intelligent technology, prediction technology based on artificial intelligence has gradually developed, but due to the complex configuration and multiple flight states of rotational body and X-type tail rudder configuration aircraft, their data samples have high-dimensional nonlinear characteristics, which makes the current artificial intelligence methods rely heavily on sample data, have high demand, high modeling costs, and the calculation cost of the required samples may be unbearable.

[0003] It can be seen from the above that for the rotating body and X-type tail rudder configuration aircraft, solving the problem of rapid generation of aerodynamic data under the conditions of limited computing resources and improving the efficiency of aerodynamic characteristics prediction of the rotating body and X-type tail rudder configuration are issues 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 rotating body aircraft, which can improve the efficiency of predicting aerodynamic characteristics of a rotating body aircraft. The specific scheme is as follows:

[0005] In a first aspect, the present application discloses a method for rapidly generating aerodynamic data of a rotating body aircraft, comprising:

[0006] 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;

[0007] 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;

[0008] A 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 no-rudder state, and the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder state is determined based on the aerodynamic data difference and the second aerodynamic data.

[0009] Optionally, 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 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;

[0011] 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.

[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 data of aerodynamic characteristics, including: axial force coefficient, normal force coefficient, lateral force coefficient, rolling moment, yaw moment and pitch moment.

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

[0014] 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.

[0015] Optionally, 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:

[0016] The preset computational fluid dynamics software is used to simulate and calculate 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 the second aerodynamic data.

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

[0018] 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.

[0019] Optionally, after determining the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deviation state according to the aerodynamic data difference and the second aerodynamic data, the method further includes:

[0020] 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;

[0021] 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.

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

[0023] 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;

[0024] 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;

[0025] The target aerodynamic data generating module is used to 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 to 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.

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

[0027] Memory, used to store computer programs;

[0028] A processor is used to execute the computer program to implement the aforementioned method for quickly generating aerodynamic data of a rotating 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 aforementioned method for rapidly generating aerodynamic data of a rotating body aircraft.

[0030] It can be seen that in the present application, a reference configuration aircraft having a rotating body and an X-shaped tail rudder is selected from a preset aerodynamic database based on the target user's needs, and the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated is determined; the aerodynamic data difference corresponding to the reference configuration aircraft in the flight state to be evaluated, the target rudder deviation state and the no-rudder deviation state is determined based on the first aerodynamic data, and the rotating body in the reference configuration aircraft is changed to a rotating body to be detected to obtain a 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 no-rudder deviation state is determined by 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 deviation state is determined based on the aerodynamic data difference and the second aerodynamic data. In this way, under the condition of limited high-dimensional sample acquisition, based on the reference configuration database data, the aerodynamic data of the target aircraft to be detected corresponding to the new configuration can be quickly generated through extrapolation calculation. Aerodynamic data can be generated quickly under limited computing resources, improving the efficiency of predicting the aerodynamic characteristics of rotating bodies and X-shaped tail rudder configurations, thereby shortening the design iteration cycle of such aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0032] Figure 1 A flow chart of a method for quickly generating aerodynamic data of a rotating body aircraft disclosed in this application;

[0033] Figure 2 A schematic diagram of a reference configuration aircraft of a rotating body and an X-shaped tail rudder disclosed in the present application;

[0034] Figure 3 A schematic diagram of a new configuration aircraft with a rotating body and an X-shaped tail rudder disclosed in the present application;

[0035] Figure 4 This is a schematic diagram of the structure of a device for quickly generating aerodynamic data of a rotating body aircraft disclosed in this application;

[0036] Figure 5 This is a structural diagram of an electronic device disclosed in this application. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0038] With the development of intelligent technology, prediction technology based on artificial intelligence has been gradually developed. However, due to the complex configuration and multiple flight states of rotating body and X-shaped tail rudder configuration aircraft, their data samples have high-dimensional nonlinear characteristics, which makes the current artificial intelligence method highly dependent on sample data, has high demand, high modeling cost, and the calculation cost of the required samples may be unbearable. Therefore, this application will specifically introduce a method for quickly generating aerodynamic data of a rotating body aircraft, which can quickly generate aerodynamic data under limited computing resources.

[0039] See also Figure 1 As shown, the embodiment of the present application discloses a method for quickly generating aerodynamic data of a rotating body aircraft, comprising:

[0040] Step S11: selecting 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 determining first aerodynamic data of the reference configuration aircraft in a flight state to be evaluated.

[0041] In this embodiment, the determination of the first aerodynamic data of the reference configuration aircraft 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 needs, and obtaining the first baseline 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; obtaining the second baseline aerodynamic data corresponding to the reference configuration aircraft in the flight state to be evaluated and the rudderless state from the preset aerodynamic database. Among them, 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 pitch moment. Specifically, from the existing aerodynamic database, according to user needs, a rotating body and an X-type tail rudder aircraft are selected as the reference configuration. In actual operation, the following can be selected: Figure 2The reference configuration aircraft with a rotating body and an X-shaped tail rudder is shown. Then, according to user needs, the flight state and rudder deviation state that need to be evaluated for the new configuration are determined. Among them, a single flight state is determined by three parameters: the flight Mach number Ma, the flight angle of attack α, and the flight sideslip angle β. The rudder deviation state is jointly determined by three parameters: the pitch rudder deviation angle Dz, the yaw rudder deviation angle Dy, and the roll rudder deviation angle Dx. When Dz, Dy, and Dx take the value of 0 at the same time, it is a no-rudder deviation state. The six-component data of aerodynamic characteristics under the corresponding flight state of the reference configuration are obtained from the existing database. Each set of six-component data of aerodynamic characteristics corresponding to the flight state and rudder deviation state includes the axial force coefficient C A , Normal force coefficient C N , lateral force coefficient C Z , rolling moment M X , yaw moment M Y and pitch moment M Z In the same flight state, the aerodynamic data of the aircraft without rudder deviation must be included. For example, the flight state and rudder deviation state that need to be evaluated for the new configuration are shown in Table 1 below:

[0042] Table 1

[0043]

[0044] The six-component data of aerodynamic characteristics of the reference configuration corresponding to the flight state obtained from the existing database, including the axial force coefficient C A , Normal force coefficient C N , lateral force coefficient C Z , rolling 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: determining the aerodynamic data difference corresponding to 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 changing the rotational body in the reference configuration aircraft to the rotational body to be detected to obtain the target aircraft to be detected.

[0048] In this embodiment, the determination of 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 includes: determining the aerodynamic data difference corresponding to the target rudder deviation angle difference based on the difference between the first reference aerodynamic data and the second reference aerodynamic data; the target rudder deviation angle difference is the rudder deviation angle difference between the target rudder deviation state and the no-rudder deviation state. Specifically, the aerodynamic data difference under different rudder deviation angles of different flight states of the reference configuration is calculated according to the following formula. The specific calculation method is, for each group of flight states Ma, α, β, calculating each aerodynamic data difference under each rudder deviation angle:

[0049] ;

[0050] ;

[0051] Where, ∆C A Denotes the axial force coefficient difference, ∆C N Denotes the normal force coefficient difference, ∆C Z Denotes the difference in lateral force coefficient, ∆M X Denotes the rolling moment difference, ∆M Y Denotes the yaw moment difference, ∆M Z Indicates the pitch moment difference; C A0 , C N0 and C Z0 They represent the axial force coefficient, normal force coefficient and lateral force coefficient under the no-rudder deflection state respectively; M X0 、M Y0 and M Z0 Respectively represent the rolling moment, yaw moment and pitch moment in the state without rudder deflection. δ represents the rudder deflection angle, and in each set of rudder deflection states, only one variable of Dz, Dy and Dx takes the value of δ, and the other variables take the value of 0. According to the example in step S11, the aerodynamic data difference under different flight states and different rudder deflection angles 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, the aerodynamic shape parameters of the rotating body of the aircraft are changed to obtain a new aerodynamic shape of the rotating body and the X-shaped tail rudder. In actual operation, the aerodynamic shape parameters of the rotating body of the aircraft can be changed to obtain the following: Figure 3 The new rotating body and X-shaped tail rudder aerodynamic shape are shown.

[0055] Step S13: 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.

[0056] In this embodiment, the use of 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 rudderless state includes: using a preset computational fluid dynamics software to simulate and calculate 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 the second aerodynamic data. Specifically, for the aerodynamic shape of the new rotating body aircraft, numerical simulation CFD (Computational Fluid Dynamics, i.e., computational fluid dynamics) software is used to calculate the six-component data of the aerodynamic characteristics of the aircraft in the rudderless 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 , Normal force coefficient C N , lateral force coefficient C Z , rolling moment M X , yaw moment M Y and pitch moment M Z . In actual operation, for example, numerical simulation CFD software is used to calculate the six-component data of the aerodynamic characteristics of the aircraft in the rudderless flight state under different flight Mach numbers Ma, flight angles of attack α and flight sideslip angles β. This embodiment uses NNW-Flowstar software, which can better calculate the aerodynamic characteristics, multi-body separation characteristics and internal and external flow coupling characteristics of the aircraft. The specific calculation results are shown in Table 4:

[0057] Table 4

[0058]

[0059] Then, based on the assumption that the rudder effects of the baseline configuration and the new rotational body configuration are consistent, the aerodynamic data of the new rotational body aircraft are calculated. Specifically, the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder deviation state are determined according to the aerodynamic data difference and the second aerodynamic data, including: 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 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. The specific calculation method is as follows:

[0060] ;

[0061] ;

[0062] Where, ∆C A Denotes the axial force coefficient difference, ∆C N Denotes the normal force coefficient difference, ∆C Z Denotes the difference in lateral force coefficient, ∆M X Denotes the rolling moment difference, ∆M Y Denotes the yaw moment difference, ∆M Z represents the pitch moment difference, and the values ​​of these six differences are all calculated in step S12. A0_new , C N0_new and C Z0_new They represent the axial force coefficient, normal force coefficient and lateral force coefficient of the new rotating body configuration without rudder deflection; M X0_new 、M Y0_new and M Z0_new They represent the rolling moment, yaw moment and pitching moment of the new rotating body configuration without rudder deflection. A_new , C N_new and C Z_new are the axial force coefficient, normal force coefficient and lateral force coefficient of the new rotating body configuration under the condition of rudder deflection angle δ; M X_new 、M Y_new and M Z_new They represent the rolling moment, yaw moment and pitch moment of the new rotating body configuration under the condition of rudder deflection angle δ. δ represents the rudder deflection angle, and in each set of rudder deflection states, only one variable of Dz, Dy and Dx takes the value of δ, and the other variables take the value of 0. In actual operation, the predicted aerodynamic data of the new configuration are 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 flight state to be evaluated and the target rudder deflection state according to the aerodynamic data difference and the second aerodynamic data, it also 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, and judging whether the difference between the third aerodynamic data and the target aerodynamic data meets the preset data simulation conditions; if the difference meets the preset data simulation conditions, it is determined that the target aerodynamic data meets the preset aerodynamic data generation standard for the rotating body aircraft. That is, by using CFD to calculate the aerodynamic data of the new rotating body under different flight states and different rudder deflection angles, and comparing with the data generated by the present invention, the comparison is shown in Table 6 below:

[0066] Table 6

[0067]

[0068] From the above simulation analysis, it can be seen that by adopting the method of the present invention, under the condition of limited high-dimensional sample acquisition, based on the reference configuration database data, through extrapolation calculation, the aerodynamic data of the new configuration can be quickly generated, and the generated aerodynamic data has a smaller error than the CFD calculation result, which meets the accuracy requirements of aircraft design.

[0069] It can be seen that in this embodiment, a reference configuration aircraft having a rotating body and an X-shaped tail rudder is selected from the preset aerodynamic database based on the target user's needs, and the first aerodynamic data of the reference configuration aircraft in the flight state to be evaluated is determined; the aerodynamic data difference corresponding to the reference configuration aircraft in the flight state to be evaluated, the target rudder deviation state and the no-rudder deviation state is determined based on the first aerodynamic data, and the rotating body in the reference configuration aircraft is changed to the rotating body 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 no-rudder deviation 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 deviation state is determined according to the aerodynamic data difference and the second aerodynamic data. In this way, under the condition of limited high-dimensional sample acquisition, based on the reference configuration database data, the aerodynamic data of the target aircraft to be detected corresponding to the new configuration can be quickly generated through extrapolation calculation. Aerodynamic data can be generated quickly under limited computing resources, improving the efficiency of predicting the aerodynamic characteristics of rotating bodies and X-shaped tail rudder configurations, thereby shortening the design iteration cycle of such aircraft.

[0070] refer to Figure 4 The embodiment of the present application also discloses a device for quickly generating aerodynamic data of a rotating body aircraft, including:

[0071] A first aerodynamic data determination module 11 is used 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;

[0072] The aircraft to be tested constructing module 12 is used to 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 tested to obtain the target aircraft to be tested;

[0073] The target aerodynamic data generating module 13 is used to 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 to 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.

[0074] It can be seen that in this embodiment, under the condition of limited high-dimensional sample acquisition, based on the reference configuration database data, the aerodynamic data of the target aircraft to be detected corresponding to the new configuration can be quickly generated through extrapolation calculation. Aerodynamic data can be quickly generated under the condition of limited computing resources, improving the efficiency of aerodynamic characteristics prediction of the rotating body and X-type tail rudder configuration, thereby shortening the design iteration cycle of such aircraft.

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

[0076] a first reference aerodynamic data determining unit, configured to determine a flight state to be evaluated and a target rudder deflection state based on the target user's requirements, and to obtain first reference aerodynamic data corresponding to the flight state to be evaluated and the target rudder deflection state of the reference configuration aircraft from the preset aerodynamic database;

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

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

[0079] A rudder angle difference determination unit is used to determine an aerodynamic data difference corresponding to a target rudder angle difference 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.

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

[0081] The second aerodynamic data determination unit is used to use preset computational fluid dynamics software to simulate and calculate 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.

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

[0083] A data calculation unit is used to substitute the aerodynamic data difference and the second aerodynamic data into a preset target aerodynamic data calculation formula to obtain 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.

[0084] In some specific embodiments, the device for quickly generating aerodynamic data of a rotating body aircraft may further include:

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

[0086] The data determination module is used to determine that the target aerodynamic data meets the preset aerodynamic data generation standard of the rotating body aircraft if the difference meets the preset data simulation condition.

[0087] Furthermore, the present application also discloses an electronic device. Figure 5 This is a structural diagram of an electronic device 20 according to an exemplary embodiment. The content in the diagram cannot be regarded as any limitation on the scope of use of the present application.

[0088] Figure 5 A schematic diagram of the structure of an electronic device 20 provided in 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. The memory 22 is used to store a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the method for rapidly generating aerodynamic data of a rotating body aircraft disclosed in any of the aforementioned embodiments. In addition, 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 working 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 the external device, and the communication protocol it follows is any communication protocol that can be applied to the technical solution of the present application, and is not specifically limited here; the input and output interface 25 is used to obtain external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs and is not specifically limited here.

[0090] In addition, the memory 22, as a carrier for storing resources, can be a read-only memory, a random access memory, a disk or 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 temporary storage or permanent storage.

[0091] The operating system 221 is used to manage and control the hardware devices and computer program 222 on the electronic device 20, and 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 aerodynamic data of a rotating body aircraft executed by the electronic device 20 disclosed in any of the aforementioned 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 aforementioned disclosed method for rapidly generating aerodynamic data of a rotating body aircraft is implemented. The specific steps of the method can be referred to the corresponding contents disclosed in the aforementioned embodiments, and will not be repeated here.

[0093] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0094] Professionals may further appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described in the above description according to function. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

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

[0096] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0097] The technical solution provided by the present application is introduced in detail above. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea. At the same time, for general technicians in this field, according to the idea of ​​the present application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present 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; A 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 no-rudder state, and the target aerodynamic data of the target aircraft to be detected in the flight state to be evaluated and the target rudder state is determined 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 claim 2, characterized in that: The method of 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 rudderless state includes: The preset computational fluid dynamics software is used to simulate and calculate 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 the second aerodynamic data.

6. The method for rapidly generating aerodynamic data of a rotating body aircraft according to claim 2, characterized in that: The step of 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 comprises: 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. The method for rapidly generating aerodynamic data of a rotating body aircraft according to any one of claims 1 to 6, 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.

8. 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; The target aerodynamic data generating module is used to 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 to 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.

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

10. 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 7.

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