Method and device for constructing dynamic inflow boundary based on aircraft flow field simulation

Abstract

The application discloses a dynamic inflow boundary construction method and device based on aircraft flow field simulation, relates to the technical field of fluid mechanics, and comprises the following steps: selecting a target inflow boundary parameter type and a combination mode according to a current maneuvering state and a current flight environment change of an aircraft; determining a corresponding target input mode according to the target inflow boundary parameter type; reading a time-varying dynamic inflow boundary parameter sequence from an external configuration source through a preset external data reading interface based on the target input mode; converting the dynamic inflow boundary parameter sequence into a target reference parameter combination according to a reference parameter type and a combination mode of initialization flow field information; and replacing corresponding parameter values in an inflow boundary area by using the target reference parameter combination, thereby completing the construction of the dynamic inflow boundary. Through dynamic adaptation to the aircraft maneuvering state and the flight environment change, the application realizes the targeted selection, flexible input and real-time update of the inflow boundary parameters, and accurately captures the dynamic change of the inflow parameters over time.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of fluid mechanics, in particular to a dynamic inflow boundary construction method and device based on aircraft flow field simulation. BACKGROUND

[0002] Nowadays, with the continuous development of aerospace technology, the flight environment faced by the new generation of aircraft is becoming more and more complex (such as cross-medium flight, near-space flight, etc.), and these complex flight environments will also be accompanied by the emergence of complex flight scenarios. The aircraft itself will appear rapid changes in flight attitude (climbing, diving, sharp turning), super-high-speed flight reentry and other maneuvering changes, and the atmospheric environment parameters will also fluctuate dramatically with the changes in space and time, and the aircraft will interact with the surrounding flow field and cause a series of problems. The above flight scenarios will cause the rapid change of the inflow state, resulting in the dynamic change of the flight height, Mach number, temperature, pressure, direction, angle of attack and other inflow parameters of the aircraft with space and time.

[0003] For the process of conventional computational fluid dynamics (CFD) simulation, static inflow boundary conditions are mostly used (that is, the flight environment parameters of the aircraft are assumed not to change during calculation), such as fixed values of inflow velocity, density, temperature, pressure, etc. The setting of static inflow boundary conditions is applicable to steady-state numerical simulation or non-steady-state simulation with short physical time intervals. However, for static inflow boundary conditions, the characteristics of parameter fixation and low dynamic response capability make it difficult to effectively capture the dynamic disturbance of the flight process, especially in high-maneuvering flight scenarios or complex aerodynamic environments, and there is often a significant deviation between the numerical simulation results and the actual flight data, which may seriously affect the safety and reliability of aircraft design.

[0004] In summary, how to solve the problem of static inflow boundary condition parameter fixation, low dynamic response capability, and inability to effectively capture the dynamic change of inflow parameters with time in high-maneuvering flight or complex atmospheric environment of the aircraft, and improve the dynamic response precision and engineering practicability of flow field simulation is a technical problem to be solved in the field. SUMMARY

[0005] Therefore, the purpose of the present application is to provide a dynamic inflow boundary construction method and device based on aircraft flow field simulation, which can solve the problem of static inflow boundary condition parameter fixation, low dynamic response capability, and inability to effectively capture the dynamic change of inflow parameters with time in high-maneuvering flight or complex atmospheric environment of the aircraft, and improve the dynamic response precision and engineering practicability of flow field simulation. The specific scheme is as follows:

[0006] In a first aspect, the application discloses a method for constructing a dynamic inflow boundary based on a flight vehicle flow field simulation, comprising:

[0007] According to the current flight vehicle's current maneuvering state and the current flight environment changes, a target inflow boundary parameter type and a combination mode are selected;

[0008] According to the target inflow boundary parameter type, a corresponding target input mode is determined; wherein the target input mode is used to determine the reading mode and the dynamic change process of the dynamic inflow boundary parameter;

[0009] Based on the target input mode and through a preset external data reading interface, a time-varying dynamic inflow boundary parameter sequence is read from an external configuration source, and the dynamic inflow boundary parameter sequence is converted into a target reference parameter combination according to the reference parameter type of the initialization flow field information and the combination mode, and then the corresponding parameter value in the inflow boundary area is replaced by the target reference parameter combination, so as to complete the construction of the dynamic inflow boundary.

[0010] Optionally, before the target inflow boundary parameter type and the combination mode are selected according to the current flight vehicle's current maneuvering state and the current flight environment changes, the method further comprises:

[0011] A geometric shape model of the current flight vehicle is determined, a calculation grid on the geometric shape model is generated, and initialization flow field information containing an inflow boundary area in the calculation grid is obtained.

[0012] Optionally, the determination of the geometric shape model of the current flight vehicle, the generation of the calculation grid on the geometric shape model, and the acquisition of the initialization flow field information containing the inflow boundary area in the calculation grid comprise:

[0013] The current flight vehicle is subjected to CAD modeling processing to obtain the geometric shape model of the current flight vehicle;

[0014] The geometric shape model is subjected to calculation grid generation processing, and boundary condition types of the calculation grid are generated in different calculation grid areas according to flow field simulation requirement information;

[0015] Based on the boundary condition types, an area where the inflow boundary is located is determined from the calculation grid to obtain an inflow boundary area, and initialization flow field information of the calculation grid is obtained.

[0016] Optionally, the target input mode is a function relationship input mode or a parameter list input mode.

[0017] Optionally, the reading of the time-varying dynamic inflow boundary parameter sequence from the external configuration source based on the target input mode and through the preset external data reading interface comprises:

[0018] reading, based on the function relationship input mode, a function relationship set of the aircraft state parameters changing with time and / or a function relationship set of the atmospheric environment parameters changing with time from the function relationship configuration file through the preset external data reading interface to obtain the dynamic inflow boundary parameter sequence.

[0019] Optionally, the reading, based on the function relationship input mode, a function relationship set of the aircraft state parameters changing with time and / or a function relationship set of the atmospheric environment parameters changing with time from the function relationship configuration file through the preset external data reading interface to obtain the dynamic inflow boundary parameter sequence comprises:

[0020] reading, based on the function relationship input mode, a function relationship set of the aircraft state parameters changing with time and / or a function relationship set of the atmospheric environment parameters changing with time from the function relationship configuration file through the preset external data reading interface to obtain the dynamic inflow boundary parameter sequence.

[0021] generating a function relationship set of the dynamic inflow boundary parameters changing with time based on the function relationship set of the aircraft state parameters changing with time and / or the function relationship set of the atmospheric environment parameters changing with time to obtain the dynamic inflow boundary parameter sequence.

[0022] Optionally, the reading, based on the target input mode, a dynamic inflow boundary parameter sequence changing with time from an external configuration source through the preset external data reading interface comprises:

[0023] reading, based on the parameter list input mode, a structured aircraft parameter under different aircraft parameter categories from a parameter list configuration file through the preset external data reading interface to obtain the dynamic inflow boundary parameter sequence.

[0024] Optionally, the reading, based on the parameter list input mode, a structured aircraft parameter under different aircraft parameter categories from a parameter list configuration file through the preset external data reading interface to obtain the dynamic inflow boundary parameter sequence comprises:

[0025] reading, based on the parameter list input mode, a structured flight parameter of the aircraft attitude parameter category, the motion parameter category and the atmospheric parameter category at different time instants from a parameter list configuration file through the preset external data reading interface to obtain the dynamic inflow boundary parameter sequence; wherein the structured flight parameter comprises a parameter quantity, a name, a type and a corresponding value.

[0026] Optionally, the method further comprises:

[0027] constructing a reference-to-flow parameter database to persistently store target reference parameter combinations;

[0028] when receiving a data read request, reading target reference parameters corresponding to the data read request from the reference-to-flow parameter database.

[0029] In a second aspect, the present application discloses a dynamic reference-to-flow boundary construction device based on aircraft flow field simulation, comprising:

[0030] a type selection module configured to select a target reference-to-flow boundary parameter type and a combination mode according to a current maneuvering state of a current aircraft and a current flight environment change;

[0031] a mode selection module configured to determine a corresponding target input mode according to the target reference-to-flow boundary parameter type; wherein the target input mode is used to determine a reading mode and a dynamic change process of the dynamic reference-to-flow boundary parameters;

[0032] a reference-to-flow boundary construction module configured to read a time-varying dynamic reference-to-flow boundary parameter sequence from an external configuration source based on the target input mode and through a preset external data reading interface, and convert the dynamic reference-to-flow boundary parameter sequence into a target reference parameter combination according to a reference parameter type of initial flow field information and the combination mode, and then replace corresponding parameter values in a reference-to-flow boundary region with the target reference parameter combination to complete construction of the dynamic reference-to-flow boundary.

[0033] In a third aspect, the present application discloses an electronic device, comprising:

[0034] a memory configured to save a computer program;

[0035] a processor configured to execute the computer program to implement steps of the dynamic reference-to-flow boundary construction method based on aircraft flow field simulation disclosed above.

[0036] In a fourth aspect, the present application discloses a computer readable storage medium configured to store a computer program; wherein the computer program is executed by a processor to implement steps of the dynamic reference-to-flow boundary construction method based on aircraft flow field simulation disclosed above.

[0037] It can be seen that the application discloses a dynamic inflow boundary construction method based on aircraft flow field simulation, which comprises the following steps: selecting a target inflow boundary parameter type and a combination mode according to a current aircraft current maneuvering state and a current flight environment change; determining a corresponding target input mode according to the target inflow boundary parameter type; wherein the target input mode is used to determine a reading mode and a dynamic change process of the dynamic inflow boundary parameter; reading a time-varying dynamic inflow boundary parameter sequence from an external configuration source based on the target input mode and through a preset external data reading interface, and converting the dynamic inflow boundary parameter sequence into a target reference parameter combination according to a reference parameter type of initialization flow field information and the combination mode, and then replacing corresponding parameter values in the inflow boundary area with the target reference parameter combination, so as to complete the construction of the dynamic inflow boundary. It can be seen that, by combining the real-time maneuvering state and the environmental change, the selected parameter type and combination are ensured to be highly matched with the actual scene, and the introduction of redundant or irrelevant parameters is avoided. By matching the parameter type with the input mode, the reading mode and the change process of the dynamic inflow boundary parameter are adapted to the parameter characteristics, the flexibility of parameter input is enhanced, different dynamic change rules can be adapted to the scene, and the limitation of a single input mode is avoided. By reading the time-varying parameter sequence through the preset interface, the real-time of the parameter source is ensured; by converting into the reference parameter combination, the parameter format is ensured to be consistent with the flow field simulation requirement, and the calculation error caused by the format incompatibility is avoided; by replacing the parameter values in the inflow boundary area, the dynamic update of the inflow boundary is directly realized, and the limitation of the fixedization of the static boundary parameter is broken. By dynamically adapting the aircraft maneuvering state and the flight environment change, the targeted selection, flexible input and real-time update of the inflow boundary parameter are realized, the dynamic change of the inflow parameter with time can be accurately captured, the adaptability and simulation accuracy of the aircraft flow field simulation to the complex flight scene are improved, and the flow field simulation requirement under the high maneuvering flight or the complex atmospheric environment is met. BRIEF DESCRIPTION OF DRAWINGS

[0038] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort on the basis of the provided drawings.

[0039] Figure 1 A flow chart of a dynamic inflow boundary construction method based on aircraft flow field simulation disclosed by the present application;

[0040] Figure 2 A schematic diagram of a calculation grid boundary setting disclosed by the present application;

[0041] Figure 3A dynamic parameter reading method flow chart disclosed by the application;

[0042] Figure 4 A dynamic inflow boundary construction device structure schematic diagram based on aircraft flow field simulation disclosed by the application;

[0043] Figure 5 An electronic equipment structure diagram disclosed by the application. DETAILED DESCRIPTION

[0044] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the application.

[0045] Nowadays, with the continuous development of aerospace technology, the flight environment faced by a new generation of aircraft is more and more complex (such as cross-medium flight, near-space flight, etc.), and these complex flight environments will also be accompanied by the emergence of complex flight scenes. The aircraft itself will appear rapid changes in flight attitude (climbing, diving, sharp turning), super-high-speed flight reentry and other maneuvering change conditions, and the atmospheric environment parameters will also fluctuate sharply with the changes in space and time, and the aircraft will interact with the surrounding flow field and cause a series of problems. The above flight scenes will cause the sharp change of the inflow state, so that the flight height, Mach number, temperature, pressure, direction, angle of attack and other inflow parameters of the aircraft will change dynamically with space and time.

[0046] For the process of conventional computational fluid dynamics (CFD) simulation, a static inflow boundary condition is mostly used (that is, it is assumed that the flight environment parameters of the aircraft are not changed during calculation), for example, the speed, density, temperature and pressure of the inflow are fixed values. The setting of the static inflow boundary condition is applicable to the steady numerical simulation process or the unsteady numerical simulation process with a short physical interval time. However, for the static inflow boundary condition, its parameters are static and have low dynamic response capability, which cannot effectively capture the dynamic disturbance of the flight process, especially in the high-maneuvering flight scene or complex aerodynamic environment, and there is often a significant deviation between the numerical simulation result and the actual flight data, which may seriously affect the safety and reliability of the aircraft design.

[0047] Therefore, the application provides a dynamic inflow boundary construction scheme based on aircraft flow field simulation, which can solve the problems of parameter fixation of the static inflow boundary condition, low dynamic response capability and inability to effectively capture the dynamic change of the inflow parameters with time in the high-maneuvering flight or complex atmospheric environment of the aircraft, and improve the dynamic response precision and engineering practicability of the flow field simulation.

[0048] Referring to Figure 1 As shown in the figure, the embodiment of the application discloses a dynamic inflow boundary construction method based on aircraft flow field simulation, comprising:

[0049] Step S11: according to the current maneuvering state of the current aircraft and the current flight environment change, select the target inflow boundary parameter type and combination mode.

[0050] In this embodiment, before selecting the target inflow boundary parameter type and combination mode according to the current maneuvering state of the current aircraft and the current flight environment change, the method further comprises: determining the geometric shape model of the current aircraft, generating a calculation grid on the geometric shape model, and obtaining initialization flow field information of the inflow boundary region in the calculation grid. Specifically, CAD modeling processing is performed on the current aircraft to obtain the geometric shape model of the current aircraft; the geometric shape model is subjected to calculation grid generation processing, and boundary condition types of the calculation grid are generated in different calculation grid regions according to flow field simulation requirement information; the region where the inflow boundary is located is determined from the calculation grid based on the boundary condition types to obtain the inflow boundary region, and the initialization flow field information of the calculation grid is obtained. It can be understood that for the CFD numerical calculation process, first, a two-dimensional or three-dimensional model (i.e. a CAD model) is constructed according to the required research object (the current aircraft), then the calculation grid is generated according to the CAD model, and the boundary condition types (such as: inflow boundary, outlet boundary, wall boundary, symmetry plane, polarity axis, etc.) of the generated calculation grid are set according to research problems, flight conditions, physical modeling, and grid topology, etc. various flow field simulation requirement information, according to the calculation grid region, wherein, Figure 2 is a schematic diagram of the calculation grid and boundary condition types of part of the wing of the current aircraft, and the dynamic boundary constructed by the present scheme is mainly operated on the inflow boundary in Figure 2 Therefore, the region where the boundary condition type is the inflow boundary is determined from the calculation grid.

[0051] In this embodiment, the dynamic incoming flow boundary is primarily used in unsteady calculations, which typically study the changes in aerodynamic parameters of an aircraft over a specific time period (e.g., t0 to t1). T0 is the initial time, and t1 is the calculation termination time. The period from t0 to t1 is divided into several sub-time periods, and each sub-time period is simulated and calculated separately. The initial value for the dynamic incoming flow boundary is primarily based on the environmental parameter Q0 at time t0 of the aircraft's unsteady calculation. Q0 represents any set of various incoming flow parameters, such as velocity, temperature, density, pressure, component mass fraction, angle of attack, and sideslip angle. After completing boundary condition initialization, the initial value Q0 of the incoming flow boundary is assigned to the entire computational grid area, thereby initializing the aircraft's flow field. This means obtaining initialized flow field information, providing initial values ​​for subsequent numerical calculations.

[0052] In this embodiment, the main purpose is to obtain the maneuvering flight state parameters of the aircraft and the changes in the flight environment. Generally speaking, during the flight test of an aircraft, different types of state parameters can be obtained based on the differences in the types and layout of the aircraft's sensors. Among them, the angle of attack and sideslip angle are attitude parameters, the Mach number and altitude are motion parameters, and the density, temperature, pressure, etc. are atmospheric parameters. Therefore, it is necessary to determine the types of target flow boundary parameters that can be obtained and the combinations of parameters that can be used for numerical calculations. For example, the combination of Mach number and flight altitude, the combination of speed, density, and temperature, etc., are different. Different target flow boundary parameter types and combinations will affect the reading method of dynamic flow boundary parameters in subsequent steps, the data conversion process, and the final dynamic change process.

[0053] Step S12: determining a corresponding target input mode according to the target incoming flow boundary parameter type; wherein the target input mode is used to determine the reading method and dynamic change process of the dynamic incoming flow boundary parameter.

[0054] In this embodiment, the target input mode is a function relationship input mode or a parameter list input mode. It can be understood that the type of dynamic incoming flow boundary parameters is determined by the given aircraft maneuvering flight state and flight environment parameters, that is, the target incoming flow boundary parameter type is determined. Therefore, the reading method of the dynamic incoming flow boundary parameters and the dynamic change process can be determined according to the actual situation. Specifically, in the above embodiment, the dynamic incoming flow parameter input method can be selected according to the aircraft flight maneuvering mode, the flight environment parameter acquisition situation and the scientific problem to be studied, that is, the target input mode is determined according to the target incoming flow boundary parameter type.

[0055] Step S13: reading a time-varying dynamic inflow boundary parameter sequence from an external configuration source based on the target input mode and through a preset external data reading interface, and converting the time-varying dynamic inflow boundary parameter sequence into a target reference parameter combination according to a reference parameter type of initializing flow field information and the combination mode, and then replacing corresponding parameter values in the inflow boundary area with the target reference parameter combination to complete the construction of the dynamic inflow boundary.

[0056] In this embodiment, two different input modes are given below for the dynamic inflow boundary parameter variation process, and their mutual relationship is described below for the following two cases. Figure 3

[0057] In this embodiment, based on the function relationship input mode and through a preset external data reading interface, a set of function relationships representing the variation of aircraft state parameters with time and / or a set of function relationships representing the variation of atmospheric environment parameters in which the aircraft is located with time are read from a function relationship configuration file to obtain a dynamic inflow boundary parameter sequence. Specifically, based on the function relationship input mode, the number of inflow parameters, the function relationship of each inflow parameter with time, and the initial value of each inflow parameter are read from the function relationship configuration file through the preset external data reading interface, and a set of function relationships representing the variation of aircraft state parameters with time and / or a set of function relationships representing the variation of atmospheric environment parameters in which the aircraft is located with time are obtained by analyzing to obtain a set of function relationships representing the variation of aircraft state parameters with time and / or a set of function relationships representing the variation of atmospheric environment parameters in which the aircraft is located with time; and a set of dynamic inflow boundary parameters with time is generated according to the set of function relationships representing the variation of aircraft state parameters with time and / or the set of function relationships representing the variation of atmospheric environment parameters in which the aircraft is located with time to obtain a dynamic inflow boundary parameter sequence.

[0058] In a specific embodiment, when the target input mode is to input the dynamic inflow parameter variation in the form of a function relationship, for this case, the user is mainly supported to input in the form of a self-defined function to reflect the dynamic variation process of the inflow parameter. When the aircraft performs regular maneuvering flight, for example, a horizontal circular flight motion of a fixed-wing aircraft with a fixed radius and height, a vertical climb / descent motion of a rotorcraft with periodic adjustment of height, etc. For the above-mentioned regular dynamic variation of the inflow parameter with time, a mapping relationship between the dynamic inflow parameter and the input variable is established in this embodiment, which is wherein, represents a set of function relationships representing the variation of aircraft state parameters with time, and specifically includes but is not limited to an angle of attack, a Mach number, an altitude, etc., represents a set of function relationships representing the variation of atmospheric environment parameters in which the aircraft is located with time, and specifically includes but is not limited to density, temperature, pressure, etc., represents a set of function relationships representing the variation of each dynamic inflow boundary parameter with time, which is composed of the above-mentioned two types of aircraft parameters, and in actual application, ​The aircraft state parameters and the atmospheric environment parameters can jointly affect the aircraft, or only one of the parameters can affect the aircraft. It should be noted that the input form of the aforementioned self-defined function is mainly for and The expressions of the parameters in the two sets over time are specifically operated as follows: first, a function.dat file is established, which mainly inputs the corresponding relationship between each incoming flow parameter and time, and the main information includes but is not limited to: the number of incoming flow parameters, the function relationship (linear or nonlinear relationship) of each incoming flow parameter and time, the initial value, and the like. Then, the relationship information in the function.dat file is read through the construction of a general external file interface ReadBCParaFile(), and relying on an existing open-source third-party mathematical expression parser library, the mathematical expression in text form can be converted into a calculable function, thereby realizing the form input of the dynamic incoming flow parameter change condition of any function relationship.

[0059] In this embodiment, based on the parameter list input mode and through a preset external data reading interface, structured aircraft parameters under different aircraft parameter categories are read from a parameter list configuration file to obtain a dynamic incoming flow boundary parameter sequence. Specifically, based on the parameter list input mode, through the preset external data reading interface, structured flight parameters of an aircraft attitude parameter category, a motion parameter category, and an atmospheric parameter category at different times are read from the parameter list configuration file to obtain the dynamic incoming flow boundary parameter sequence; wherein the structured flight parameters include parameter quantity, name, type, and corresponding numerical value.

[0060] In another specific embodiment, when the target input mode is to support the user to input the random, irregular flow parameters in the form of parameter list to reflect the dynamic changing process. In this embodiment, compared with the regularity of the above-mentioned embodiment, it is suitable for irregular motion flight, such as aircraft out of control and abnormal state flight, test of large angle of attack stall test, reentry of space vehicle into the atmosphere, etc. The above-mentioned irregular flight generally refers to the lack of fixed rules in time or space in flight trajectory, attitude or control mode, showing the characteristics of high dynamic, random or unpredictable. For the above-mentioned situation, the flight data is measured and transmitted and stored in real time by sensor, so as to obtain various flight parameters such as flight height, speed, temperature, pressure, etc. In this embodiment, parameterList.dat file is first established, which mainly contains the number, name, type, value of flight parameter, and the flight parameters are classified according to the category, and the change of dynamic flow parameter is input in a structured form to form the parameter list corresponding to different heights, different Mach numbers, different temperatures and other dynamic changes at different times, and then the flight data information in parameterList.dat file is read through the construction of general external file interface ReadBCParaFile(), to realize the input of dynamic flow parameter change in the form of self-defined value.

[0061] In this way, through the construction of the two flight environment parameter input modes, the appropriate mode can be selected according to the actual situation, so as to ensure the flexibility and practicality of parameter input; further, it has dynamic response capability, which can provide basis for subsequent real-time update of boundary conditions, adapt to the situation of aircraft maneuvering flight and rapid change of flight environment.

[0062] In this embodiment, according to the type of dynamic flow parameter of aircraft and the different reading modes, the dynamic flow parameter conversion and storage method is constructed to realize the unified processing of flow field dynamic flow parameter. Specifically, for the application range of dynamic flow boundary, it is mainly used for the calculation process of unsteady flow under complex scene such as high maneuvering flight of aircraft. Different flight scenes will cause great difference in the type of dynamic flow parameter, and different combinations of dynamic flow parameters may have different reading, conversion and storage methods, resulting in low code reusability and low calling efficiency. Therefore, a relatively flexible and widely applicable data conversion method and unified data storage method need to be constructed, which is applicable to flow parameters including but not limited to: flow velocity, Mach number, temperature, density, pressure, height, component mass fraction, angle of attack, side slip angle, etc.

[0063] In this embodiment, after the dynamic flow parameter is read by the general file reading interface ReadBCParaFile(), the data is converted and the unified data storage is completed, and the specific operation is as follows:

[0064] First, the inflow parameter type identification is performed. Generally, in the process of performing the flow field numerical calculation, in order to ensure the correctness of the calculation, the integrity of the flow field initial parameters must be ensured, and the reference parameters of density, X / Y / Z direction velocity, pressure and temperature must exist. However, the type combination of the obtained parameters is not necessarily to simultaneously give the above-mentioned reference variables, and there are multiple possibilities for the parameter type combination, such as "Mach number - flight height", "Mach number - Reynolds number - temperature", "total temperature - total pressure", etc. If directly input to the main program, it will cause parameter identification exception and error. Therefore, the parameter conversion interface parameterConversion() is established here to realize the conversion of the uncertain inflow parameter type combination into the inflow parameter combination composed of reference parameters, thereby facilitating the direct calling of the program.

[0065] Secondly, the reference inflow parameter database is constructed to persistently store the target reference parameter combination; it can be understood that, based on the name and type of the inflow parameter, the converted data in the target reference parameter combination obtained after the conversion through the parameterConversion() interface is stored in the database named GlobalDataBase. In the subsequent unsteady calculation, according to the different scientific problems to be studied, only the reference parameters are read from the database in different combination modes, thereby avoiding the repeated process of reading parameters from external files and conversion, and improving the calculation efficiency.

[0066] Finally, when receiving a data reading request, the target reference parameter corresponding to the data reading request is read from the reference inflow parameter database. In this step, the reference parameters obtained after the dynamic inflow parameter unification are mainly taken out from the database, the required inflow parameter combination is taken out, the inflow boundary value of the aircraft is updated, thereby realizing the dynamic change of the inflow parameter in the real flow environment of the aircraft with time (i.e. dynamic assignment of the initial value of the inflow boundary), completing the t0 to t1 unsteady simulation calculation, and further more accurately capturing the details of the change of the flow field aerodynamic characteristics and aerodynamic thermal environment, and providing reliable numerical calculation results for engineering design, scientific research analysis and system optimization.

[0067] As can be seen, starting from the real-time dynamic feedback of the aircraft motion state and the flight environment parameters, a dynamic inflow boundary data input system combining the self-defined setting of the flight parameters and the reading from the external parameter file is specifically constructed, the uniformity of the data format of the two input modes and the repeatability of the code are ensured through the construction of the unified data structure, the practicability of the engineering type research is possessed, and it has important significance for capturing the unsteady flow field characteristic information of the aircraft.

[0068] It can be seen that the application discloses a dynamic inflow boundary construction method based on aircraft flow field simulation, comprising: selecting a target inflow boundary parameter type and a combination mode according to a current maneuvering state of a current aircraft and a current flight environment change; determining a corresponding target input mode according to the target inflow boundary parameter type; wherein the target input mode is used to determine a reading mode and a dynamic change process of a dynamic inflow boundary parameter; reading a time-varying dynamic inflow boundary parameter sequence from an external configuration source based on the target input mode and through a preset external data reading interface, and converting the dynamic inflow boundary parameter sequence into a target reference parameter combination according to a reference parameter type of initialization flow field information and the combination mode, and then replacing corresponding parameter values in an inflow boundary area with the target reference parameter combination to complete construction of the dynamic inflow boundary. It can be seen that, by combining real-time maneuvering state and environmental change, it is ensured that the selected parameter type and combination are highly matched with an actual scene, and introduction of redundant or irrelevant parameters is avoided. By matching the parameter type with the input mode, the reading mode and the change process of the dynamic inflow boundary parameter are adapted to the parameter characteristics, flexibility of parameter input is enhanced, different scenes with different dynamic change laws can be adapted, and limitations of a single input mode are avoided. By reading the time-varying parameter sequence through the preset interface, real-time performance of the parameter source is ensured; by converting into the reference parameter combination, it is ensured that the parameter format is consistent with flow field simulation requirements, and calculation errors caused by format incompatibility are avoided; by replacing the parameter values in the inflow boundary area, dynamic updating of the inflow boundary is directly realized, and limitations of parameter fixation of the static boundary are broken. By dynamically adapting the aircraft maneuvering state and the flight environment change, targeted selection, flexible input and real-time updating of the inflow boundary parameter are realized, dynamic changes of the inflow parameter over time can be accurately captured, adaptability and simulation accuracy of the aircraft flow field simulation to a complex flight scene are improved, and flow field simulation requirements under high maneuvering flight or a complex atmospheric environment are met.

[0069] Referring to Figure 4 The application also discloses a dynamic inflow boundary construction device based on aircraft flow field simulation, comprising:

[0070] A type selection module 11 is configured to select a target inflow boundary parameter type and a combination mode according to a current maneuvering state of a current aircraft and a current flight environment change.

[0071] A mode selection module 12 is configured to determine a corresponding target input mode according to the target inflow boundary parameter type; wherein the target input mode is used to determine a reading mode and a dynamic change process of a dynamic inflow boundary parameter.

[0072] The inflow boundary construction module 13 is configured to read a time-varying dynamic inflow boundary parameter sequence from an external configuration source based on the target input mode and through a preset external data reading interface, convert the dynamic inflow boundary parameter sequence into a target reference parameter combination according to a reference parameter type of initialized flow field information and the combination mode, and replace corresponding parameter values in an inflow boundary region with the target reference parameter combination to complete construction of the dynamic inflow boundary.

[0073] It can be seen that the application discloses selection of a target inflow boundary parameter type and a combination mode according to a current maneuvering state of a current aircraft and a current flight environment change, determination of a corresponding target input mode according to the target inflow boundary parameter type, wherein the target input mode is used to determine a reading mode and a dynamic change process of a dynamic inflow boundary parameter, reading of a time-varying dynamic inflow boundary parameter sequence from an external configuration source based on the target input mode and through a preset external data reading interface, conversion of the dynamic inflow boundary parameter sequence into a target reference parameter combination according to a reference parameter type of initialized flow field information and the combination mode, and replacement of corresponding parameter values in an inflow boundary region with the target reference parameter combination to complete construction of the dynamic inflow boundary. It can be seen that, by combining a real-time maneuvering state and an environment change, the selected parameter type and combination are ensured to be highly matched with an actual scene, and introduction of redundant or irrelevant parameters is avoided. By matching the parameter type and the input mode, the reading mode and the change process of the dynamic inflow boundary parameter are adapted to the parameter characteristics, flexibility of parameter input is enhanced, different scenes with different dynamic change rules can be adapted to, and limitations of a single input mode are avoided. By reading the time-varying parameter sequence through the preset interface, real-time performance of a parameter source is ensured. By conversion into the reference parameter combination, the parameter format is ensured to be consistent with a flow field simulation requirement, and calculation errors caused by format incompatibility are avoided. By replacement of the parameter values in the inflow boundary region, dynamic update of the inflow boundary is directly implemented, and limitations of parameter fixation of a static boundary are broken. By dynamic adaptation of the maneuvering state of the aircraft and the flight environment change, targeted selection, flexible input and real-time update of the inflow boundary parameter are implemented, dynamic changes of inflow parameters over time can be accurately captured, adaptability and simulation accuracy of flow field simulation of the aircraft to a complex flight scene are improved, and flow field simulation requirements under high maneuvering flight or a complex atmospheric environment are met.

[0074] Further, the application also discloses an electronic device, Figure 5 Fig. 1 is a structural diagram of an electronic device 20 according to an example embodiment, and the content in the figure should not be considered as any limitation on the use range of the application.

[0075] Figure 5A structural schematic diagram of an electronic device 20 is provided in the embodiments of the present application. The electronic device 20 can 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 configured to store a computer program, and the processor 21 is configured to load and execute the computer program to implement the related steps in the method for constructing a dynamic flow boundary based on a flow field simulation of an aircraft disclosed in any of the foregoing embodiments. In addition, the electronic device 20 in the embodiments of the present application can be specifically an electronic computer.

[0076] In the embodiments of the present application, the power supply 23 is configured to provide working voltage for each hardware device on the electronic device 20; the communication interface 24 is capable of creating a data transmission channel between the electronic device 20 and external devices, and the communication protocol followed by the communication interface 24 can be any communication protocol applicable to the technical solutions of the present application, which is not specifically limited herein; the input / output interface 25 is configured to obtain external input data or output data to the outside, and the specific interface type can be selected according to the specific application needs, which is not specifically limited herein.

[0077] The processor 21 can include one or more processing cores, such as a 4-core processor, an 8-core processor, etc. The processor 21 can be implemented in at least one of a hardware form of a DSP (Digital Signal Processing), an FPGA (Field-Programmable Gate Array) and a PLA (Programmable Logic Array). The processor 21 can also include a main processor and a coprocessor. The main processor is a processor for processing data in a wake-up state, also known as a CPU (Central Processing Unit). The coprocessor is a low-power processor for processing data in a standby state. In some embodiments, the processor 21 can be integrated with a GPU (Graphics Processing Unit) that is responsible for rendering and drawing the content to be displayed on the display screen. In some embodiments, the processor 21 can further include an AI (Artificial Intelligence) processor for processing machine learning-related computing operations.

[0078] In addition, the memory 22 as a carrier for resource storage can be a read-only memory, a random access memory, a magnetic disk or an optical disk, etc. The resources stored thereon can include an operating system 221, a computer program 222, etc., and the storage mode can be temporary storage or permanent storage.

[0079] The operating system 221 is used to manage and control each hardware device on the electronic device 20 and the computer program 222, so as to realize the operation and processing of the processor 21 on the mass data 223 in the memory 22, which can be Windows Server, Netware, Unix, Linux, etc. In addition to the computer program capable of completing the method for constructing the dynamic flow boundary based on the aircraft flow field simulation disclosed in any one of the foregoing embodiments executed by the electronic device 20, the computer program 222 can further include a computer program capable of completing other specific work. In addition to the data transmitted by the external device and received by the electronic device, the data 223 can also include the data collected by the self input / output interface 25, etc.

[0080] Further, the application also discloses a computer readable storage medium for storing a computer program; wherein the computer program is executed by the processor to realize the method for constructing the dynamic flow boundary based on the aircraft flow field simulation disclosed in the foregoing. The specific steps of the method can refer to the corresponding contents disclosed in the foregoing embodiments, which will not be described here.

[0081] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred 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 the relevant part can refer to the method part.

[0082] Those skilled in the art will further appreciate that the units and algorithm steps of the examples described in connection with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or any combination thereof. To clearly illustrate the interchangeability of hardware and software, various components have been described above generally in terms of their functionality, without limitation. The handwiring and software implementations of the examples described herein could be accomplished using any number of microprocessors, microcontrollers, programmable consumption logic devices, application-specific integrated circuits, or general-purpose computers with interconnecting circuits that either run software programs or use opencircuit or other hardware components that are designed to perform the functions described herein. The embodiments described herein can be implemented along with software modules, and the software modules can be stored on any of a variety of non-transitory machine-readable media. A non-transitory machine-readable medium includes any medium that participates in providing instructions to a processor for execution. Such a medium can take many forms, including but not limited to, non-volatile media, volatile media, and transmission media. Non-volatile media includes, for example, optical or magnetic disks and other persistent memory. Volatile media includes dynamic memories, and physical registers. Transmission media includes coaxial cables, copper wires and fiber optic cables, including wires that comprise bus conductors. Transmission media also can also take the form of acoustic or light waves, such as those generated during radio frequency (RF) and infrared (IR) data communications. Common forms of computer-readable media include, for example, a floppy disk, a flexible disk, hard disk, solid-state drive, magnetic tape, or any other magnetic data storage medium, a Compact Disc - Read Only Memory (CD-ROM), any other optical medium, punch cards, paper tape, any other physical medium with patterns of holes, a RAM, a programmable ROM (PROM), an erasable PROM (EPROM), a FLASH-EPROM, any other memory chip or cartridge, a carrier wave, a

[0083] Finally, it should also be noted that, in the present text, relational terms such as first and second and the like can only be used to distinguish one entity or operation from another entity or operation, without necessarily requiring or implying any such actual relationship or order between such entities or operations. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by an occurrence of the phrase "comprising a" does not exclude the presence of additional identical elements in the process, method, article, or apparatus that includes the element.

[0084] The above has carried on the detailed introduction to the scheme provided by the present application, the principle and implementation mode of the present application are described by applying the specific examples in the present text, the above example explanation is only applicable to help understanding the method and core idea of the present application; simultaneously, for the general technical personnel in the field, according to the idea of the present application, there will be the change in the specific implementation mode and application range, the above-mentioned content should not be understood as the limitation of the present application.

Claims

1. A method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation, characterized in that: include: According to the current maneuvering state of the current aircraft and the current flight environment changes, the target flow boundary parameter type and combination method are selected; Determining a corresponding target input mode according to the target incoming flow boundary parameter type; wherein the target input mode is used to determine the reading method and dynamic change process of the dynamic incoming flow boundary parameter; Based on the target input mode and through a preset external data reading interface, a dynamic incoming flow boundary parameter sequence that varies in time is read from an external configuration source, and the dynamic incoming flow boundary parameter sequence is converted into a target reference parameter combination according to the reference parameter type of the initialization flow field information and the combination method, and then the target reference parameter combination is used to replace the corresponding parameter values ​​in the incoming flow boundary area to complete the construction of the dynamic incoming flow boundary; The method of reading a dynamic incoming flow boundary parameter sequence that changes in time from an external configuration source through a preset external data reading interface based on the target input mode includes: Based on the function relation input mode and through a preset external data reading interface, a relation set representing the time-varying state parameters of the aircraft and / or a relation set representing the time-varying atmospheric environment parameters of the aircraft are read from the function relation configuration file to obtain a dynamic incoming flow boundary parameter sequence; The method of obtaining a dynamic incoming flow boundary parameter sequence by reading a set of relational expressions representing the time-varying state parameters of an aircraft and / or a set of relational expressions representing the time-varying atmospheric environment parameters of an aircraft from a function relational expression configuration file based on a function relational expression input mode and through a preset external data reading interface includes: Based on the functional relationship input mode, the number of incoming flow parameters, the functional relationship between each incoming flow parameter and time, and the initial value of each incoming flow parameter are read from the functional relationship configuration file through a preset external data reading interface, and parsed to obtain a set of relationship formulas for the change of aircraft state parameters over time and / or a set of relationship formulas for the change of aircraft atmospheric environment parameters over time; A set of dynamic incoming flow boundary parameters over time is generated according to a set of relationship expressions of the aircraft state parameters changing over time and / or a set of atmospheric environment parameters where the aircraft is located changing over time, so as to obtain a dynamic incoming flow boundary parameter sequence.

2. The method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation according to claim 1, characterized in that: Before selecting the target incoming flow boundary parameter type and combination method according to the current maneuvering state of the current aircraft and the current flight environment change, the method further includes: The geometrical shape model of the current aircraft is determined, a computational grid on the geometrical shape model is generated, and initialization flow field information including an incoming flow boundary region in the computational grid is obtained.

3. The method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation according to claim 2, characterized in that: The step of determining a geometrical shape model of the current aircraft, generating a computational grid on the geometrical shape model, and obtaining initialization flow field information of an incoming flow boundary region in the computational grid includes: Performing CAD modeling processing on the current aircraft to obtain a geometric shape model of the current aircraft; Performing computational grid generation processing on the geometric shape model, and generating boundary condition types of the computational grid in different computational grid areas according to flow field simulation requirement information; Based on the boundary condition type, the area where the incoming flow boundary is located is determined from the calculation grid to obtain the incoming flow boundary area, and the initialization flow field information of the calculation grid is obtained.

4. The method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation according to claim 1, characterized in that: The target input mode is a function relation input mode or a parameter list input mode.

5. The method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation according to claim 4, characterized in that: The method of reading a dynamic incoming flow boundary parameter sequence that changes in time from an external configuration source through a preset external data reading interface based on the target input mode includes: Based on the parameter list input mode, structured aircraft parameters representing different aircraft parameter categories are read from a parameter list configuration file through a preset external data reading interface to obtain a dynamic incoming flow boundary parameter sequence.

6. The method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation according to claim 5, characterized in that: The method of reading structured aircraft parameters representing different aircraft parameter categories from a parameter list configuration file based on the parameter list input mode and through a preset external data reading interface to obtain a dynamic incoming flow boundary parameter sequence includes: Based on the parameter list input mode, the structured flight parameters of the aircraft attitude parameter category, motion parameter category, and atmospheric parameter category at different times are read from the parameter list configuration file through a preset external data reading interface to obtain a dynamic incoming flow boundary parameter sequence; wherein, the structured flight parameters include the number, name, type, and corresponding numerical value of the parameters.

7. The method for constructing a dynamic incoming flow boundary based on aircraft flow field simulation according to any one of claims 1 to 6, characterized in that: Also includes: Build a benchmark flow parameter database to persistently store target benchmark parameter combinations; When a data read request is received, the target reference parameter corresponding to the data read request is read from the reference incoming flow parameter database.

8. A dynamic incoming flow boundary construction device based on aircraft flow field simulation, characterized in that: include: The type selection module is used to select the target flow boundary parameter type and combination method according to the current maneuvering state of the current aircraft and the current flight environment changes; A mode selection module, configured to determine a corresponding target input mode according to the target incoming flow boundary parameter type; wherein the target input mode is used to determine a reading method and a dynamic change process of the dynamic incoming flow boundary parameter; An incoming flow boundary construction module is configured to read a time-varying dynamic incoming flow boundary parameter sequence from an external configuration source through a preset external data reading interface based on the target input mode, convert the dynamic incoming flow boundary parameter sequence into a target reference parameter combination according to the reference parameter type of the initial flow field information and the combination method, and then use the target reference parameter combination to replace the corresponding parameter values ​​in the incoming flow boundary area to complete the construction of the dynamic incoming flow boundary; The incoming flow boundary construction module is specifically configured to read a set of relational expressions representing the time-varying state parameters of the aircraft and / or the time-varying atmospheric environment parameters of the aircraft from a function relational expression configuration file through a preset external data reading interface based on a function relational expression input mode, so as to obtain a dynamic incoming flow boundary parameter sequence; The dynamic incoming flow boundary construction device is specifically used to read the number of incoming flow parameters, the functional relationship between each incoming flow parameter and time, and the initial value of each incoming flow parameter from a functional relationship configuration file through a preset external data reading interface based on a functional relationship input mode, and parse to obtain a set of relationship formulas for the change of aircraft state parameters over time and / or a set of relationship formulas for the change of aircraft atmospheric environment parameters over time; generate a set of dynamic incoming flow boundary parameters over time based on the set of relationship formulas for the change of aircraft state parameters over time and / or the change of aircraft atmospheric environment parameters over time to obtain a dynamic incoming flow boundary parameter sequence.

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