Intake plugging cone design method, device, storage medium and electronic equipment

Abstract

The embodiments of the present application disclose a method, device, storage medium and electronic device for designing an intake cone plug, which relates to the field of aircraft manufacturing technology, including: obtaining external drag data of the target aircraft in a clean state based on a simulation model of a target cone plug; adjusting the degree of a given cone angle according to the number of steps corresponding to the external drag error data, and returning to the simulation model based on the target cone plug to obtain the external drag data of the target aircraft in a clean state, until the external drag error data meets the termination condition, and the target cone angle is obtained. The present application uses the external drag coefficient in the intake working state and the external drag coefficient of the intake cone plug in a clean state as the card control, and uses the external drag error data as the basis and cooperates with the cyclic optimization of parameters to adjust the degree of a given cone angle, so that the external flow field characteristics of the entire aircraft in different states are highly consistent, which can effectively improve the quality of the intake cone plug design.

Description

Technical Field

[0001] The present application relates to the field of aircraft manufacturing technology, and in particular to an air intake plugging cone design method, device, storage medium and electronic equipment. Background Art

[0002] A reasonable intake cone is the basis for obtaining accurate aerodynamic data in the early stage of rapid model design and full-machine force measurement experiments, and can approximate the actual external flow field characteristics during flight. However, the current design method does not consider the impact of the inlet duct, lip, etc. on the external flow field of the entire aircraft when the aircraft is working near the design point, especially in the supersonic design state, the resistance of the intake cone state can be more than 30% greater than the actual flight state, resulting in serious deviations in model design. Therefore, it is urgent to improve the design quality of the intake cone. Summary of the invention

[0003] The main purpose of the present application is to provide an air intake plugging cone design method, device, storage medium and electronic device, aiming to solve the problem of poor quality of air intake plugging cone design in the prior art.

[0004] To achieve the above objectives, the technical solutions adopted in the embodiments of the present application are as follows:

[0005] In a first aspect, an embodiment of the present application provides a method for designing an air intake cone, comprising the following steps:

[0006] Based on the simulation model of the target blocking cone, the external drag data of the target aircraft in a clean state is obtained; wherein the simulation model is obtained based on a given cone angle of the target blocking cone;

[0007] According to the number of steps corresponding to the external resistance error data, the degree of the given cone angle is adjusted, and the simulation model based on the target blocking cone is returned to obtain the steps of the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and the target cone angle is obtained; wherein the external resistance error data is obtained according to the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

[0008] In a possible implementation of the first aspect, before adjusting the degree of a given cone angle according to the step number corresponding to the external resistance error data, the intake cone blocking design method further includes:

[0009] According to the pressure boundary of the outlet static pressure data of the air inlet, a simulation model of the target aircraft in the air intake state is established;

[0010] According to the simulation model of the target aircraft in the air intake state, the external drag coefficient of the target aircraft in the air intake state is obtained.

[0011] In a possible implementation of the first aspect, before establishing a simulation model of the target aircraft in an intake state according to a pressure boundary of the outlet static pressure data of the intake duct, the intake cone design method further includes:

[0012] According to the pressure wind tunnel test results of the air inlet of the target aircraft, the outlet static pressure data of the air inlet is obtained.

[0013] In a possible implementation of the first aspect, before adjusting the degree of a given cone angle according to the step number corresponding to the external resistance error data, the intake cone blocking design method further includes:

[0014] The external drag error data is obtained according to the external drag coefficient of the target aircraft in the intake state and the external drag coefficient of the target aircraft in the clean state.

[0015] In a possible implementation manner of the first aspect, the external resistance error data is calculated according to the following formula:

[0016] δ=|C D2 / C D1 -1|

[0017] Among them, δ is the external resistance error data, C D2 is the external drag coefficient of the target aircraft in a clean state, C D1 is the external drag coefficient of the target aircraft in the intake state.

[0018] In a possible implementation of the first aspect, adjusting the degree of a given cone angle according to the stepping degree corresponding to the external resistance error data includes:

[0019] Determine the stepping frequency according to the external resistance error data;

[0020] Increases or decreases the step size by the given cone angle in degrees to adjust the given cone angle in degrees.

[0021] In a possible implementation of the first aspect, the stepping frequency is determined according to the external resistance error data, according to the following formula:

[0022]

[0023] Among them, dθ is the step number, and δ is the external resistance error data.

[0024] In a second aspect, an embodiment of the present application provides an air intake cone design device, comprising:

[0025] An acquisition module, the acquisition module is used to obtain the external drag data of the target aircraft in a clean state based on a simulation model of the target blocking cone; wherein the simulation model is obtained based on a given cone angle of the target blocking cone;

[0026] The loop module is used to adjust the degree of a given cone angle according to the number of steps corresponding to the external resistance error data, and return a simulation model based on the target blocking cone to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and obtain the target cone angle; wherein the external resistance error data is obtained based on the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

[0027] In a third aspect, an embodiment of the present application provides a computer-readable storage medium storing a computer program. When the computer program is loaded and executed by a processor, the intake plugging cone design method provided in any one of the first aspects above is implemented.

[0028] In a fourth aspect, an embodiment of the present application provides an electronic device, including a processor and a memory, wherein:

[0029] The memory is used to store computer programs;

[0030] The processor is used to load and execute a computer program so that the electronic device executes the air intake plugging cone design method provided in any one of the first aspects above.

[0031] Compared with the prior art, the beneficial effects of this application are:

[0032] An embodiment of the present application proposes an intake cone design method, device, storage medium and electronic device, the method comprising: obtaining external resistance data of a target aircraft in a clean state based on a simulation model of a target cone; wherein the simulation model is obtained based on a given cone angle of the target cone; adjusting the degree of the given cone angle according to the step number corresponding to the external resistance error data, and returning to the simulation model based on the target cone to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and the target cone angle is obtained; wherein the external resistance error data is obtained based on the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state. The present application considers the interference characteristics of the external flow field of the aircraft when the air inlet duct is working in the aircraft intake state at the initial stage of design, takes the external drag coefficient in the intake working state and the external drag coefficient of the intake plugging cone in the clean state as the control, takes the external drag error data as the basis and cooperates with the cyclic optimization of the parameters to step-by-step adjust the degree of the given cone angle so that the external flow field characteristics of the whole aircraft in the clean state, that is, with the air inlet plugging cone, are highly consistent with the external flow field characteristics of the whole aircraft in the intake working state of the target aircraft. The intake plugging cone is designed with the target cone angle optimized at this time as a parameter, which can effectively improve the quality of the intake plugging cone design, and thus provide better data support for the design of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1A schematic diagram of the structure of an electronic device of a hardware operating environment involved in an embodiment of the present application;

[0034] Figure 2 A schematic diagram of a flow chart of an air intake plugging cone design method provided in an embodiment of the present application;

[0035] Figure 3 A schematic diagram of a flow chart of an intake cone blocking design method provided in an embodiment of the present application in one implementation manner;

[0036] Figure 4 A schematic diagram of the composition of the external resistance of the entire machine in the intake state in the intake cone design method provided in the embodiment of the present application;

[0037] Figure 5 A schematic diagram of the external resistance composition of the entire machine when the plugging cone is in a clean state in the intake plugging cone design method provided in an embodiment of the present application;

[0038] Figure 6 A curve chart of the results of the wind tunnel test of the air intake pressure measurement in the air intake cone design method provided in the embodiment of the present application;

[0039] Figure 7 A schematic diagram of parameterization of an air intake plugging cone in the air intake plugging cone design method provided in an embodiment of the present application;

[0040] Figure 8 An optimized convergence curve diagram of the air intake plugging cone in the air intake plugging cone design method provided in an embodiment of the present application;

[0041] Fig. 9 A schematic diagram of a module of an air intake cone blocking design device provided in an embodiment of the present application;

[0042] Markings in the figure: 101 - processor, 102 - communication bus, 103 - network interface, 104 - user interface, 105 - memory. DETAILED DESCRIPTION

[0043] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0044] The main solution of the embodiment of the present application is: based on the simulation model of the target blocking cone, the external resistance data of the target aircraft in a clean state is obtained; wherein, the simulation model is obtained based on the given cone angle of the target blocking cone; according to the step number corresponding to the external resistance error data, the degree of the given cone angle is adjusted, and the simulation model based on the target blocking cone is returned to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and the target cone angle is obtained; wherein, the external resistance error data is obtained based on the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

[0045] A reasonable intake plug is the basis for obtaining accurate aerodynamic data in the early stage of rapid model design and full-machine force measurement experiments, and can approximate the actual external flow field characteristics during flight. At present, there are two main methods for designing intake plugs: one is to use the fuselage dug out during the design of the intake duct as the intake plug; the other is to add a cone in front of the air inlet. For the aircraft model with head intake, it is a 30° cone cut at the lip of the air inlet, and for the aircraft model with side or belly intake, it is a 15° half cone cut at the lip of the air inlet.

[0046] However, the design of the air intake plug cone rarely considers the impact of the air intake duct, lip, etc. on the external flow field of the entire aircraft when the aircraft is working near the design point. Especially in the supersonic design state, the resistance of the air intake plug cone state can be more than 30% greater than the actual flight state, which leads to serious deviations in model design iterations and wind tunnel data, directly restricting flight performance. Therefore, in order to obtain aerodynamic data closer to the actual flight state, the air intake plug cone must be optimized.

[0047] In the existing technology, the optimization design of the intake plug cone relies on fluid mechanics theory, experimental fluid mechanics methods, and computational fluid dynamics (CFD) methods. The influence of the intake plug cone on the external resistance of the whole aircraft, especially the quantitative evaluation of the external resistance of the whole aircraft, is rarely involved in fluid mechanics theory; the implementation in experimental fluid mechanics is difficult, costly, has a long design cycle, and it is difficult to obtain flow field information, which seriously limits the model design progress and cost control; and with the development and continuous improvement of CFD theory and computer technology, computational fluid dynamics methods have many advantages such as complete flow field information, easy to obtain component forces, low cost, and short cycle. It can clearly observe the details of the flow field inside and outside the aircraft, facilitate the analysis of aerodynamic mechanisms, and provide technical support for the optimization design of the intake plug cone.

[0048] To this end, the present application provides a solution. At the initial stage of design, the interference characteristics of the external flow field of the aircraft when the air inlet duct is working in the aircraft intake state are considered. The external drag coefficient in the intake working state and the external drag coefficient of the intake plugging cone in the clean state are used as the control. Based on the external resistance error data and in conjunction with the cyclic optimization of the parameters, the degree of the given cone angle is adjusted in a step-by-step manner to make the external flow field characteristics of the entire aircraft in the clean state, that is, with the air inlet plugging cone, highly consistent with the external flow field characteristics of the entire aircraft in the intake working state of the target aircraft. The air inlet plugging cone is designed with the target cone angle optimized at this time as a parameter, which can effectively improve the quality of the air inlet plugging cone design, and thus provide better data support for the design of the aircraft.

[0049] See attached Figure 1 , attached Figure 1This is a schematic diagram of the structure of an electronic device of the hardware operating environment involved in the embodiment of the present application. The electronic device may include: a processor 101, such as a central processing unit (CPU), a communication bus 102, a user interface 104, a network interface 103, and a memory 105. Among them, the communication bus 102 is used to realize the connection and communication between these components. The user interface 104 may include a display screen (Display), an input unit such as a keyboard (Keyboard), and the user interface 104 may also include a standard wired interface and a wireless interface. The network interface 103 may optionally include a standard wired interface and a wireless interface (such as a wireless fidelity (WIreless-FIdelity, WI-FI) interface). The memory 105 may optionally be a storage device independent of the aforementioned processor 101. The memory 105 may be a high-speed random access memory (RAM) or a stable non-volatile memory (NVM), such as at least one disk storage; the processor 101 may be a general-purpose processor, including a central processing unit, a network processor, etc., or may be a digital signal processor, an application-specific integrated circuit, a field programmable gate array or other programmable logic device, a discrete gate or transistor logic device, or a discrete hardware component.

[0050] Those skilled in the art will appreciate that Figure 1 The structure shown in the figure does not constitute a limitation on the electronic device, and may include more or less components than shown in the figure, or combine certain components, or arrange the components differently.

[0051] As attached Figure 1 As shown, the memory 105 as a storage medium may include an operating system, a network communication module, a user interface module, and an air intake cone design device.

[0052] In the attached Figure 1 In the electronic device shown, the network interface 103 is mainly used for data communication with the network server; the user interface 104 is mainly used for data interaction with the user; the processor 101 and the memory 105 in the present application can be set in the electronic device, and the electronic device calls the air intake cone design device stored in the memory 105 through the processor 101, and executes the air intake cone design method provided in the embodiment of the present application.

[0053] See attached Figure 2 Based on the hardware device of the aforementioned embodiment, the embodiment of the present application provides a method for designing an air intake cone, comprising the following steps:

[0054] S10: Based on the simulation model of the target blocking cone, external drag data of the target aircraft in a clean state is obtained; wherein the simulation model is obtained based on a given cone angle of the target blocking cone.

[0055] In the specific implementation process, the embodiment of the present application is optimized based on the existing model of the air intake plug cone, and the target plug cone is the air intake plug cone that needs to be optimized. Given the cone angle θ of the air intake plug cone tangent to the lip, that is, given the cone angle, determine the position of the fuselage base point in front of the air inlet on the symmetry plane, and establish the air intake plug cone section through the B-spline curve and multi-section surface commands. The CATIA secondary development is called through the VB program, and the purpose of parameterizing the air intake plug cone model is achieved by changing the cone angle θ. Then, a CFD simulation model is established based on the model, and the external resistance data of the air intake plug cone in the clean state is obtained by integration, which is recorded as D2. The clean state is the state after the air intake is blocked by the air intake plug cone based on the original model.

[0056] S20: According to the number of steps corresponding to the external resistance error data, adjust the degree of the given cone angle, and return to the simulation model based on the target blocking cone to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and obtain the target cone angle; wherein the external resistance error data is obtained based on the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

[0057] In the specific implementation process, the external drag error data is obtained by combining the external drag coefficient of the target aircraft in the intake state with the external drag coefficient of the target aircraft in the clean state. The target aircraft is the aircraft model where the intake cone is designed. The external drag coefficient of the target aircraft in the intake state is recorded as C D1 , based on the external drag D1 of the target aircraft in the intake state, similarly, the external drag coefficient of the target aircraft in the clean state is recorded as C D2 , based on the external resistance data D2 of the intake cone in a clean state. The step number is the degree of increase or decrease in each cycle, that is, the cone angle θ is controlled by a successive approximation algorithm, and the above steps are repeated to obtain high-quality parameters, that is, parameters that meet the termination conditions.

[0058] The external resistance error data is calculated using the following formula:

[0059] δ=|C D2 / C D1 -1|

[0060] Among them, δ is the external resistance error data, C D2 is the external drag coefficient of the target aircraft in a clean state, C D1 is the external drag coefficient of the target aircraft in the intake state.

[0061] According to the external resistance error data, determine the step frequency according to the following formula:

[0062]

[0063] Among them, dθ is the stepping frequency, and δ is the external resistance error data. Whether the stepping frequency is increased or decreased is determined according to the actual situation, whether it is forward optimization or reverse optimization. For example, if the given initial cone angle degree is large, the stepping frequency is negative, that is, the given cone angle degree is reduced; conversely, if the given initial cone angle degree is small, the stepping frequency is positive, that is, the given cone angle degree is increased. That is: according to the stepping frequency corresponding to the external resistance error data, the degree of the given cone angle is adjusted, including:

[0064] Determine the stepping frequency according to the external resistance error data;

[0065] Increases or decreases the step size by the given cone angle in degrees to adjust the given cone angle in degrees.

[0066] In one embodiment, before adjusting the degree of a given cone angle according to the step number corresponding to the external resistance error data, the intake cone blocking design method further includes:

[0067] According to the pressure wind tunnel test results of the air inlet of the target aircraft, the outlet static pressure data of the air inlet is obtained;

[0068] According to the pressure boundary of the outlet static pressure data of the air inlet, a simulation model of the target aircraft in the air intake state is established;

[0069] According to the simulation model of the target aircraft in the air intake state, the external drag coefficient of the target aircraft in the air intake state is obtained.

[0070] In this embodiment, the corresponding flow coefficient φ is obtained by interpolation based on the results of the inlet pressure wind tunnel test 目标 The total inlet pressure recovery coefficient σ under the condition of , the inlet outlet static pressure p can be obtained by the following formula:

[0071]

[0072] p 0∞ =(1+0.2Ma 2 ) 3.5 ·p ∞ , T 0∞ =(1+0.2Ma 2 )·T ∞

[0073]

[0074] q(λ)=(1.2-0.2·λ 2 ) 2.5 ·λ

[0075]

[0076] in, is the engine conversion flow; T ∞ 、T 0∞ , ∞ 、p ∞ 、p 0∞ are the far-field incoming flow temperature, total temperature, density, static pressure and total pressure respectively; A 参考 The reference area is generally the frontal area of ​​the inlet at zero angle of attack; q(λ) and λ are the gas function and velocity coefficient respectively. Then, a CFD simulation model of the intake state is established through the inlet outlet pressure boundary, and the total machine resistance D1 under the design working state is calculated.

[0077] In this embodiment, by considering the interference characteristics of the external flow field of the aircraft when the air inlet duct is working in the aircraft intake state at the initial stage of design, the external drag coefficient in the intake working state and the external drag coefficient of the intake plugging cone in the clean state are used as control, and based on the external resistance error data and in conjunction with the cyclic optimization of parameters, the degree of the given cone angle is adjusted in a step-by-step manner, so that the external flow field characteristics of the entire aircraft in the clean state, that is, with the air inlet plugging cone, are highly consistent with the external flow field characteristics of the entire aircraft in the intake working state of the target aircraft. The air inlet plugging cone is designed with the target cone angle optimized at this time as a parameter, which can effectively improve the quality of the air inlet plugging cone design, and thus provide better data support for the design of the aircraft.

[0078] See attached Figure 3-8 Taking a supersonic, belly-intake UAV as an example, the optimization design process of the intake cone is as follows:

[0079] As attached Figure 4 , 5 As shown in the figure, the aircraft is disassembled into parts in the intake state and the clean state of the plug cone to determine the composition of the external resistance of the whole aircraft. Body is the fuselage, Wing is the wing, Tail is the tail, Vtail is the V-shaped tail, Bump is the bulge, Lip is the lip, and Cone is the intake plug cone. The resistance of the intake state is divided. The aerodynamic external resistance D of the aircraft can be expressed as:

[0080] D=D ab +D ex

[0081] D ab =D body +D wing +D tail

[0082] D ex =D spill =Dadd +D cowl

[0083]

[0084] Among them, D ab is the body resistance, mainly including the body resistance D body , Wing resistance D wing , tail drag D tail ;D in , D ex They are the internal resistance of the intake duct and the external resistance of the intake duct, among which the external resistance of the intake duct D ex The additional resistance D add , outer cover resistance D cowl (In addition, the clamshell inlet also has bulge resistance D bump ), namely, the overflow resistance D spill ; p, A, V are the average pressure, cross-sectional area and airflow velocity of the inlet outlet section, p ∞ 、V ∞ is the pressure and velocity of the flow from infinity, is the mass flow rate of air through the intake duct.

[0085] According to the definition of overflow resistance, overflow resistance is:

[0086] D spill =(D add +D cowl ) φ≠1 -(D add +D cowl ) φ＝1

[0087] The external resistance D1 in flight working state is:

[0088] D1=(D ab +D add +D cowl ) φ≠1 -(D cowl ) φ＝1

[0089] Among them, the flow coefficient φ is the actual captured flow in the inlet duct Capture flow with theory The ratio of, that is, under the external flow field characteristics, the external resistance in the flight working state does not include the internal resistance of the inlet duct.

[0090] Resistance division in clean state (with air intake plug). At this time, the aircraft external resistance D2 is equal to the total aircraft resistance D, and the calculation formula is:

[0091] D2=D' ab +D cone

[0092] Among them, D' ab D is the fuselage resistance after the fuselage area is reduced due to the intake cone. cone It is the resistance of the intake cone.

[0093] As attached Figure 3 As shown in the flowchart, on the one hand, the static pressure of the inlet duct outlet under the working state is obtained by the inlet matching, and then the inlet model and flow field solution are established based on the outlet static pressure to obtain the external resistance D1 of the whole aircraft under the working state. According to the wind tunnel test results, as shown in the attached Figure 6 As shown, under the design state Ma=1.3, H=13km:

[0094] Incoming matching flow coefficient φ 目标 =0.805, at this time, the total pressure recovery coefficient of the inlet duct σ = 0.87; the frontal area A of the airway inlet at zero angle of attack 参考 =0.04235m 2 、Exit area A3=0.06468m 2 ; Far-field inflow data refer to standard atmospheric table; Full machine reference area S = 2.5m 2 .

[0095] The calculated inlet outlet p3 = 37510.4 pa. The CFD model for air intake simulation is established, and the conditions are set as follows: the far field is the free flow boundary, the inlet outlet is the static pressure boundary, and the fuselage and inlet are the no-slip wall boundaries. The calculation integral obtains the external resistance coefficient C of the UAV in the designed working state. D = 0.030697, the same as above can be calculated for the drag coefficient C of the UAV's inlet lip when φ = 1 D =0.003157, then the external resistance coefficient of the whole machine considering the overflow resistance in the design state is C D1 =0.02754.

[0096] On the other hand, by giving the parameters of the intake blocking cone, parametric modeling of the intake blocking cone is realized, and then a simulation model of the blocking cone in the clean state is established and solved to obtain the external resistance D2 of the whole machine in the blocking cone clean state.

[0097] Intake cone parametric modeling, as shown in the attached Figure 7As shown, a sketch is created, an initial cone angle θ = 15° is given, the position of the fuselage base point in front of the air inlet on the symmetry plane is determined, and a B-spline spline curve and a multi-section surface are established through the base point to generate a multi-section surface tangent to the air inlet lip, and the redundant fuselage and air inlet are cut off. The com interface of CATIA secondary development is obtained through VB programming, and part operation instructions are obtained through commands such as GetObject. The cone angle constraint of the sketch modification base point is controlled through partSet sketch1 = sketches1.Item ("sketch.1"), angle.Value = θ, and the output geometric model is updated.

[0098] The clean model of the plug cone output in the previous step is used to establish the whole aircraft simulation CFD model. The setting conditions are: the far field is the free flow boundary condition, the fuselage and the air intake plug cone are the no-slip wall boundary conditions, and the reference area is S = 2.5m 2 The external resistance coefficient C of the UAV with the initial blocking cone is obtained by simulation calculation. D2 =0.03529, and the resistance error of the UAV's working design state is |0.03529 / 0.02754-1|=28.1%. Since the external resistance and its corresponding external resistance coefficient are obtained in proportion, the external resistance error will remain unchanged as long as the same type of data is used. That is, the calculation formula of the external resistance error can also be: δ=|D2 / D1-1|.

[0099] By controlling the cone angle θ through successive approximation, repeat the above steps. Figure 8 The optimization curve of the cone angle is given. When the cone angle θ is 9° at the sixth iteration, C D2 =0.02810 and the error of the total aircraft external resistance under the flight design state is 2.03%. The iteration termination condition is δ<3%. The condition is met, the iteration is terminated, and the intake cone model is output.

[0100] See attached Figure 3 Based on the same inventive concept as in the above-mentioned embodiment, the embodiment of the present application further provides an air intake cone blocking design device, which includes:

[0101] An acquisition module, the acquisition module is used to obtain the external drag data of the target aircraft in a clean state based on a simulation model of the target blocking cone; wherein the simulation model is obtained based on a given cone angle of the target blocking cone;

[0102] The loop module is used to adjust the degree of a given cone angle according to the number of steps corresponding to the external resistance error data, and return a simulation model based on the target blocking cone to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and obtain the target cone angle; wherein the external resistance error data is obtained based on the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

[0103] Those skilled in the art should understand that the division of the various modules in the embodiment is merely a division of logical functions, and in actual application, all or part of them can be integrated into one or more actual carriers, and these modules can be implemented entirely in the form of software called through a processing unit, or entirely in the form of hardware, or in the form of a combination of software and hardware. It should be noted that each module in the air intake cone plugging design device in this embodiment corresponds one-to-one to each step in the air intake cone plugging design method in the aforementioned embodiment. Therefore, the specific implementation method of this embodiment can refer to the implementation method of the aforementioned air intake cone plugging design method, which will not be repeated here.

[0104] Based on the same inventive concept as in the aforementioned embodiment, an embodiment of the present application further provides a computer-readable storage medium storing a computer program. When the computer program is loaded and executed by a processor, an intake plugging cone design method as provided in an embodiment of the present application is implemented.

[0105] Based on the same inventive concept as in the above-mentioned embodiment, an embodiment of the present application further provides an electronic device, including a processor and a memory, wherein:

[0106] The memory is used to store computer programs;

[0107] The processor is used to load and execute a computer program so that the electronic device executes the air intake plugging cone design method provided in the embodiment of the present application.

[0108] In some embodiments, the computer readable storage medium may be a memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash memory, magnetic surface memory, optical disk, or CD-ROM; or various devices including one or any combination of the above memories. The computer may be various computing devices including intelligent terminals and servers.

[0109] In some embodiments, executable instructions may be in the form of a program, software, software module, script or code, written in any form of programming language (including compiled or interpreted languages, or declarative or procedural languages), and may be deployed in any form, including as a stand-alone program or as a module, component, subroutine or other unit suitable for use in a computing environment.

[0110] As an example, executable instructions may, but need not, correspond to a file in a file system, may be stored as part of a file that stores other programs or data, such as in one or more scripts in a HyperText Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files storing one or more modules, subroutines, or code portions).

[0111] By way of example, executable instructions may be deployed to be executed on one computing device, or on multiple computing devices located at one site, or on multiple computing devices distributed across multiple sites and interconnected by a communication network.

[0112] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or system 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 system. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, method, article or system including the element.

[0113] The serial numbers of the above-mentioned embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0114] Through the description of the above implementation methods, those skilled in the art can clearly understand that the above-mentioned embodiment methods can be implemented by means of software plus a necessary general hardware platform, and of course by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present application, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as a read-only memory / random access memory, a magnetic disk, or an optical disk), and includes a number of instructions for enabling a multimedia terminal device (which can be a mobile phone, a computer, a television receiver, or a network device, etc.) to execute the methods described in each embodiment of the present application.

[0115] In summary, the present application provides a method, device, storage medium and electronic device for designing an intake cone, the method comprising: obtaining external resistance data of a target aircraft in a clean state based on a simulation model of a target cone; wherein the simulation model is obtained based on a given cone angle of the target cone; adjusting the degree of the given cone angle according to the step number corresponding to the external resistance error data, and returning to the simulation model based on the target cone to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and the target cone angle is obtained; wherein the external resistance error data is obtained based on the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state. The present application considers the interference characteristics of the external flow field of the aircraft when the air inlet duct is working in the aircraft intake state at the initial stage of design, takes the external drag coefficient in the intake working state and the external drag coefficient of the intake plugging cone in the clean state as the control, takes the external drag error data as the basis and cooperates with the cyclic optimization of the parameters to step-by-step adjust the degree of the given cone angle so that the external flow field characteristics of the whole aircraft in the clean state, that is, with the air inlet plugging cone, are highly consistent with the external flow field characteristics of the whole aircraft in the intake working state of the target aircraft. The intake plugging cone is designed with the target cone angle optimized at this time as a parameter, which can effectively improve the quality of the intake plugging cone design, and thus provide better data support for the design of the aircraft.

[0116] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. A method for designing an air intake blocking cone, characterized in that: The following steps are involved: Based on the simulation model of the target blocking cone, the external drag data of the target aircraft in a clean state is obtained; wherein the simulation model is obtained based on a given cone angle of the target blocking cone; According to the number of steps corresponding to the external resistance error data, the degree of the given cone angle is adjusted, and the simulation model based on the target blocking cone is returned to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and the target cone angle is obtained; wherein the external resistance error data is obtained according to the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

2. The method for designing an air intake cone according to claim 1, characterized in that: Before adjusting the degree of the given cone angle according to the step number corresponding to the external resistance error data, the intake cone blocking design method further includes: Establishing a simulation model of the target aircraft in an intake state according to the pressure boundary of the outlet static pressure data of the intake duct; According to the simulation model of the target aircraft in the air intake state, the external drag coefficient of the target aircraft in the air intake state is obtained.

3. The method for designing an air intake cone according to claim 2, characterized in that: Before establishing the simulation model of the target aircraft in the intake state according to the pressure boundary of the outlet static pressure data of the intake duct, the intake cone design method further includes: According to the pressure wind tunnel test results of the air inlet of the target aircraft, the outlet static pressure data of the air inlet is obtained.

4. The method for designing an air intake cone according to claim 1, characterized in that: Before adjusting the degree of the given cone angle according to the step number corresponding to the external resistance error data, the intake cone blocking design method further includes: The external resistance error data is obtained according to the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

5. The method for designing an air intake cone according to claim 4, characterized in that: The external resistance error data is calculated according to the following formula: δ=|C D2 / C D1 -1| Among them, δ is the external resistance error data, C D2 is the external drag coefficient of the target aircraft in a clean state, C D1 is the external drag coefficient of the target aircraft in the intake state.

6. The method for designing an air intake cone according to claim 1, characterized in that: The stepping degree corresponding to the external resistance error data is adjusted to adjust the given cone angle, including: Determine the stepping frequency according to the external resistance error data; The stepping amount is increased or decreased on the degree of the given cone angle to adjust the degree of the given cone angle.

7. The method for designing an air intake cone according to claim 6, characterized in that: The stepping frequency is determined according to the external resistance error data, according to the following formula: Among them, dθ is the step number, and δ is the external resistance error data.

8. An air intake cone design device, characterized in that: include: An acquisition module, the acquisition module is used to obtain the external drag data of the target aircraft in a clean state based on a simulation model of a target blocking cone; wherein the simulation model is obtained based on a given cone angle of the target blocking cone; A loop module, wherein the loop module is used to adjust the degree of the given cone angle according to the step number corresponding to the external resistance error data, and return the simulation model based on the target blocking cone to obtain the external resistance data of the target aircraft in a clean state, until the external resistance error data meets the termination condition, and obtain the target cone angle; wherein the external resistance error data is obtained according to the external resistance coefficient of the target aircraft in the intake state and the external resistance coefficient of the target aircraft in the clean state.

9. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is loaded and executed by the processor, the intake cone plugging design method according to any one of claims 1 to 7 is implemented.

10. An electronic device, characterized in that: comprising a processor and a memory, wherein: The memory is used to store computer programs; The processor is used to load and execute the computer program so that the electronic device executes the intake cone design method according to any one of claims 1 to 7.

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