CN115795696B - Method, device, equipment and medium for generating ice shape in Rong Bing airfoil design process - Google Patents
Method, device, equipment and medium for generating ice shape in Rong Bing airfoil design process Download PDFInfo
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Abstract
The application discloses a method, a device, equipment and a medium for generating ice shape in the design process of ice-containing wing sections, which relate to the technical field of aerospace numerical optimization and comprise the following steps: parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and corresponding airfoil sample data sets; the wing section sample parameters are parameters of a non-ice-containing wing section; determining an ice shape data set corresponding to the wing profile sample data set, performing dimension reduction on the ice shape data set to obtain a first ice shape coefficient, and determining a mapping relation between wing profile sample parameters and the first ice shape coefficient; and determining Rong Bing airfoil sample parameters, and predicting according to the mapping relation to obtain the ice shape corresponding to Rong Bing airfoil sample parameters. Therefore, the method and the device establish the mapping relation between the wing profile and the ice shape, wherein the wing profile is the wing profile without considering ice containing, and then realize the rapid prediction from the ice containing wing profile to the corresponding ice shape based on the mapping relation, so that the purposes of shortening the design period of the ice containing wing profile and improving the design efficiency are achieved.
Description
Technical Field
The invention relates to the technical field of aerospace numerical optimization, in particular to a method, a device, equipment and a medium for ice shape in the process of designing an ice-containing airfoil.
Background
With the intelligent and unmanned development of combat, unmanned aerial vehicles play an increasingly wide role in the battlefield, including reconnaissance, striking, transportation and the like, and meanwhile, unmanned aerial vehicles are widely applied to civilian use. The requirements of unmanned aerial vehicle on large load and ultra-long-range endurance design require that the wing optimal design has good aerodynamic performance. In addition, unmanned aerial vehicle cruises the altitude and is in cloud fog coverage, inevitably encounters wing icing problem. In order to consider the strong aerodynamic performance of the wing design and the aerodynamic performance of the wing after icing, in recent years, the wing design research of the concept of ice containing appears, and the processing flexibility of the wing after icing is effectively improved.
In the design of the ice-containing wing profile, an optimization algorithm can iterate to generate a wing profile with a middle point, then a computational fluid dynamics (Computational Fluid Dynamics, CFD) method is used for solving the water drop impact characteristic and the ice shape corresponding to the wing profile, and further the wing profile aerodynamic performance after icing is considered to optimize the middle wing profile. Repeatedly, an optimized airfoil meeting both pre-icing and post-icing aerodynamic requirements is ultimately obtained. However, since the ice shape numerical simulation of the airfoil involves the processes of air flow field calculation, water drop flow field calculation, and icing thermodynamic model solving, the time is long, and the ice shape numerical simulation and the grid scale form a positive correlation, the extra design time is brought to the originally complex optimization design process.
Therefore, how to achieve the purpose of shortening the optimal design period of the ice-containing airfoil profile by improving the generation efficiency of the ice profile corresponding to the ice-containing airfoil profile is a problem to be solved in the field.
Disclosure of Invention
In view of the above, the present invention aims to provide a method, a device and a medium for generating ice shapes in the process of designing an ice-containing airfoil, which can achieve the purpose of shortening the period of optimizing the design of the ice-containing airfoil by improving the efficiency of generating ice shapes corresponding to the ice-containing airfoil, and the specific scheme is as follows:
in a first aspect, the present application discloses a method for generating ice shapes in an ice-containing airfoil design process, including:
parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile;
determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient;
and determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients.
Optionally, the parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters includes:
and carrying out parameterization representation on the initial airfoil by using a disturbance CST method to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters.
Optionally, the determining an ice shape data set corresponding to the airfoil sample data set includes:
an ice shape dataset corresponding to the airfoil sample dataset is determined based on a computational fluid dynamics numerical method.
Optionally, the dimension reduction of the ice-shape data set to obtain a first ice-shape coefficient corresponding to the ice-shape data set includes:
and performing dimension reduction on the ice-shaped data set by using a POD dimension reduction method to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set.
Optionally, the predicting, according to the mapping relationship between the airfoil sample parameter and the first ice shape coefficient, an ice shape corresponding to the ice-containing airfoil sample parameter includes:
determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter according to the mapping relation between the airfoil sample parameter and the first ice shape coefficient;
and predicting and obtaining the ice shape corresponding to the ice-containing airfoil profile sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter by using a POD reconstruction method.
Optionally, the predicting, by the POD reconstruction method and based on the second ice shape coefficient corresponding to the ice-containing airfoil sample parameter, an ice shape corresponding to the ice-containing airfoil sample parameter includes:
determining dimension reduction dimensions in the POD dimension reduction method;
and predicting the ice shape corresponding to the ice-containing airfoil sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil sample parameter by using a POD reconstruction method and the dimension reduction dimension.
Optionally, the determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter includes:
and determining a second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter based on the Kriging proxy model.
In a second aspect, the present application discloses a device for generating ice shape during design of ice-containing airfoil, comprising:
the sample data establishing module of the non-ice-containing airfoil is used for carrying out parameterization representation on the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile;
an ice shape data determining module of a non-ice-containing airfoil profile for determining an ice shape data set corresponding to the airfoil profile sample data set;
the mapping relation determining module is used for reducing the dimension of the ice-shaped data set to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set, and then determining the mapping relation between the wing-shaped sample parameter and the first ice-shaped coefficient;
and Rong Bing the ice shape determining module is used for determining the ice-containing airfoil sample parameters and predicting to obtain the ice shape corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficient.
In a third aspect, the present application discloses an electronic device comprising:
a memory for storing a computer program;
and the processor is used for executing the computer program to realize the ice shape generating method in the ice-containing airfoil design process.
In a fourth aspect, the present application discloses a computer-readable storage medium for storing a computer program; the method for generating the ice shape in the ice-containing wing profile design process is realized when the computer program is executed by a processor.
Therefore, the application provides a method for generating ice shape in the design process of ice-containing wing sections, which comprises the following steps: parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile; determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient; and determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients. In summary, the present application first establishes a mapping relationship between an airfoil and an ice shape, where the airfoil is an airfoil that does not consider ice containing, and then based on the mapping relationship, realizes rapid prediction from the ice containing airfoil to the corresponding ice shape, so as to achieve the purpose of shortening the optimization design period of the ice containing airfoil by improving the generating efficiency of the ice shape corresponding to the ice containing airfoil.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method of generating ice shapes during the design of an ice-tolerant airfoil disclosed herein;
FIG. 2 is a flow chart of a method of generating ice shapes during a particular ice-tolerant airfoil design process disclosed herein;
FIG. 3 is a schematic diagram of a device for generating ice during design of an ice-containing airfoil disclosed herein;
fig. 4 is a block diagram of an electronic device disclosed in the present application.
Description of the embodiments
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the design of the ice-containing wing profile, an optimization algorithm can iterate to generate a wing profile with a middle point, then a computational fluid mechanical method is used for solving the impact characteristics and the ice shape of water drops corresponding to the wing profile, and further the wing profile aerodynamic performance after icing is considered to optimize the middle wing profile. Repeatedly, an optimized airfoil meeting both pre-icing and post-icing aerodynamic requirements is ultimately obtained. However, since the ice shape numerical simulation of the airfoil involves the processes of air flow field calculation, water drop flow field calculation, and icing thermodynamic model solving, the time is long, and the ice shape numerical simulation and the grid scale form a positive correlation, the extra design time is brought to the originally complex optimization design process.
Therefore, the embodiment of the application provides a scheme for generating the ice shape in the design process of the ice-containing wing profile, and the aim of shortening the optimal design period of the ice-containing wing profile can be achieved by improving the generation efficiency of the ice shape corresponding to the ice-containing wing profile.
The embodiment of the application discloses a method for generating ice shapes in the design process of ice-containing wing sections, which is shown in fig. 1 and comprises the following steps:
step S11: parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing section sample parameters are wing section sample parameters of a non-ice-containing wing section.
In this embodiment, the initial airfoil profile is modified by a perturbing CST method
Parameterized representation is performed to obtain->
Individual airfoil sample parameters->
And an airfoil sample data set corresponding to said airfoil sample parameters +.>
It should be noted that the airfoil sample parameters are airfoil sample parameters of a non-ice tolerant airfoil, i.e., airfoil sample parameters that do not take into account the airfoil ice tolerant design.
For the first
The airfoil profile, its coordinates and sample parameters have the following relationship:
wherein, the liquid crystal display device comprises a liquid crystal display device,
is Hadamard product representing multiplication of matrix corresponding elements, +.>
，/>
Generally 0.5 and 1,/o>
Is the order.
Step S12: determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient.
In this embodiment, the determination of the airfoil sample dataset is based on a computational fluid dynamics numerical method
Individual ice-shape dataset->
And performing dimension reduction on the ice-shaped data set by using a POD dimension reduction method to obtain a first ice-shaped coefficient (I) corresponding to the ice-shaped data set>
。
The process of dimension reduction for the ice-shaped data set specifically comprises the following steps: the abscissa of the ice shape data is formed into a sample matrix
The method comprises the steps of carrying out a first treatment on the surface of the The sample matrix is decentered, and a standardized sample matrix is obtained>
Wherein->
For sample mean +.>
The method comprises the steps of carrying out a first treatment on the surface of the Constructing covariance matrix->
For->
Order real symmetric matrix->
Singular value decomposition is performed, wherein->
Is the dimension of the sample, resulting in feature values ordered from big to small +.>
And its corresponding feature vector->
The method comprises the steps of carrying out a first treatment on the surface of the Get front->
Characteristic value of->
Wherein->
For a given energy threshold, 99.9% is typically taken; will->
The individual feature vectors are called sample matrix->
Defining a mapping matrix
. Thus, each sample data can be effectively reduced in dimension by the factor +.>
The dimension-reduction representation is carried out,
，/>
is->
Column vectors of dimensions. Likewise, the +.>
The ordinate of the individual ice-shaped data->
Coefficient column vector after dimension reduction +.>
。
Step S13: and determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients.
In this embodiment, predicting, according to a mapping relationship between the airfoil sample parameter and the first ice shape coefficient, an ice shape corresponding to the ice-containing airfoil sample parameter specifically includes: determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter according to the mapping relation between the airfoil sample parameter and the first ice shape coefficient; and predicting and obtaining the ice shape corresponding to the ice-containing airfoil profile sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter by using a POD reconstruction method. It should be noted that, when the POD reconstruction method is used in this embodiment, the dimension of the dimension reduction of the POD in the foregoing process needs to be determined, and then, based on the second ice shape coefficient corresponding to the ice-containing airfoil sample parameter, the ice shape corresponding to the ice-containing airfoil sample parameter is predicted by the POD reconstruction method and the dimension reduction dimension.
In this embodiment, determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter specifically includes: and determining a second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter based on the Kriging proxy model.
Specifically, the expression of the proxy model is:
；/>
wherein, the liquid crystal display device comprises a liquid crystal display device,
representing a linear regression term, ++>
Is a polynomial basis function,/->
Is the weight corresponding to the basis function,
the random process model established based on the data space correlation meets the following conditions: hope->
Variance is->
. For any two different data points +.>
And->
The covariance of the random amount can be expressed as:
wherein, the liquid crystal display device comprises a liquid crystal display device,
referred to as a spatial correlation model, representing the correlation between random variables at different positions, which is related to the correlation function and the distance between data points, +.>
Is a relevant parameter. According to the optimal requirement of minimum mean square error, the optimal weight can be obtained
The following is shown:
wherein, the liquid crystal display device comprises a liquid crystal display device,
is->
Matrix of medium linear regression terms, +.>
Is a matrix of correlation functions, < >>
Is that
Parameters of the wing profile
As an argument, ice shape factor +.>
As a dependent variable, obtain
The individual matrix elements of (a) have the following form:
wherein the method comprises the steps of
And->
The mapping matrix is respectively an abscissa mapping matrix and an ordinate mapping matrix generated during the dimension reduction of the POD (point of sale)>
And->
Is the sample mean.
Therefore, the application provides a method for generating ice shape in the design process of ice-containing wing sections, which comprises the following steps: parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile; determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient; and determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients. In summary, the present application first establishes a mapping relationship between an airfoil and an ice shape, where the airfoil is an airfoil that does not consider ice containing, and then based on the mapping relationship, realizes rapid prediction from the ice containing airfoil to the corresponding ice shape, so as to achieve the purpose of shortening the optimization design period of the ice containing airfoil by improving the generating efficiency of the ice shape corresponding to the ice containing airfoil.
FIG. 2 is a flow chart of a method of generating ice shapes during a particular design of an ice-tolerant airfoil disclosed herein, as shown in FIG. 2, wherein the present application first identifies an initial airfoil and then generates the ice without consideration of the ice content
Airfoil parameters are calculated and CFD numerical simulation is then performed to obtain +.>
Ice shape, and dimension reduction of ice shape by POD to obtain +.>
And ice shape factor. Further, under the condition of considering ice containing, determining ice containing wing profile parameters, then obtaining corresponding ice shapes based on a Kriging proxy model, the ice containing wing profile parameters and ice shape coefficients and using a POD reconstruction method, and in summary, the method and the device establish a mapping relation between wing profiles and the ice shapes, wherein the wing profiles are wing profiles without considering ice containing, and then realize rapid prediction from the ice containing wing profiles to the corresponding ice shapes based on the mapping relation.
Correspondingly, the embodiment of the application also discloses a device for generating ice shape in the design process of the ice-containing wing profile, as shown in fig. 3, the device comprises:
the sample data establishing module 11 of the non-ice-containing airfoil is used for parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile;
an ice shape data determination module 12 of a non-ice tolerant airfoil for determining an ice shape data set corresponding to the airfoil sample data set;
the mapping relation determining module 13 is configured to reduce the dimension of the ice-shape data set to obtain a first ice-shape coefficient corresponding to the ice-shape data set, and then determine a mapping relation between the airfoil sample parameter and the first ice-shape coefficient;
and the Rong Bing airfoil ice shape determining module 14 is configured to determine an ice-containing airfoil sample parameter, and predict an ice shape corresponding to the ice-containing airfoil sample parameter according to a mapping relationship between the airfoil sample parameter and the first ice shape coefficient.
The more specific working process of each module may refer to the corresponding content disclosed in the foregoing embodiment, and will not be described herein.
Therefore, the application provides a method for generating ice shape in the design process of ice-containing wing sections, which comprises the following steps: parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile; determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient; and determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients. In summary, the present application first establishes a mapping relationship between an airfoil and an ice shape, where the airfoil is an airfoil that does not consider ice containing, and then based on the mapping relationship, realizes rapid prediction from the ice containing airfoil to the corresponding ice shape, so as to achieve the purpose of shortening the optimization design period of the ice containing airfoil by improving the generating efficiency of the ice shape corresponding to the ice containing airfoil.
Further, the embodiment of the application also provides electronic equipment. Fig. 4 is a block diagram of an electronic device 20, according to an exemplary embodiment, and the contents of the diagram should not be construed as limiting the scope of use of the present application in any way.
Fig. 4 is a schematic structural diagram of an electronic device 20 according to an embodiment of the present application. The electronic device 20 may specifically include: at least one processor 21, at least one memory 22, a display screen 23, an input output interface 24, a communication interface 25, a power supply 26, and a communication bus 27. Wherein the memory 22 is used for storing a computer program, which is loaded and executed by the processor 21 for realizing the following steps:
parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile;
determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient;
and determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients.
In some embodiments, the processor may specifically implement the following steps by executing the computer program stored in the memory:
and carrying out parameterization representation on the initial airfoil by using a disturbance CST method to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters.
In some embodiments, the processor may specifically implement the following steps by executing the computer program stored in the memory:
an ice shape dataset corresponding to the airfoil sample dataset is determined based on a computational fluid dynamics numerical method.
In some embodiments, the processor may specifically implement the following steps by executing the computer program stored in the memory:
and performing dimension reduction on the ice-shaped data set by using a POD dimension reduction method to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set.
In some embodiments, the processor may specifically implement the following steps by executing the computer program stored in the memory:
determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter according to the mapping relation between the airfoil sample parameter and the first ice shape coefficient;
and predicting and obtaining the ice shape corresponding to the ice-containing airfoil profile sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter by using a POD reconstruction method.
In some embodiments, the processor may specifically implement the following steps by executing the computer program stored in the memory:
determining dimension reduction dimensions in the POD dimension reduction method;
and predicting the ice shape corresponding to the ice-containing airfoil sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil sample parameter by using a POD reconstruction method and the dimension reduction dimension.
In some embodiments, the processor may specifically implement the following steps by executing the computer program stored in the memory:
and determining a second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter based on the Kriging proxy model.
In this embodiment, the power supply 26 is used to provide an operating voltage for each hardware device on the electronic device 20; the communication interface 25 can create a data transmission channel between the electronic device 20 and an external device, and the communication protocol to be followed is any communication protocol applicable to the technical solution of the present application, which is not specifically limited herein; the input/output interface 24 is used for obtaining external input data or outputting external output data, and the specific interface type thereof may be selected according to the specific application needs, which is not limited herein.
The memory 22 may be a read-only memory, a random access memory, a magnetic disk, an optical disk, or the like, and the resources stored thereon may include the computer program 221, which may be stored in a temporary or permanent manner. The computer program 221 may further include a computer program for performing other specific tasks in addition to the computer program for performing the method of generating ice shapes in the Rong Bing airfoil design process performed by the electronic device 20 disclosed in any of the foregoing embodiments.
Further, the embodiment of the application also discloses a computer readable storage medium for storing a computer program; the method for generating the ice shape in the ice-containing wing profile design process is realized when the computer program is executed by a processor.
For specific steps of the method, reference may be made to the corresponding contents disclosed in the foregoing embodiments, and no further description is given here.
In this application, each embodiment is described in a progressive manner, and each embodiment focuses on the difference from other embodiments, and the same or similar parts between the embodiments refer to the devices disclosed in the embodiments, so that the description is relatively simple because it corresponds to the method disclosed in the embodiments, and the relevant parts refer to the description of the method section.
Those of skill would further appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both, and that the various illustrative elements and steps are described above generally in terms of functionality in order to clearly illustrate the interchangeability of hardware and software. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present application.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software modules may be disposed in Random Access Memory (RAM), memory, read Only Memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.
Finally, it is further noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation 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 may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The method, the device, the equipment and the storage medium for generating the ice shape in the design process of the ice-containing airfoil profile provided by the application are described in detail, and specific examples are applied to the description of the principle and the implementation mode of the application, and the description of the examples is only used for helping to understand the method and the core idea of the application; meanwhile, as those skilled in the art will have modifications in the specific embodiments and application scope in accordance with the ideas of the present application, the present description should not be construed as limiting the present application in view of the above.
Claims (8)
1. The method for generating the ice shape in the design process of the ice-containing airfoil profile is characterized by comprising the following steps of:
parameterizing the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile;
determining an ice shape data set corresponding to the airfoil sample data set, reducing the dimension of the ice shape data set to obtain a first ice shape coefficient corresponding to the ice shape data set, and then determining the mapping relation between the airfoil sample parameters and the first ice shape coefficient;
determining Rong Bing airfoil sample parameters, and predicting ice shapes corresponding to the ice-containing airfoil sample parameters according to the mapping relation between the airfoil sample parameters and the first ice shape coefficients;
the dimension reduction is performed on the ice-shaped data set to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set, which comprises the following steps: performing dimension reduction on the ice-shaped data set by using a POD dimension reduction method to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set;
and predicting the ice shape corresponding to the ice-containing airfoil sample parameter according to the mapping relation between the airfoil sample parameter and the first ice shape coefficient, wherein the method comprises the following steps: determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter according to the mapping relation between the airfoil sample parameter and the first ice shape coefficient; and predicting and obtaining the ice shape corresponding to the ice-containing airfoil profile sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter by using a POD reconstruction method.
2. The method for generating ice shapes in a Rong Bing airfoil design process according to claim 1, wherein said parameterizing an initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters comprises:
and carrying out parameterization representation on the initial airfoil by using a disturbance CST method to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters.
3. The method of generating ice shapes in a Rong Bing airfoil design process of claim 1, wherein said determining an ice shape dataset corresponding to said airfoil sample dataset comprises:
an ice shape dataset corresponding to the airfoil sample dataset is determined based on a computational fluid dynamics numerical method.
4. The method according to claim 1, wherein predicting, by a POD reconstruction method, an ice shape corresponding to the ice-containing airfoil sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil sample parameter, comprises:
determining dimension reduction dimensions in the POD dimension reduction method;
and predicting the ice shape corresponding to the ice-containing airfoil sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil sample parameter by using a POD reconstruction method and the dimension reduction dimension.
5. The method of claim 1, wherein determining a second ice shape factor corresponding to the ice containing airfoil sample parameter comprises:
and determining a second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter based on the Kriging proxy model.
6. An ice shape generating device in the process of designing an ice-containing airfoil, which is characterized by comprising:
the sample data establishing module of the non-ice-containing airfoil is used for carrying out parameterization representation on the initial airfoil to obtain a plurality of airfoil sample parameters and airfoil sample data sets corresponding to the airfoil sample parameters; the wing profile sample parameters are wing profile sample parameters of a non-ice-containing wing profile;
an ice shape data determining module of a non-ice-containing airfoil profile for determining an ice shape data set corresponding to the airfoil profile sample data set;
the mapping relation determining module is used for reducing the dimension of the ice-shaped data set to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set, and then determining the mapping relation between the wing-shaped sample parameter and the first ice-shaped coefficient;
the Rong Bing airfoil ice shape determining module is used for determining an ice-containing airfoil shape sample parameter, and predicting to obtain an ice shape corresponding to the ice-containing airfoil shape sample parameter according to the mapping relation between the airfoil shape sample parameter and the first ice shape coefficient;
the mapping relation determining module is specifically configured to: performing dimension reduction on the ice-shaped data set by using a POD dimension reduction method to obtain a first ice-shaped coefficient corresponding to the ice-shaped data set;
the ice shape determining module of the ice containing airfoil is specifically used for: determining a second ice shape coefficient corresponding to the ice-containing airfoil sample parameter according to the mapping relation between the airfoil sample parameter and the first ice shape coefficient; and predicting and obtaining the ice shape corresponding to the ice-containing airfoil profile sample parameter based on the second ice shape coefficient corresponding to the ice-containing airfoil profile sample parameter by using a POD reconstruction method.
7. An electronic device, comprising:
a memory for storing a computer program;
a processor for executing the computer program to implement a method of generating ice shapes in a Rong Bing airfoil design process as claimed in any of claims 1 to 5.
8. A computer-readable storage medium for storing a computer program; wherein the computer program when executed by a processor implements a method of generating ice shapes in a Rong Bing airfoil design process as claimed in any of claims 1 to 5.
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